NASA - NSSDC - Master Catalog

Transcripción

Cronología de
Lanzamientos
Espaciales
Año 2005
Recopilación de datos Ing. Eladio Miranda Batlle.
Los textos, imágenes y tablas fueron obtenidos de la National Space Science.
Data Center. NASA
NASA - NSSDC - Spacecraft - Query Results
Monday, 18 October 2010
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
Spacecraft Query Results
Publications
There were 73 spacecraft returned.
Maps
Spacecraft Name
NSSDC ID
Launch Date
New/Updated Data
AMC 12
2005-003A
2005-02-03
Lunar/Planetary Events
AMS 23
2005-052A
2005-12-29
Anik F1R
2005-036A
2005-09-09
Apstar 6
2005-012A
2005-04-12
Astromag FF
ASTRMAG
2005-01-01
CartoSat 1
2005-017A
2005-05-10
Cosmos 2414
2005-002A
2005-01-20
Cosmos 2415
2005-034A
2005-09-02
Cosmos 2417
2005-050C
2005-12-25
Cosmos 2418
2005-050B
2005-12-25
Cosmos 2419
2005-050A
2005-12-25
CubeSat 11-5
2005-043F
2005-10-27
DART
2005-014A
2005-04-15
Deep Impact Impactor (DII) Vehicle
2005-001D
2005-01-12
Deep Impact/EPOXI
2005-001A
2005-01-12
DirecTV 8
2005-019A
2005-05-22
Express AM2
2005-010A
2005-03-29
Express AM3
2005-023A
2005-06-24
Foton M-2
2005-020A
2005-05-31
FSW 21
2005-027A
2005-08-02
FSW 22
2005-033A
2005-08-29
Galaxy 14
2005-030A
2005-08-13
Galaxy 15
2005-041A
2005-10-13
GIOVE-A
2005-051A
2005-12-28
Gonets-D1M 1
2005-048A
2005-12-21
Hamsat
2005-017B
2005-05-05
Inmarsat 4-F1
2005-009A
2005-03-11
Inmarsat 4-F2
2005-044A
2005-11-08
Insat 4A
2005-049A
2005-12-21
Intelsat Americas 8
2005-022A
2005-06-23
Maqsat
2005-005B
2005-02-12
Mars Reconnaissance Orbiter
2005-029A
2005-08-12
Monitor-E
2005-032A
2005-08-26
Moz 5/Safir/Rubin 5
2005-043G
2005-10-27
MSG 2
2005-049B
2005-12-21
Mtsat-1R
2005-006A
2005-02-26
http://nssdc.gsfc.nasa.gov/nmc/spacecraftSearch.do[17/10/2010 23:29:29]
NASA - NSSDC - Spacecraft - Query Results
Navstar 57
2005-038A
2005-09-26
NOAA 18
2005-018A
2005-05-20
OICETS
2005-031A
2005-08-23
Progress M-52
2005-007A
2005-02-28
Progress M-53
2005-021A
2005-06-16
Progress M-54
2005-035A
2005-09-08
Progress M-55
2005-047A
2005-12-21
Reimei
2005-031B
2005-08-23
Rodnik
2005-048B
2005-12-21
Shenzhou 6
2005-040A
2005-10-12
Shijian 7
2005-024A
2005-07-05
Sinah 1
2005-043D
2005-10-27
Sloshsat
2005-005C
2005-02-12
Soyuz-TMA 6
2005-013A
2005-04-15
Soyuz-TMA 7
2005-039A
2005-10-01
Spaceway 1
2005-015A
2005-04-26
Spaceway 2
2005-046A
2005-11-16
SSETI-Express
2005-043E
2005-10-27
STP-R1
2005-037A
2005-09-23
STS 114
2005-026A
2005-07-26
SuitSat
2005-035C
2005-09-08
Suzaku
2005-025A
2005-07-10
Syracuse 3A
2005-041B
2005-10-13
Tatiana
2005-002C
2005-01-20
Telcom 2
2005-046B
2005-11-16
Thaicom 4
2005-028A
2005-08-11
TNS-0
2005-007C
2005-03-28
TopSat
2005-043B
2005-10-27
Tsinghua
2005-043A
2005-10-27
USA 181
2005-004A
2005-02-03
USA 182
2005-016A
2005-04-30
USA 186
2005-042A
2005-10-19
UWE 1
2005-043C
2005-10-27
Venus Express
2005-045A
2005-11-09
XM 3
2005-008A
2005-03-01
XSS-11
2005-011A
2005-04-11
XTAR-EUR
2005-005A
2005-02-12
+ Privacy Policy and Important Notices
http://nssdc.gsfc.nasa.gov/nmc/spacecraftSearch.do[17/10/2010 23:29:29]
NASA Official: Dr. Ed Grayzeck
Curator: E. Bell, II
Version 4.0.14, 08 October 2010
NASA - NSSDC - Spacecraft - Details
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
AMC 12
Publications
NSSDC ID: 2005-003A
Maps
New/Updated Data
Alternate Names
Description
AMC 12 is an American geostationary satellite that was
launched by a Proton-M rocket from Baikonur at 03:27 UT on 3
February 2005. The five tonne satellite carries 72 C-band
transponders to provide voice and video services to the North
and South Americas, and Africa through separate beams to
each region, after parking over the Atlantic Ocean
28526
Facts in Brief
Launch Date: 2005-0203
Launch
Vehicle: Proton-M
Launch Site: Tyuratam
(Baikonur Cosmodrome),
Kazakhstan
Funding Agency
Unknown (United States)
Discipline
Communications
Additional
Information
Launch/Orbital
information for AMC 12
Experiments on AMC 12
Data collections from AMC
12
Questions or comments
about this spacecraft can
be directed to: Coordinated
Request and User Support
Office.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2005-003A[17/10/2010 23:51:43]
NSSDC Master
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Spacecraft
Experiments
Data Collections
Personnel
AMS 23
Publications
NSSDC ID: 2005-052A
Maps
New/Updated Data
Alternate Names
Description
AMS 23, with a pre-launch name of Worldsat 3, is an
American geostationary communications satellite that was
launched by a Proton-M rocket from Baikonur at 02:28 UT on
29 December 2005. The five tonne craft carries 20 high-power
Ku-band, and 18 C-band transponders to provide voice, video
and internet services to the Asia-Pacific region after parking
over 172 deg-E longitude.
Worldsat 3
28924
Facts in Brief
Launch
Vehicle: Proton-M
Kazakhstan
Funding Agency
Discipline
Communications
Additional
Information
Launch/Orbital
information for AMS 23
Experiments on AMS 23
Data collections from AMS
23
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
Anik F1R
Publications
NSSDC ID: 2005-036A
Maps
New/Updated Data
Alternate Names
Description
Anik F1R is a Canadian geostationary communications satellite
that was launched by a Proton-M rocket from Baikonur at
21:53 UT. The 4 tonne, 10 kW satellite carries 24 C-band, and
32 Ku-band transponders to provide voice, video and internet
communications to all of North America after parking over
107.3 deg-W longitude. It replaces the aging ANIK F1 satellite.
28868
Facts in Brief
Launch
Vehicle: Proton-M
Kazakhstan
Funding Agency
Unknown (Canada)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Anik F1R
Experiments on Anik F1R
Data collections from Anik
F1R
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
Apstar 6
Publications
NSSDC ID: 2005-012A
Maps
New/Updated Data
Alternate Names
Description
Apstar 6 is a Chinese (Hong Kong) geostationry
communications satellite that was launched by a Long March
3B rocket from Xichang Satellite Launch Center in Sichuan
province at 12:00 UT on 12 April 2005. The 4.8 tonne satellite
carries 38 C-band and 12 Ku-band transponders to provide
digital multimedia transmissions to East Asian countries, India,
and Australia, replacing the aging APSTAR 1A.
28638
Facts in Brief
Launch Vehicle: Long
March 3B
Launch Site: Xichang,
Peoples Republic of China
Funding Agency
Unknown (Russia)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Apstar 6
Experiments on Apstar 6
Data collections from
Apstar 6
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
Astromag FF
Publications
NSSDC ID: ASTRMAG
Maps
New/Updated Data
Description
Astromag Free-Flyer (FF) permits measurements of high
energy (>1GeV/nucleon) cosmic ray nuclei and electrons with
unprecedented accuracy and sensitivity. The primary science
objectives for Astromag FF are: to test cosmological models by
searching for antimatter and dark matter candidates; to
measure the high energy spectra of antiprotons and protons; to
study the origin and evolution of matter in the galaxy by direct
sampling of galactic material for evidence of nucleosynthesis
and galactic evolutionary effects; to study the origin and
acceleration of the relativistic particle plasma in the galaxy and
its effects on the dynamics and evolution of the galaxy; and to
measure the isotopic composition of cosmic ray nuclei at
energies of several GeV/nucleon and with previously
unattained sensitivity. In 1988, Astromag was originally
designed to be one facility on the Space Station Freedom
(SSF), and experiments were selected in 1989. In late 1990, it
became clear that facilities the size and scope of Astromag
could not be accommodated on a reduced-scale SSF, so an
Astromag Free-Flyer concept was developed and proposed in
May 1991. In June 1991, the Space Science and Applications
Advisory Committee moved Astromag FF from first to fifth in
the OSSA queue of missions for the 1990's, and therefore it is
not currently funded and it will not be launched before about
2005, if ever. Astromag FF consists of: a magnet of two
identical 1.44-m diameter magnet coils of superconducting
NbTi wire, with a 1.67-m separation; surrounded by a 2250 liter
liquid helium dewar in the spacecraft's central section; with a
scientific experiment (LISA or WiZard) on each end; plus the
primary power, attitude control, and communications subsystems, etc. The magnetic coils are about 10-cm long, and a
few centimeters thick. Their detailed structure is not yet
decided. The coil axes are colinear with each other and with
the spacecraft longitudinal axis, and the spacecraft
experiments are attached to the central section at the ends of
this axis. The magnet uses a design current of about 800 A
and the peak field at each coil is approximately 7 T, but
decreases rapidly with distance from the coil. To make the
dipole moment as low as possible, the coils have opposite
polarity. (So when the coils are powered to 800 A, the force
pushing the two coils apart is just over 35 metric tons.) Since
the coils are superconducting, the circulating current decays
less than 1% per year, so that the magnetic field is maintained
without a need for continuous application of power. The
spacecraft is planned to be in a low (500 km altitude) circular
geocentric orbit, and the mission lifetime is expected to be 2
years. The attitude control system must provide time-tagged
attitude knowledge to 1 or 2 degrees accuracy for each axis,
and give a pointing control accuracy of 10 degrees about each
axis. The attitude knowledge is provided by two earth horizon
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=ASTRMAG[17/10/2010 23:54:44]
Alternate Names
Astromag Free-Flyer
SS/Astromag
Facts in Brief
Launch Vehicle: Atlas
Launch Site: Cape
Canaveral, United States
Mass: 5250.0 kg
Funding Agency
NASA-Office of Space
Science (United States)
Discipline
Astronomy
Additional
Information
Launch/Orbital
information for Astromag
FF
Experiments on Astromag
FF
Astromag FF
Office.
scanners and a 3-axis magnetometer on a 50-foot boom, plus
sun sensors. The pointing control is done with a pitch wheel
momentum-biased system using magnetic torquers for initial
acquisition, wheel momentum unloading, spacecraft nutation
damping, and roll/yaw control. The power supply system,
composed of two solar panels, with areas of approximately 15
sq m, and two 50-Ahr NiCd batteries, for use during spacecraft
eclipses, provides the required 1250 W orbital average power
at +28 V, and the 2500 W for initial magnet charging. During
full sun periods with fully charged batteries, approximately
2880 W is expected to be available. The command and data
handling system is based on the Small Explorer Data System
and it provides an orbital average telemetry data stream of 100
kbps and the capability for its on-board storage in 2.5 Gbits of
bulk memory, real-time WiZard diagnostic data at 250 kbps,
and stored and real-time command processing for either 1 or 2
kbps rates, plus an additional 1.25 Mbps high speed serial port
for stored data dumps. The RF communications system
consists of NASA Standard Transponders, power amplifier, 28
dB high-gain pointable S-band antenna, omnidirectional
antennas, and electronics. It performs stored data dumps at up
to 2 Mbps through the Tracking and Data Relay Satellite
System for about 21.8 minutes every six hours, 1kbps
telemetry and command communications, and real-time data
transmission at 250 kbps (for WiZard diagnostic data). The
best reference for details and descriptions of Astromag FF and
its experiments is the document, Astromag Free-Flyer, Vols. I
and II, May 1991, done at GSFC which provides the results of
the Astromag FF program study and recommendations. It is
available through the project personnel.
Personnel
Name
Role
Original Affiliation
E-mail
Dr. Robert E.
Streitmatter
General
Contact
NASA Goddard Space
Flight Center
[email protected]
Dr. Robert
Golden
General
Contact
NASA Johnson Space
Center
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=ASTRMAG[17/10/2010 23:54:44]
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
CartoSat 1
Publications
NSSDC ID: 2005-017A
Maps
New/Updated Data
Alternate Names
Description
CartoSat 1 is an Indian (ISRO) mapping and remote-sensing
satellite that was launched by a PSLV C6 rocket from
Sriharikota on the southeastern coast of India, at 04:44 UT on
5 May 2005. The 1.56 tonne satellite carries two f/4.5,
Panchromatic cameras, one 26 degrees ahead of the nadir,
and another at 5 degrees behind the nadir. Together they
enable a stereoscopic image at a resolution of 2.5 m. Both
cameras scan cross-track to image a swath of 30 km with the
images being stored in a 12,000 pixel CCD. It stores the data
in a 120 GB memory to be downlinked over Indian (or
Indonesian and Russian) passes. The data from the satellite
will help in topographic mapping, land use, forest cover, and
river flow assessment.
28649
Facts in Brief
Launch Vehicle: PSLV
Launch Site: Sriharikota,
India
Mass: 1560.0 kg
Funding Agency
Indian Space Research
Organization (India)
Discipline
Earth Science
Additional
Information
Launch/Orbital
information for CartoSat 1
Experiments on CartoSat 1
CartoSat 1
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
Cosmos 2414
Publications
NSSDC ID: 2005-002A
Maps
New/Updated Data
Alternate Names
Description
Cosmos 2414 is a Russian military satellite that was launched
by a Cosmos-3M rocket from Plesetsk at 03:00 UT on 20
January 2005.
28521
Facts in Brief
Launch
Vehicle: Cosmos
Launch Site: Plesetsk,
Russia
Funding Agency
Unknown (Russia)
Discipline
Surveillance and Other
Military
Additional
Information
Launch/Orbital
information for Cosmos
2414
Experiments on Cosmos
2414
Cosmos 2414
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
Cosmos 2415
Publications
NSSDC ID: 2005-034A
Maps
New/Updated Data
Alternate Names
Description
Cosmos 2415 is a Russian military satellite that was launched
by a Soyuz-U rocket from Baikonur at 09:50 UT on 2
September 2005.
28841
Facts in Brief
Launch
Vehicle: Soyuz-U
Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Military
Additional
Information
Launch/Orbital
2415
2415
Cosmos 2415
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
Cosmos 2417
Publications
NSSDC ID: 2005-050C
Maps
New/Updated Data
Alternate Names
Description
Cosmos 2417 is one of the three latest additions to the
Russian GLONASS navigational fleet. They were launched by
a Proton-K rocket from Baikonur at 05:07 UT on 25 December
2005. They will be positioned in Slot-3. For the status of the
constellation, see
http://www.glonass-center.ru/nagu.txt
Glonass 798
28917
Facts in Brief
Launch
Vehicle: Proton-K
Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Uncategorized Cosmos
Additional
Information
Launch/Orbital
2417
2417
Cosmos 2417
Office.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2005-050C[17/10/2010 23:57:29]
NSSDC Master
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Spacecraft
Experiments
Data Collections
Personnel
Cosmos 2418
Publications
NSSDC ID: 2005-050B
Maps
New/Updated Data
Alternate Names
Description
constellation, see
Glonass 713
28916
Facts in Brief
Launch
Vehicle: Proton-K
Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Additional
Information
Launch/Orbital
2418
2418
Cosmos 2418
Office.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2005-050B[17/10/2010 23:58:23]
NSSDC Master
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Spacecraft
Experiments
Data Collections
Personnel
Cosmos 2419
Publications
NSSDC ID: 2005-050A
Maps
New/Updated Data
Alternate Names
Description
constellation, see
Glonass 714
28915
Facts in Brief
Launch
Vehicle: Proton-K
Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Additional
Information
Launch/Orbital
2419
2419
Cosmos 2419
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
CubeSat 11-5
Publications
NSSDC ID: 2005-043F
Maps
New/Updated Data
Alternate Names
Description
CubeSat 11-5 is a Japanese picosatellite that was launched by
a Cosmos 3M rocket from Plesetsk at 06:52 UT on 27 October
2005. (It was actually released from the microsatellite, SSETI).
OSCAR 58
28895
Facts in Brief
Launch
Vehicle: Cosmos
Russia
Mass: 1.0 kg
Funding Agency
University of Tokyo
(Japan)
Disciplines
Communications
Engineering
Additional
Information
Launch/Orbital
information for CubeSat
11-5
Experiments on CubeSat
11-5
CubeSat 11-5
Office.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2005-043F[17/10/2010 23:59:32]
NSSDC Master
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Experiments
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Personnel
DART
Publications
NSSDC ID: 2005-014A
Maps
New/Updated Data
Alternate Names
Description
DART (Demonstration of Autonomous Rendezvous
Technology) was a technology demonstrator that was
launched by a Pegasus-XL HAPS rocket from an L-1011 cargo
aircraft flying out of Vandenberg AFB at 18:25 UT on 15 April
2005. The satellite was to test its capability to rendezvous and
maneuver around a specially equipped DoD satellite,
MUBLCOM (1999-026B). A malfunction of the satellite, while it
had reached 91 m from the target satellite, resulted in the
failure of the mission.
Demonstration of
Autonomous Rendezvous
Technology
28642
Facts in Brief
Launch
Vehicle: Pegasus XL
Launch
Site: Vandenberg AFB,
United States
Mass: 360.0 kg
Funding Agency
National Aeronautics and
Space Administration
(United States)
Discipline
Technology Applications
Additional
Information
Launch/Orbital
information for DART
Experiments on DART
DART
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
Deep Impact Impactor (DII) Vehicle
Publications
NSSDC ID: 2005-001D
Maps
New/Updated Data
Description
Facts in Brief
The Deep Impact Impactor (DII) vehicle was designed to
collide with Comet 9P/Tempel 1 at over 10 km/s, producing a
crater and ejecting material which could be observed by the
Deep Impact flyby bus. The scientific objectives of the mission
are to: improve the knowledge of the physical characteristics of
cometary nuclei and directly assess the interior of cometary
nucleus; determine properties of the surface layers such as
density, strength, porosity, and composition from the crater and
its formation; study the relationship between the surface layers
of a cometary nucleus and the possibly pristine materials of the
interior by comparison of the interior of the crater with the
surface before impact; and improve our understanding of the
evolution of cometary nuclei, particularly their approach to
dormancy, by comparing the interior and the surface.
Observations were made of the ejecta, much of which
represented pristine material from the interior of the comet, the
crater formation process, the resulting crater, and outgassing
from the nucleus, particularly the newly exposed surface. This
project was selected as a Discovery class mission in July,
1999.
Launch Vehicle: Delta
II
Launch Site: Cape
Mass: 370.0 kg
Spacecraft and Subsystems
The DII projectile is made of primarily copper (49%) and only
24% aluminum so it will be easily identifiable and minimize
contamination in the spectra after the projectile is largely
vaporized and mixed in with the comet ejecta on impact. The
impactor is a short hexagonal cylinder built above the copper
cratering mass. It has a small hydrazine propulsion system for
targeting which can provide delta-V of 25 m/s. Targeting is
accomplished using a high-precision star-tracker, autonavigation algorithms, and the Impactor Targeting Sensor
(ITS), a camera which provides images for autonomous control
and targeting. The ITS will operate until impact, and images
will be sent back to Earth via the flyby spacecraft.
Communication with the flyby spacecraft is via S-band. The
impactor was mechanically and electrically connected to the
flyby spacecraft until 24 hours prior to encounter. After
separation it ran on internal battery power.
Mission Profile
Deep Impact launched on 12 January 2005 at 18:47:08.574 UT
(1:47:08 p.m. EST) on a Delta II. The spacecraft transferred
into a heliocentric orbit and rendezvoused with comet
P/Tempel 1 in July 2005. Deep Impact was 880,000 km from
the comet on 3 July 2005 moving at a velocity of 10.2 km/s
relative to the comet. The projectile was released at this point
and shortly after release the flyby spacecraft executed a
maneuver to slow down relative to the impactor by 120 m/s
and divert by 6 m/s. On 4 July the impactor struck the sunlit
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2005-001D[18/10/2010 0:00:24]
Funding Agency
(United States)
Discipline
Planetary Science
Additional
Information
Launch/Orbital
information for Deep
Impact Impactor (DII)
Vehicle
PDMP information for
Deep Impact Impactor
(DII) Vehicle
Telecommunications
Vehicle
Experiments on Deep
Vehicle
Data collections from Deep
Vehicle
be directed to: Dr. David R.
Williams.
side of the comet nucleus 24 hours after release, at 5:52 UT
(1:52 a.m. EDT). At 10.2 km/s velocity, the impactor had an
impact energy of about 19 gigajoules, and hit at an oblique
angle of approximately 25 degrees. Material from the nucleus
was ejected into space and the impactor and much of the
ejecta was vaporized.
The flyby spacecraft was approximately 10,000 km away at the
time of impact and began imaging 60 seconds before impact.
The comet and spacecraft were about 0.89 AU from Earth and
1.5 AU from the Sun during the encounter. Selected impactor
images and flyby images and spectra were returned to Earth in
real time during the encounter. Primary data return will be over
the first day after encounter, with a 28 day supplemental data
return period. Earth-based observatories also studied the
impact. The total budget for the mission was $240 million.
For information on the Deep Impact Flyby Bus, see:
http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2005001A
Personnel
Name
Role
E-mail
Dr. Michael
F. A'Hearn
Mission Principal
Investigator
University of Maryland
[email protected]
Mr. James E.
Graf
Project Manager
NASA Jet Propulsion
Laboratory
[email protected]
NSSDC Master
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Experiments
Data Collections
Personnel
Deep Impact/EPOXI
Publications
NSSDC ID: 2005-001A
Maps
New/Updated Data
Deep Impact/EPOXI
Description
The goals of the Deep Impact mission were to rendezvous with
comet 9P/Tempel 1 and launch a projectile into the comet
nucleus. Observations were made of the ejecta, much of which
represented pristine material from the interior of the comet, the
crater formation process, the resulting crater, and outgassing
from the nucleus, particularly the newly exposed surface. The
scientific objectives of the mission are to: improve the
knowledge of the physical characteristics of cometary nuclei
and directly assess the interior of cometary nucleus; determine
properties of the surface layers such as density, strength,
porosity, and composition from the crater and its formation;
study the relationship between the surface layers of a
cometary nucleus and the possibly pristine materials of the
interior by comparison of the interior of the crater with the
surface before impact; and improve our understanding of the
evolution of cometary nuclei, particularly their approach to
dormancy, by comparing the interior and the surface. This
project was selected as a Discovery class mission in July,
1999. After the primary mission, Deep Impact was selected for
a two-part extended mission designated EPOXI.
The spacecraft consists of a 370 kg cylindrical copper impactor
attached to a 650 kg flyby bus. The spacecraft is a box-shaped
honeycomb aluminum framework with a flat rectangular
Whipple debris shield mounted on one side to protect
components during comet close approach. Body mounted on
the framework are one high- and one medium-resolution
instrument, each of which consists of an imaging camera and
an infrared spectrometer which will be used to observe the
ejected ice and dust, much of which will be exposed to space
for the first time in over 4 billion years. The medium resolution
camera has a field of view (FOV) of 0.587 degrees and a
resolution of 7 m/pixel at 700 km distance and is used for
navigation and context images. The high resolution camera
has a FOV of 0.118 degrees and a resolution of 1.4 m/pixel at
700 km. The infrared spectrometers cover the range from 1.05
to 4.8 micrometers with FOV of 0.29 degrees (hi-res) and 1.45
degrees (lo-res). The total flyby bus instrument payload has a
mass of 90 kg and will use an average of 92 W during
encounter.
The flyby spacecraft measures approximately 3.2 m x 1.7 m x
2.3 m, is three-axis stabilized and uses a blowdown hydrazine
primary propulsion system with 5000 N-s RCS total impulse
providing a total delta-V of 190 m/s. Communications with the
ground from the flyby bus are via X-band (8.000 MHz) through
a 1 meter diameter parabolic dish antenna mounted on a 2axis gimbal or through a fixed low-gain antenna.
Alternate Names
Deep Impact
EPOXI
28517
Facts in Brief
II
Launch Site: Cape
Mass: 650.0 kg
Nominal
Power: 620.0 W
Funding Agency
(United States)
Discipline
Planetary Science
Additional
Information
Launch/Orbital
Impact/EPOXI
Experiments on Deep
Impact/EPOXI
Data collections from Deep
Impact/EPOXI
Williams.
Communication between the impactor and flyby spacecraft is
in S-band. The uplink data rate will be 125 bps, downlink will
be at 175 kbps. Power of 620 W at the encounter is provided
by a 7.2 square meter solar array and stored in a small NiH2
battery. The spacecraft control system consists of four
hemispherical resonator gyros, two star trackers, reaction
wheels, and hydrazine thrusters. Pointing accuracy is 200
microradians with 65 microradian knowledge. Thermal control
is achieved by insulating blankets, surface radiators, finishes,
and heaters. The spacecraft has two redundant RAD750
computers with 309 MB each of memory for scientific data.
The Impactor
The impactor projectile is made of primarily copper (49%) and
only 24% aluminum so it will be easily identifiable and
minimize contamination in the spectra after the projectile is
largely vaporized and mixed in with the comet ejecta on
impact. The impactor is a short hexagonal cylinder built above
the copper cratering mass. It has a small hydrazine propulsion
system for targeting which can provide delta-V of 25 m/s.
Targeting is accomplished using a high-precision star-tracker,
auto-navigation algorithms, and the Impactor Targeting Sensor
(ITS), a camera which provides images for autonomous control
and targeting. The ITS will operate until impact, and images
will be sent back to Earth via the flyby spacecraft. Damage to
the instrument due to dust in the coma may make imaging
impossible duing the last minute or so before impact.
Communication with the flyby spacecraft is via S-band. The
impactor is mechanically and electrically connected to the flyby
spacecraft until 24 hours prior to encounter. After separation it
runs on internal battery power.
For the Deep Impact Impactor (DII) spacecraft record, see:
http://nssdc.gsfc.nasa.gov/database/MasterCatalog?sc=2005001D
Mission Profile
Deep Impact launched on 12 January 2005 at 18:47:08.574 UT
(1:47:08 p.m. EST) on a Delta II. The spacecraft transferred
into a heliocentric orbit and will rendezvous with comet
P/Tempel 1 in July 2005. Deep Impact was 880,000 km from
the comet on 3 July 2005 moving at a velocity of 10.2 km/s
relative to the comet. The projectile was released at this point
and shortly after release the flyby spacecraft executed a
maneuver to slow down relative to the impactor by 120 m/s
and divert by 6 m/s. On 4 July the impactor struck the sunlit
side of the comet nucleus 24 hours after release, at 5:52 UT
(1:52 a.m. EDT). At 10.2 km/s velocity, the impactor had an
impact energy of about 19 gigajoules, and hit at an oblique
angle of approximately 25 degrees. Material from the nucleus
was ejected into space and the impactor and much of the
ejecta was vaporized.
The flyby spacecraft was approximately 10,000 km away at the
time of impact and began imaging 60 seconds before impact.
At 600 seconds after impact the spacecraft was about 4000 km
from the nucleus and observations of the crater began and
continued up to a range of about 700 km, about 50 seconds
before closest approach. At this point (about 961 seconds after
impact) imaging ended as the spacecraft reoriented itself by 45
degrees to optimize protection from dust damage as it flew by
the nucleus. Closest approach to the nucleus was at a
distance of about 500 km. At 1270 seconds the crossing of the
inner coma was complete and the spacecraft oriented itself to
look back at the comet and begin imaging again. At 3000
seconds the spacecraft began playback of data to Earth at 20
to 200 kilobits per second. The comet and spacecraft were
about 0.89 AU from Earth and 1.5 AU from the Sun during the
encounter. Real time return of selected impactor images and
flyby images and spectra were returned to Earth during the
encounter. Primary data return took place over the first day
after encounter, with a 28 day supplemental data return period.
Earth-based observatories also studied the impact. The
spacecraft ranged over a distance of 0.93 to 1.56 AU from the
Sun during the primary mission. End of primary mission was
August 2005. The total budget for the primary mission was
$240 million.
Deep Impact has been funded for an extended mission which
has two parts. The Deep Impact Extended Investigation (DIXI)
involves flying by comet 103P/Hartley 2 on 4 November 2010
at a closest approach of approximately 700 km. (The original
target was comet Boethin on 5 December 2008) and return
images and data. The Extrasolar Planet Observation and
Characterization (EPOCh) investigation will use the Deep
Impact imaging system to observe nearby bright stars with
known large planets to characterize the planets as they orbit
behind and in front of the stars and to search other planets in
those systems. This phase of the mission begins 26 January
2008 and continues until the end of July. The spacecraft made
an Earth flyby on 31 December 2007 to target itself for Hartley
2. It will make two more Earth flybys before the encounter with
Hartley 2. The two extended missions together are known as
EPOXI. Total cost of the extended mission is $40 million.
Comet Tempel 1
Comet 9P/Tempel 1 is a periodic comet which orbits the Sun
every 5.51 years. It has a semi-major axis of 3.12 astronomical
units (AU, the distance from the Sun to the Earth) and a
perihelion distance of 1.5 AU, which puts it between the orbits
of Mars and Jupiter. Its orbit is inclined 10.5 degrees to the
ecliptic. The orbit has changed in the past but the perihelion
has been within 10 AU for at least 300,000 years. The nucleus
is estimated to be roughly 14 km long and 4 km wide. The
perihelion occurs on 5 July 2005, the day after the encounter.
The comet was discovered on 3 April 1867 by Ernst Wilhelm
Leberecht Tempel and was first recognized to be periodic in
May of that year by C. Bruhns.
Personnel
Name
Role
E-mail
Dr. Michael F.
A'Hearn
Mission Principal
Investigator
University of Maryland
[email protected]
Dr. Tim
Larson
Project Manager
NASA Jet Propulsion
Laboratory
[email protected]
Selected References
Belton, M. J. S., and M. F. A'Hearn, Deep sub-surface exploration of cometary nuclei, Adv.
Space Res., 24, No. 9, 1167-1173, May 1999.
A'Hearn, M. F., et al., Deep Impact: A Large-Scale Active Experiment on a Cometary Nucleus,
Space Sci. Rev., 117, No. 1-2, 1-21, June 2005.
Blume, W. H., Deep Impact Mission Design, Space Sci. Rev., 117, No. 1-2, 23-42, June 2005.
A'Hearn, M. F., et al., Deep Impact: Excavating comet Tempel 1, Science, 310, No. 5746, 258264, Oct. 2005.
A'Hearn, M. F., and M. R. Combi, Deep Impact at Comet Tempel 1, Icarus, 187, No. 1, 1-3,
Mar. 2007.
Deep Impact
Nacionalidad: EEUU
· Fecha de lanzamiento: 12.01.05
· Objetivo: Encuentro e impacto de subsonda con el cometa Tempel-1
Introducción
Deep Impact es una sonda de bajo presupuesto destinada a estudiar un cometa de una forma diferente
hasta cómo se ha hecho hasta ahora. Los cometas atesoran valiosa información de los momentos iniciales
del sistema solar, son en principio cuerpos primitivos, formados en el exterior de nuestro sistema, y se
presume que han resultado menos alterados que la mayoría de objetos de nuestro sistema solar. Por ello es
una buena forma de estudiar las condiciones de su formación retrocediendo miles de millones de años en
el tiempo. Estos fósiles helados destacan al acercarse el sol, haciéndose más brillantes y a veces
desplegando una espectacular cola iónica. Se ha calculado que los cometas de más corto período no
pueden sobrevivir muchos episodios de calentamiento al acercarse al Sol si su período es breve.
Hasta ahora se han estudiado cuatro cometas en la era espacial mediante sondas robóticas, son cuerpos
muy pequeños y esquivos y la muestra de cometas estudiados puede no ser representativa de estos astros.
Por ello la misión Deep Impact va intentar estudiar un cometa desde un punto de vista diferente. Deep
Impact lanzará un proyectil que colisionará con el cometa Tempel 1 a gran velocidad, la nave nodriza
estudiará desde una distancia prudente, como se forma el cráter, su profundidad y diámetro. Asimismo
estudiará las propiedades de la eyecta y transmitirá datos para evaluar los cambios en la ritmo de
producción de gas y polvo tras el impacto.
Tempel 1 reune las características buscadas de ser un cometa muy evolucionado y de baja actividad, al
igual que encontrarse cerca del perihelio y ser fácilmente observable en lugares diferentes de la Tierra
(cercano al ecuador celeste). El cometa se encontrará cerca de la Tierra y eso permite una buena
observación desde nuestro planeta y además de un tiempo de misión bastante corto. Físicamente es un
cometa alargado con un tamaño de unos 11 x 3.2. x 3.2 kms, lo que dificultará aun mas el impacto.
Objetivos científicos
Sondas anteriores como Stardust, Deep Space 1 o Giotto, nos han aportado mucho al conocimiento de
estos cuerpos helados, pero persisten todavía dudas sobre la estructura interna de los cometas. No es raro
que un cometa se disgregue o fragmente se conocen ejemplos a lo largo de la historia esto lleva a pensar
que estos cuerpos son poco densos y compactos, y los modelos de su estructura interna son más bien los
de una pila de escombros agregados que un cuerpo sólido y cohesionado.
Los cometas pasan en muchas ocasiones alrededor del Sol sobre todo si son de corto período. La
provisión de hielos de un cometa no es inagotable y tarde o temprano se acaban sublimando y
perdiéndose en el espacio. ¿Qué queda entonces después de que un cometa se apague? Parece ser que se
transforman en un tipo de asteroides aunque esto no podemos afirmarlo con seguridad para todos los
cometas. Existen misteriosos asteroides que de vez en cuando tienen una breve actividad cometaria
pasando después a un periodo de latencia. Así mismo como en los casos de Phaeton o Icarus presentan
órbitas excéntricas más propias de los cometas que de los asteroides.
La misión Deep Impact lanzará un proyectil en su mayoría de cobre, de 370 kg que impactará a 10.2 km/s
generando una energía cinética de impacto equivalente a 4,800 kg de TNT. La colisión podría provocar
un destello de alrededor de magnitud 0 visible a simple vista desde la Tierra, provocando hasta 10,000º C
en el impacto. El impacto tendrá lugar a ser posible en el borde del cometa y aunque se espera un cráter y
el desprendimiento de eyecta no sabemos con certeza sus dimensiones y la cantidad de eyecta. Es poco
probable pero incluso podría darse el caso de una pequeña fragmentación del núcleo cometario e incluso
que el impactor atravesase el cometa y saliese por el lado contrario.
Fechas importantes en la misión
Una vez completadas las fases de ensamblaje y verificación, que comenzaron en noviembre de 1999. Está
previsto que Deep Impact parta el 12 de enero de 2005 mediante un cohete Boeing Delta 2. Existe una
ventana de lanzamiento, y dentro de ésta otra ventana en las primeras horas de la mañana, si existieran
contratiempos meteorológicos o técnicos el lanzamiento tendría que posponerse al menos 24 horas. Tras
una corta fase de crucero Deep impact impactará en Tempel 1 el 4 de julio de 2005. Unas 24 horas antes,
la nave nodriza y proyectil se separarán.
La nave madre tomará datos e imágenes hasta 4 días después del impacto. Transcurrido ese tiempo y si no
hay extensiones, la misión se dará por concluida. Como en otras misiones los datos obtenidos
presumiblemente requerirán de un análisis por parte del equipo de la misión y de otros investigadores,
durante un tiempo de al menos 9 meses.
- Lanzamiento: 12-enero-2005
- Separación del impactador: 3-julio-2005
- Impacto contra el cometa Tempel-1: 4-julio-2005
El cohete
El cohete encargado del lanzamiento es el Boeing Delta 2 Modelo 2925. Este cohete es uno de los más
económicos de los que utiliza la NASA, y es un viejo conocido pues se ha utilizado con éxito en misiones
como: Stardust, NEAR o Deep Space 1 entre otras. Su fiabilidad es muy alta.
Primera etapa: Combustible sólido. Consta de un motor principal y 9 aceleradores sólidos (boosters)
desechables.
Segunda etapa: combustible líquido con capacidad de reencendido.
Tercera etapa o superior: Combustible sólido
La Sonda
Deep Impact consta de dos partes la nave nodriza o principal y el impactador o proyectil, nos referiremos
a él también como subsonda.
- Nave Nodriza
La nave nodriza alberga al proyectil y su masa es de 650 kg excluido éste último. La nave es de estructura
de aluminio y utiliza mantas para su control térmico. Uno de los lados de la nave lleva un escudo de
protección para evitar que las partículas de polvo de la coma puedan dañar el interior de la nave, su
electrónica y su sistema de comunicaciones.
La nave está estabilizada en tres ejes y utiliza una cámara como ayuda a la navegación, aparte de la
navegación tradicional ejercida desde tierra por las antenas del DSN. El cerebro de la nave es una
computadora RAD750.
Emplea como propelente hidracina para sus correcciones de trayectoria y sobre todo para maniobrar una
vez soltado el proyectil y evitar el rumbo de colisión. Su alimentación eléctrica la obtiene de un panel
solar fotovoltaico de carácter fijo. El sistema eléctrico lo completa una batería recargable de hidruro de
niquel (NiH), en el momento de la cita el panel rinde 92 W. Durante la fase de encuentro la antena de alta
ganancia transmitirá en tiempo real las imágenes del impacto. Utiliza la Banda X para comunicarse con la
Tierra y la Banda S para comunicarse con el impactador después de la separación.
La función de la nave nodriza es observar el impacto, eyecta, otros efectos e interior del cráter. La nave
principal tomará rumbo de colisión soltará el proyectil y seguidamente se apartará del rumbo de colisión
del cometa disminuyendo su velocidad. Se pretende que pase a unos 500 km del núcleo del Tempel 1.
Instrumentos científicos
- Cámara de Alta Resolución (High Resolution Instrument)
- Cámara de Media Resolución (Medium Resolution Instrument)
Estos dos instrumentos recogen imágenes de campo medio y estrecho, pudiéndose utilizar una como
instrumento redundante del otro en caso de fallo. Su misión es obtener imágenes y espectros del cometa
durante el pre-impacto, impacto y post-impacto
- La cámara ITS (Impactor Targeting Sensor): viaja abordo de la subsonda de impacto es esencialmente
igual a la MRI de la nave nodriza.
El impactador
Se separa de la nave nodriza 24 horas antes de que impacte en la superficie de núcleo del cometa Tempel
1. La energía de cinética de impacto equivale a 4800 kg TNT. Esta energía es fruto de la masa del
impactador (370 kg) y de la velocidad de impacto (aprox. 10.2 km/seg).
Resulta un desafío para esta misión que la sonda de impacto que viaja a 10 km/s pueda colisionar con el
cometa que apenas mide 6 km de diámetro, partiendo desde una distancia de 864,000 km. Para conseguir
el impacto la subsonda lleva un rastreador estelar (Star-Tracker) de alta precisión llamado Impactor
Target Sensor (ITS) desarrollado por el JPL para una misión anterior, el demostrador tecnológico Deep
Space 1. ITS dispone de algoritmos de autonavegación para llevarle hasta su objetivo. El impactador
posee una pequeña provisión de hidracina así como un pequeño sistema propulsor para realizar pequeñas
correcciones de trayectoria si fueran necesarias. La subsonda de impacto viaja acoplada a la nave nodriza,
y dispone de una batería interna para las 24 horas de su misión.
Two Discovery program missions of opportunity involving extended missions for the Deep Impact
spacecraft have been selected - a mission to another comet and use of its camera for extrasolar
planet studies. For more information, see the NASA press release.
Images of the Deep Impact encounter with Comet Tempel 1 - 4 July 2005
Call for CCD Observations of Comet Tempel 1
Comet Page
Comet Fact Sheet
NASA's Discovery Program
Deep Impact Press Releases
NASA sends spacecraft on mission to Comet Hartley 2 - 13 December 2007
New extended missions chosen for Deep Impact - 3 July 2007
Deep Impact extended missions chosen for further study - 30 October 2006
NASA's Deep Impact tells a tale of the comet - 4 July 2005
Deep Impact kicks off Fourth of July with deep space fireworks - 4 July 2005
NASA announces spectacular day of the comet - 9 June 2005
NASA's Deep Impact spacecraft spots its quarry, stalking begins - 27 April 2005
NASA releases Deep Impact mission status report - 25 March 2005
Deep Impact launched and flying toward date with a comet - 12 January 2005
Deep Impact arrives in Florida to prepare for launch - 18 October 2004
Deep Impact launch date changed - 01 April 2003
University of Maryland Press Release on Deep Impact - 07 July 1999
EPOXI Project Home Page
Deep Impact Project Home Page
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DirecTV 8
Publications
NSSDC ID: 2005-019A
Maps
New/Updated Data
Alternate Names
Description
DirecTV 8 is an American geostationary communications
satellite that was launched by a Proton-M rocket from Baikonur
at 17:59 UT on 22 May 2005. The satellite carries 32 Ku-band
and four Ka-band transponders to provide high definition TV
after parking over 93 deg-W longitude.
28659
Facts in Brief
Launch
Vehicle: Proton-M
Kazakhstan
Mass: 3700.0 kg
Funding Agency
Discipline
Communications
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Express AM2
Publications
NSSDC ID: 2005-010A
Maps
New/Updated Data
Alternate Names
Description
Express AM-2 is a Russian geostationary communications
spacecraft that was launched by a Proton-K rocket from
Baikonur at 22:31 UT on 29 March 2004. The 2.6 tonne
satellite carries 16 C-band, 12 Ku-band and one L-band
transponders to provide digital broadcasting, telephony and
video-conferencing and broadband internet access to all
countries either side of the Himalayan range, after parking
over 80 deg-E longitude.
28629
Facts in Brief
Launch
Vehicle: Proton-K
Russia
Mass: 580.0 kg
Nominal
Power: 6000.0 W
Funding Agency
Russian Satellite
Communications
Company (Russia)
Discipline
Communications
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AM2
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Express AM3
Publications
NSSDC ID: 2005-023A
Maps
New/Updated Data
Alternate Names
Description
Express-AM3 is a Russian geostationary communications
satellite that was launched by a Proton-K rocket from Baikonur
at 20:41 UT on 24 June 2005. The 2.5 tonne satellite carries
16 C-band, 12 Ku-band, and a single L-band transponders to
provide video and radio transmissions to all of Russia after
parking over 140 deg-E longitude. The EXPRESS-AM fleet is
replacing the aging fleets of GORIZONT and EKRON-M.
28707
Facts in Brief
Launch
Vehicle: Proton-K
Kazakhstan
Mass: 580.0 kg
Nominal
Power: 6000.0 W
Funding Agency
Russian Satellite
Communications
Company (Russia)
Discipline
Communications
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AM3
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Foton M-2
Publications
NSSDC ID: 2005-020A
Maps
New/Updated Data
Alternate Names
Description
Foton M-2 is a Russian retrievable craft that was launched by a
Soyuz-U rocket from Baikonur at 12:00 UT on 31 May 2005.
The 6.3 tonne craft carries three modules: a spherical
retrievable unit that houses many microgravity experiments, a
battery pack and a service module. The retrievable module
carries several units totaling 550 kg to conduct 39 ESA-built
experiments. Among them are experiments in physical
sciences, biology, fluid mechanics, exobiology, material
science, and technology demonstration. After orbiting for 16
days, the module will be parachuted to land in Russia on 16
June 2005 at 08:32 UT.
28686
Facts in Brief
Launch
Vehicle: Soyuz-U
Kazakhstan
Mass: 6300.0 kg
Funding Agency
Russian Space Agency
(Russia)
Disciplines
Life Science
Microgravity
Technology Applications
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FSW 21
Publications
NSSDC ID: 2005-027A
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Description
FSW 21, also known as FSW-3 4, is a Chinese (PRC)
recoverable satellite that was launched by a Long March 2C
rocket from Jiuquan Launch Center in northwest China at
07:30 UT on 02 August 2005. It will conduct "scientific
research, land surveying and mapping".
FSW-3 4
28776
Facts in Brief
March 2C
Launch Site: Jiuquan,
Funding Agency
Unknown (Peoples
Republic of China)
Discipline
Earth Science
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FSW 22
Publications
NSSDC ID: 2005-033A
Maps
New/Updated Data
Alternate Names
Description
FSW 22, also known as FSW-3 5, is a Chinese (PRC)
recoverable satellite that was launched by a Long March 2-4
from Jiuquan Launch Center in northwestern China on 29
August 2005. It will carry out scientific research, land
surveying, mapping and space-technological tests.
FSW-3 5
28824
Facts in Brief
Launch Vehicle: null
Funding Agency
Unknown (Peoples
Republic of China)
Disciplines
Engineering
Earth Science
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Galaxy 14
Publications
NSSDC ID: 2005-030A
Maps
New/Updated Data
Alternate Names
Description
Galaxy 14 is an American geostationary communications
satellite that was launched by a Soyuz-FG rocket from
Baikonur at 23:28 UT on 13 August 2005. The 2,100 kg
satellite carries 22 C-band transponders to provide
entertainment and information services to cable channels and
direct-to-home receivers in North and South America, after
parking over 125° W longitude.
28790
Facts in Brief
Launch Vehicle: Soyuz
FG
Kazakhstan
Mass: 2100.0 kg
Funding Agency
Discipline
Communications
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information for Galaxy 14
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Galaxy 14
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Galaxy 15
Publications
NSSDC ID: 2005-041A
Maps
New/Updated Data
Alternate Names
Description
Galaxy 15 is an American geostationary communications
satellite that was launched by an Ariane 5 rocket from Kourou
at 22:32 UT on 13 October 2005. The 1,892 kg (with
propellant) satellite carries 24 C-band transponders, and a few
in L-band to provide direct-to-home video entertainment and
information after parking, probably, at 72 degrees-W longitude.
It will also relay GPS transmissions to aircraft to facilitate their
landing.
28884
Facts in Brief
Launch Vehicle: Ariane
5GS
Launch Site: Kourou,
French Guiana
Mass: 885.0 kg
Nominal
Power: 4700.0 W
Funding Agency
Pan American Satellite
(United States)
Discipline
Communications
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GIOVE-A
Publications
NSSDC ID: 2005-051A
Maps
New/Updated Data
Alternate Names
Description
GIOVE-A (Galileo In-Orbit Validation Element) is a an
European (ESA) navigational satellite. The 600 kg satellite was
launched by a Soyuz-Fregat rocket from Baikonur at 05:19 UT
on 28 December 2005. It is the first member of a planned fleet
of 30 Galileo satellites to operate independent of the American
GPS and the Russian GLONASS fleets, though quite
compatible with either. (The ESA fleet may involve
technical/financial participation by India and China. Unlike the
GPS and GLONASS, which are under military control, the
Galileo fleet will be wholly civilian-controlled, with global
access guaranteed to the public ("except in direst
emergencies") and providing a one-meter resolution,
comparable to the resolution of the other fleets that is available
for their militaries. The full Galileo fleet will be completed by
2010. (ESA expects that the profits from the accesses through
2020 will total to about five-fold of the investment.)
Galileo In-Orbit Validation
Element
28922
Facts in Brief
Launch
Vehicle: Soyuz-Fregat
Kazakhstan
Funding Agency
European Space Agency
(International)
Discipline
Navigation & Global
Positioning
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Gonets-D1M 1
Publications
NSSDC ID: 2005-048A
Maps
New/Updated Data
Alternate Names
Description
Gonets-D1M 1 is a Russian low-altitude communications
satellite that was launched by a Kosmos-3M rocket from
Plesetsk at 18:34 UT on 21 December 2005. It is the first of a
fleet of 12 satellites in four planes. The 250 kg, 40 W craft is
expected to serve some 30 Russian agencies and
organizations with email and short messages. An earlier fleet
of six Gonets-D1 satellites had served that role in the 1990s.
28908
Facts in Brief
Launch
Vehicle: Kosmos-3M
Russia
Funding Agency
Unknown (Russia)
Discipline
Communications
Additional
Information
Launch/Orbital
information for GonetsD1M 1
Experiments on GonetsD1M 1
Gonets-D1M 1
Office.
NSSDC Master
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Hamsat
Publications
NSSDC ID: 2005-017B
Maps
New/Updated Data
Alternate Names
Description
HAMSAT is an Indian (ISRO) microsatellite that was launched
by PSLV-C6 rocket from Sriharikota on the southeastern coast
of India at 04:44 UT on 5 May 2005. The 43 kg satellite will
relay amateur VHF radio communications.
VUSat
OSCAR 52
28650
Facts in Brief
Launch Vehicle: PSLV
Launch Site: Sriharikota,
India
Mass: 42.5 kg
Funding Agency
Indian Space Research
Organization (India)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Hamsat
Experiments on Hamsat
Hamsat
Office.
NSSDC Master
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Spacecraft
Experiments
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Inmarsat 4-F1
Publications
NSSDC ID: 2005-009A
Maps
New/Updated Data
Alternate Names
Description
Inmarsat 4-F1 is a geostationary communications satellite of
the international INMARSAT consortium, that was launched by
an Atlas 5 rocket from Cape Canaveral at 21:42 UT on 11
March 2005. The 5.95 tonne satellite will provide direct-tohome, high-speed digital communications to much of Europe,
Asia and Africa via 200 spot beams in C- and L-bands after
parking over 64 deg-E longitude.
28628
Facts in Brief
V
Launch Site: Cape
Funding Agency
Inmarsat (International)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Inmarsat
4-F1
Experiments on Inmarsat
4-F1
Inmarsat 4-F1
Office.
NSSDC Master
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Inmarsat 4-F2
Publications
NSSDC ID: 2005-044A
Maps
New/Updated Data
Alternate Names
Description
Inmarsat 4-F2 is a geostationary communications satellite of
the London/UK-headquartered INMARSAT network that is
closely linked with the international GMDSS (Global Maritime
Distress and Safety System). It was launched by an UkrainianRussian Zenit 3SL rocket from the floating platform in the
equatorial Pacific Ocean, Odyssey located at 154 deg-W
longitude, at 14:07 UT on 8 November 2005. The six tonne, 13
kW satellite will provide video, data, video- conferencing and
Internet services to North and South America as well as to
Pacific and Atlantic ocean based receivers, through 200 spotbeams after parking over 53 deg-W longitude.
28899
Facts in Brief
Launch Vehicle: Zenit
3SL
Launch Site: Odyssey
(Sea Launch Platform), null
Funding Agency
Inmarsat (International)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Inmarsat
4-F2
Experiments on Inmarsat
4-F2
Inmarsat 4-F2
Office.
NSSDC Master
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Insat 4A
Publications
NSSDC ID: 2005-049A
Maps
New/Updated Data
Alternate Names
Description
INSAT 4A is an Indian geostationary communications satellite
that was launched by an Ariane 5G rocket from Kourou at
22:33 UT on 21 December 2005. The 3.1 tonne, 5.5 kW
satellite carries 12 140 W Ku-band transponders and 12 63 W
C-band transponders to provide Direct-to Home (DTH) data
and TV services to India and neighboring countries, after
parking over 83°E longitude.
28911
Facts in Brief
5GS
French Guiana
Mass: 1335.0 kg
Funding Agency
Unknown (India)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Insat 4A
Experiments on Insat 4A
Data collections from Insat
4A
Office.
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Intelsat Americas 8
Publications
NSSDC ID: 2005-022A
Maps
New/Updated Data
Description
Intelsat Americas 8 (also known as IA 8) is an American
(Bermuda registered) geostationary satellite that was launched
by a Zenit 3SL rocket from Odyssey, the platform floating on
the equatorial Pacific Ocean at 154 deg-W longitude, at 15:03
UT on 23 June 2005. The 5.5 tonne, 16 kW satellite carries 28
C-, 36 Ku-, and 24 Ka-band transponders to provide video and
data transmissions to all countries in North and South
Americas, after parking over 89 deg-W longitude. It will be the
28th satellite in the INTELSAT fleet.
Alternate Names
IA 8
Galaxy 28
G-28
28702
Facts in Brief
3SL
Funding Agencies
International
Telecommunications
Satellite Corporation
(International)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Intelsat
Americas 8
Experiments on Intelsat
Americas 8
Intelsat Americas 8
Office.
NSSDC Master
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Spacecraft
Experiments
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Maqsat
Publications
NSSDC ID: 2005-005B
Maps
New/Updated Data
Alternate Names
Description
Maqsat is a European (ESA) monitor that remained attached
to the Ariane 5-ECA rocket that was launched from Kourou at
21:03 UT on 12 February 2005. It will monitor the dynamic
behavior of the rocket from launch through the release of the
two satellites, XTAR-EUR and SLOSHSAT.
28543
Facts in Brief
5 ECA
French Guiana
Funding Agency
(International)
Discipline
Engineering
Additional
Information
Launch/Orbital
information for Maqsat
Experiments on Maqsat
Maqsat
Office.
NSSDC Master
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Spacecraft
Experiments
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Publications
NSSDC ID: 2005-029A
Maps
New/Updated Data
Mars Reconnaissance
Orbiter
Description
The Mars Reconnaissance Orbiter (MRO) is designed to orbit
Mars over a full martian year and gather data with six scientific
instruments, including a high-resolution imager. The science
objectives of the mission are to: characterize the present
climate of Mars and its physical mechanisms of seasonal and
interannual climate change; determine the nature of complex
layered terrain on Mars and identify water-related landforms;
search for sites showing evidence of aqueous and/or
hydrothermal activity; identify and characterize sites with the
highest potential for landed science and sample return by
future Mars missions; and return scientific data from Mars
landed craft during a relay phase. MRO will return high
resolution images, study surface composition, search for
subsurface water, trace dust and water in the atmosphere, and
monitor weather.
The Mars Reconnaissance Orbiter consists of a main bus,
constructed of titanium, carbon composites, and aluminum
honeycomb. Extending from the bus are two solar panel wings
and a 3 meter high-gain antenna dish. The bus houses the
propulsion system, telecommunications, command, guidance,
and science instruments. The maximum spacecraft mass is
2180 kg, which includes 1149 kg of propellants.
Propulsion is provided by a total of 20 thrusters. Six 170 N
(Newton) monopropellant (hydrazine) main-engine thrusters
are used for the Mars Orbit insertion burn, a maneuver which
will require about 70% of the total fuel onboard. Six 22 N
thrusters are used for trajectory correction maneuvers and
eight 0.9 N thrusters for pointing. All thrusters are fed from a
single propellant tank mounted near the center of the main
bus. A pressurant tank is used to force propellant to the
motors. Spacecraft control is achieved with the use of reaction
wheels and reaction control system thrusters. Navigation and
attitude knowledge is determined by 16 sun sensors, two star
tracker cameras, and two inertial measurement units, which
use accelerometers and gyroscopes.
Two way telecommunications will be via X-band at about 8000
MHz, primarily through a 3 m diameter steerable high-gain dish
antenna. Two low-gain Ka-band antennas, mounted on the
high-gain dish, are also available for transmission and
reception. Two transponders and three traveling wave tube
amplifiers allow maximum data rates of 6 megabits/sec. Power
is provided by the two solar cell arrays on wings mounted on
opposite side of the bus. Each array has an area of 10 square
meters and contains 3744 solar cells. The panels produce
1000 Watts at Mars which is used to run the equipment directly
Alternate Names
MRO
Facts in Brief
V 401
Launch Site: Cape
Mass: 1031.0 kg
Nominal
Power: 1000.0 W
Funding Agency
(United States)
Discipline
Planetary Science
Additional
Information
Launch/Orbital
information for Mars
Reconnaissance Orbiter
Mars Reconnaissance
Orbiter
Telecommunications
information for Mars
Experiments on Mars
Data collections from Mars
and also to charge two nickel-hydrogen 50 A-hr, 32-volt
batteries. Thermal control is achieved by a combination of
radiators, surface coatings, insulation, and heaters.
Williams.
MRO's science payload includes the High Resolution Imaging
Science Experiment (HiRISE), a visible stereo imaging camera;
the Compact Reconnaissance Imaging Spectrometer for Mars
(CRISM), a visible/near-infrared spectrometer to study the
surface composition; the Mars Climate Sounder (MCS), an
infrared radiometer to study the atmosphere, a shallow
subsurface sounding radar (SHARAD) provided by the Italian
Space Agency to search for underground water; the Context
Camera (CTX), to provide wide-area views; and the Mars
Color Imager (MARCI), to monitor clouds and dust storms. In
addition, there are three engineering instruments aboard MRO:
the Electra UHF communications and navigation package,
which will be used as a relay between the Earth and future
Mars missions; the optical navigation camera, which will be
tested for possible navigational use on future planetary
spacecraft; and the Ka-band telecommunications experiment
package, which will be testing high performance Ka-band
communications. Engineering accelerometer data will be used
to study the structure of the martian atmosphere and tracking
of the orbiter will be used to study the gravity field of Mars.
Mission Profile
Launch on an Atlas V-401 took place at 11:43 UT (7:43 a.m.
EDT) on 12 August 2005 from Kennedy Space Center. The
cruise to Mars took seven months and included checkouts,
calibrations, navigation, and five trajectory correction
maneuvers. On 10 March 2006 MRO reached Mars and
perform a Mars orbit insertion maneuver, passing under the
southern hemisphere of Mars and firing its main engines for
about 27 minutes. Signals that the burn has started reached
Earth at 21:24 UT (4:24 p.m. EST) on 10 March. With 6
minutes left in the burn MRO passed behind Mars as seen
from Earth. Radio communication resumed when it re-emerged
about 30 minutes later.
Mars Reconnaissance Orbiter reached Mars and went into
orbit on 10 March 2006. The signal that the orbit insertion burn
started reached Earth at 21:24 UT (4:24 p.m. EST). The first
signals following its reappearance reached Earth at about
22:16 UT (5:16 EST). The 1641 second burn slowed the
spacecraft by about one km/sec, leaving it in a 400 x 35000 km
polar capture orbit with a 35 hour period. Aerobraking was
used over the next six months to lower the orbit to the 255 x
320 km science orbit (with periapsis over the south pole and
apoapsis over the north pole). There will be twelve sunsynchronous orbits per day so that the orbiter will always see
the ground at 3:00 p.m. local time at the equator. Science
operations take place nominally from the end of solar
conjunction in November 2006 to the start of the next solar
conjunction in November 2008, roughly one martian year. Total
cost of the mission is estimated at about $720 million.
Personnel
Name
Role
E-mail
Dr. Richard W.
Zurek
Project
Scientist
NASA Jet Propulsion
Laboratory
[email protected]
Mr. James E.
Graf
Project
Manager
NASA Jet Propulsion
Laboratory
[email protected]
Dr. R. Stephen
Saunders
Program
Scientist
NASA Headquarters
[email protected]
Selected References
Graf, J. E., et al., The Mars Reconnaissance Orbiter Mission, Acta Astronaut., 57, No. 2-8, 566578, 2005.
Zurek, R. W., and S. E. Smrekar, An overview of the Mars Reconnaissance Orbiter (MRO)
science mission, J. Geophys. Res., 112, E05S01, doi:10.1029/2006JE002701, 2007.
The first image of Mars taken by the HiRISE Camera on MRO.
The image was taken from an altitude of 2489 km on 24 March 2006.
Spacecraft set to reach
NASA press release on
milestone, reports technical glitches - 7 February 2007
MRO reaching Mars - 10 March 2006
launch of MRO - 12 August 2005
upcoming August launch of MRO - 21 July 2005
selection of MRO instruments - 11 November 2001
Mars Reconnaissance Orbiter Home Page - NASA JPL
2001 Mars Odyssey
Mars Global Surveyor
Mars Home Page
Mars Fact Sheet
· Nacionalidad: EEUU
· Fecha de lanzamiento: 12.08.05
· Objetivo: Orbitador de Marte
INTRODUCCION
Esta sonda orbitadora tiene como principal objetivo la búsqueda de evidencias de la persistencia del agua
en la superficie de Marte durante largos periodos de tiempo y nos permitirá conocer la historia de su
evolución. Tras siete meses de viaje y seis meses de aerofrenado, la nave buscará pistas sobre el agua
desde su órbita científica obteniendo fotografías de altísima resolución de la superficie, analizando los
minerales, buscando agua bajo el subsuelo y examinando la atmósfera en busca del polvo y el agua que se
encuentren presentes. Además realizará mapas diarios del clima marciano.
Lanzamiento de MRO
La nave permitirá conocer si se han formado depósitos minerales por la acción del agua, detectará la
existencia de posibles líneas de costa de antiguos mares y lagos y analizará los minerales encontrados.
Además nos dirá si el hielo subterráneo encontrado por la sonda Odyssey se encuentra sólo en la capa
superior del suelo o si bien es la capa más alta de grandes depósitos subterráneos.
Las cámaras de la sonda son las mayores jamás enviadas a Marte y podrán identificar pequeños objetos en
la superficie menores que el tamaño de una mesa, lo que servirá para comprender las estructuras presentes
en la superficie y para decidir las zonas de aterrizaje para futuros aterrizadores y rovers por todo el
planeta. El espectrómetro permitirá conocer en pequeña escala la composición del terreno y sus
características. Además servirá como una poderosa herramienta para las comunicaciones y la navegación
de las próximas misiones a Marte.
FECHAS PRINCIPALES
· Lanzamiento: 12 Agosto 2005
· Llegada a Marte y Maniobra de Inserción Orbital: 10 Marzo 2006
· Comienzo del Aerofrenado: mediados Marzo 2006
· Comienzo de la misión científica: Noviembre 2006
· Fin de la misión primaria: Diciembre 2010
Su misión primaria finaliza el 31 de diciembre del año 2010 pero si se encuentra en buen estado en esas
fechas podría ampliarse cinco años más.
LA NAVE
MRO usa un nuevo diseño producido por Lockheed Martin Space Systems que supera a cualquier misión
lanzada con anterioridad. Es la primera sonda diseñada específicamente para el aerofrenado lo que
permitirá realizar esta fase de una forma mucho más efectiva. Su peso total ronda los 2.180 kilogramos de
los cuales 1.149 kilogramos corresponden al combustible y el peso seco (la nave en sí y sus instrumentos)
es de 1.031 kilogramos.
La sonda orbitando Marte
Para las comunicaciones la sonda utilizará una enorme antena parabólica de alta ganancia de 3 metros de
diámetro lo que permitirá el envío de datos a alta velocidad. Además porta dos antenas de baja ganancia
situadas en las dos caras de la antena principal y servirán para la comunicaciones a un menor ritmo,
situaciones de emergencia y la maniobra de inserción orbital ya que permiten el envío de datos en
cualquier orientación de la nave.
La única fuente de energía para la sonda es el Sol y en sus laterales opuestos la nave porta dos paneles
solares con un total de 40 metros cuadrados de superficie y 3.744 células individuales con un rendimiento
del 26%, muy superior a los paneles de otras misiones. La nave funciona a 32 Voltios y sus paneles
proporcionan hasta 1000 Vatios de potencia. Durante el aerofrenado los paneles tendrán un papel
principal al frenar la sonda por rozamiento con la atmósfera y se han preparado para que resistan
temperaturas de hasta 200º Centígrados.
Configuración durante la fase científica
INSTRUMENTOS
La nave lleva seis instrumentos científicos, tres instrumentos de ingeniería y dos experimentos de ciencia.
· Instrumentos científicos: Los instrumentos realizaran ocho investigaciones diferentes en Marte con tres
propósitos: mapas globales, estudios regionales y objetivos a alta resolución en la superficie.
- Cámara HiRISE (High Resolution Imaging Science Experiment): Esta cámara en luz visible fotografiará
la superficie con gran detalle mostrando pequeños objetos en la superficie y detalles geológicos en
cañones, cráteres y estratos.
Funciona usando unas lentes telescópicas que permitirán la mayor resolución jamás obtenida en Marte,
llegando a poder ver objetos del tamaño de 1 metro. Además realizará observaciones en infrarrojo para
obtener detalles de la composición mineral de la zona seleccionada. Con una altura de observación que
variará entre los 200 y los 400 kilómetros, la cámara llegará a una resolución de entre 30 y 60 centímetros
por píxel. Para seleccionar las zonas a observar se investigarán las fotografías de MGS y Odyssey,
seleccionando las regiones de mayor interés.
La nave obtendrá sus fotografías a color mezclando imágenes en tres colores: verde, rojo e infrarrojo
cercano para mostrar imágenes con un color real. Las imágenes tendrán un impresionante tamaño de
20.000 por 35.000 píxeles, con un total de 700 megapíxeles por fotografía.
- Cámara CTX (Context Camera): dará vistas de amplias áreas para ayudar en la puesta en contexto de las
imágenes de alta resolución HiRISE y CRISM. Aunque la resolución no será excesivamente grande, dará
imágenes de áreas mayores lo que permitirá estudiar las rocas y minerales con los otros instrumentos.
Desde 400 kilómetros de altura la cámara dará una resolución de 8 metros por píxel, mostrando el terreno
con una anchura de 40 kilómetros.
- Cámara MARCI (Mars Color Imagen): es una cámara meteorológica que buscará nubes y tormentas a
nivel global, observando en 5 bandas de luz visible, así como en dos bandas ultravioletas para detectar
variaciones en el ozono y dióxido de carbono en escalas de decenas de kilómetros.
La cámara HiRISE de alta resolución
- Espectrómetro CRISM (Compact Reconnaissance Imaging Spectrometer for Mars): este instrumento
observará en luz visible y en el infrarrojo cercano para obtener cientos de ‘colores’ que identificarán los
minerales, especialmente aquellos formados en presencia de agua, en superficies de un tamaño inferior a
un campo de fútbol. En particular inspeccionará regiones que hayan podido tener fuentes termales y lagos
en la historia marciana. Desde una altura de 300 kilómetros tendrá una resolución de 18 metros.
- Radiómetro MCS (Mars Climate Sounder): Este instrumento sondeará la atmósfera para detectar las
variaciones verticales en la temperatura, el polvo y las concentraciones de vapor de agua.
- Radar SHARAD (Shallow Radar): Este radar de sondeo proporcionado por la Agencia Espacial Italiana
(ASI) penetrará en la superficie marciana para ver si existe en la actualidad agua helada a profundidades
mayores de un metro. La nave enviará a través de su antena señal de radar en las frecuencias entre los 15
y los 25 MHz para conseguir penetrar en el suelo hasta al menos 1 kilómetro de profundidad. La antena
captará las señales rebotadas en el suelo y medirá los cambios en las características de la onda para
conocer los elementos presentes bajo la superficie. Tiene un resolución horizontal que variará entre los
0,3 y los 3 kilómetros y una resolución vertical de 15 metros.
El radar SHARAD en funcionamiento
· Instrumentos de ingeniería: Portará 3 instrumentos que ayudarán a asistir a la sonda en navegación y
comunicaciones.
- Electra UHF Communications and Navigation Package. Permite a MRO actuar como un repetidor de
comunicaciones de alta velocidad entre la Tierra y las sondas de la superficie que no tienen suficiente
potencia para una comunicación directa.
- Optical Navigation Camera: Servirá para mejorar la navegación de las futuras misiones y servirán como
‘ojos’ de alta precisión para guiar a las sondas que se acerquen. La cámara de MRO no es más grande que
una cámara normal y posee unas lentes para proporcionar los aumentos. Tiene un peso de 2,8 kilogramos
y tiene 30 centímetros de largo, con una apertura de 60 milímetros de diámetro. Durante la aproximación
a Marte y comenzando 30 días antes de la llegada, la cámara obtendrá unas 500 fotografías y la mayoría
de ellas serán obtenidas durante los 8 últimos días para mejorar la precisión (superior a 1 kilómetros) en
la navegación y la inserción orbital. Las imágenes se obtendrán fundamentalmente de las lunas de Marte
para comparar las fotografías con las posiciones previstas por ordenador, lo que permitirá conocer la
situación exacta en el espacio.
- Experimento de Telecomunicaciones en Banda-Ka. MRO usará la frecuencia de radio en Banda-Ka para
aumentar enormemente la capacidad de envío de datos hacia la tierra usando menos energía.
La sonda MRO servirá como repetidor para otras misiones
· Experimentos de ciencia:
- Investigación del campo gravitatorio: siguiendo la órbita en la fase primaria, los científicos serán
capaces de realizar mapas de gravedad del planeta que servirán para comprender la geología de la
superficie y el interior marciano, así como los procesos geofísicos que crearon las estructuras visibles, así
como conocer la redistribución de masa en el planeta durante la formación y disipación de los Polos.
- Acelerómetros de investigación de la estructura atmosférica: Durante el aerofrenado los acelerómetros
medirán los cambios de velocidad en la sonda lo que ayudará a entender la estructura de capas de la
atmósfera marciana.
SERVICIOS DE TELECOMUNICACIONES
La fase de repetidor comienza al finalizar la fase científica y tiene una duración de al menos dos años,
finalizando el 31 de diciembre de 2010, aunque MRO llevará bastante combustible como para funcionar
hasta finales del año 2015.
La sonda proporcionará apoyo a todas las misiones que se encuentren operativas en Marte y dará
información sobre navegación y transmisión de comunicaciones a las que se acerquen. Su órbita le
permite acceder a cualquier lugar del planeta, de tal manera que cualquier sonda en la superficie tenga al
menos una o dos oportunidades de contacto diarias.
Para esta función se ha dotado a la nave del instrumento Electra que proporcionará cobertura en UHF a
los landers y rovers con la antena que apuntará al nadir (hacia la superficie marciana).
La sonda vista de frente con su enorme antena
La sonda dará tres tipos de servicios:
· Navegación: ayudará a las sondas en la aproximación a Marte dando datos de navegación y ayudará a
localizar de forma precisa los aterrizadores y rovers de la superficie. Cuando las sondas estén a un mes de
su llegada al planeta rojo, MRO apuntará su antena hacia la nave que llega y se comunicará con ella
enviándole las señales de la DSN. Si la sonda que se aproxima posee el sistema de comunicación Electra,
recibirá las señales y determinará la distancia y la velocidad relativa respecto a Marte, de forma que la
navegación es mucho más precisa. Cuando las naves hayan aterrizado en Marte, el sistema Electra
determinará con precisión los datos Doppler que al ser combinados con la posición de MRO nos dará la
situación exacta de la sonda aterrizada.
· Repetidor de datos: los datos serán enviados hacia el aterrizador a través de la MRO y más tarde el
aterrizador enviará sus datos a MRO para que los envíe a la Tierra. En la practica será como dotar a las
sondas aterrizadas en Marte de un servicio de internet de alta velocidad que será usado durante al menos 5
minutos dos veces al día, lo que les dará más oportunidades de comunicación, aparte de las que tengan
por sus propios medios. Algunos aterrizadores incluso no llevarán sistemas de comunicación con la Tierra
para ahorrar peso y energía, por lo que usarán a MRO como su comunicador.
· Servicios horarios: darán señales horarias a los aterrizadores y a los rovers para que sepan que hora es
exactamente en cada momento.
Comparación de su tamaño (antena, paneles, cámara) con los orbitadores previos
FRECUENCIAS DE RADIO
La sonda MRO puede comunicarse con las antenas de la DSN usando dos frecuencias de radio diferentes:
· Banda-X: es la banda usada para las comunicaciones en la actualidad, que al ser amplificada permite al
orbitador enviar a la Tierra datos a una velocidad 10 veces superior a las misiones anteriores.
· Banda-Ka: Es una frecuencia no probada con anterioridad que es 4 veces mayor que la Banda-X, lo que
permitiría un envío más rápido aun de los datos. Será usada como parte de una demostración tecnológica
de comunicaciones de tal forma que las futuras sondas podrían usar como standard esta banda del
espectro que tiene una frecuencia 4 veces mayor que la banda-X (32 Gigahercios en comparación con los
8 gigahercios de la Banda-X). lo que permitirá velocidades aun mayores. Las antenas DSN capaces de
usar esta banda enviarán y recibirán datos dos veces a la semana como parte del experimento.
Desde el punto de vista de una antena DSN en la Tierra, el orbitador pasa un tercio de su tiempo en cada
órbita oculto tras el planeta. En esos momentos el orbitador está ‘ocultado desde la Tierra”. En esas
ocultaciones, MRO no puede enviar ni recibir señales de radio. Por eso, de las 16 horas de seguimiento
diario por parte de la DSN, el orbitador MRO podrá enviar datos a la Tierra durante 10 u 11 horas,
durante al menos 700 días. El ritmo de estas retransmisiones será de unos 0,5 hasta los 4 megabits por
segundo, por lo que el volumen estimado de datos recibidos rondará los 34 terabits, el equivalente a unos
4 terabytes o unos 6.500 CDs. Estos datos suman una cantidad 20 veces superior a los datos enviados por
todas las misiones planetarias previas juntas.
Comparación de los datos devueltos por cada misión
La Banda-X será la principal forma de comunicación entre MRO y las antenas de 34 metros de diámetro
de la DSN en Madrid, California y Australia. Para comunicarse el orbitador utilizará su antena de 3
metros de alta ganancia y un amplificador de 100 W para transmitir las señales, lo que da una potencia el
doble de las usadas en las misiones anteriores, lo que significará un envío de datos 10 veces más rápido
que otros orbitadores.
A la máxima distancia de la Tierra (400 millones de kilómetros), el orbitador mandará datos a un ritmo de
unos 500 kilobits por segundo. Conforme Marte se acerque a la Tierra, la señal será más fuerte y por tanto
se podrán enviar más datos. Durante algunos meses de mayor cercanía (unos 100 millones de kilómetros),
se podrán mandar datos a 4 megabits por cada segundo, a una velocidad que compite con el cable-modem
y la banda ancha de Internet. Dos antenas de la DSN seguirán el orbitador durante al menos ocho horas
cada día y ocasionalmente se usará alguna antena de 70 metros.
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Monitor-E
Publications
NSSDC ID: 2005-032A
Maps
New/Updated Data
Alternate Names
Description
Monitor-E is a Russian remote-sensing satellite that was
launched by a Rockot booster from Plesetsk at 18:34 UT on 26
August 2005. The 825 kg satellite has instruments to image
Earth's surface at a resolution of eight meters in color as well
as in black-and-white, providing input for agricultural
estimates, pollution levels, and disaster management.
28822
Facts in Brief
Launch Vehicle: Rokot
Russia
Mass: 825.0 kg
Funding Agency
Unknown (Russia)
Discipline
Earth Science
Additional
Information
Launch/Orbital
information for Monitor-E
Experiments on Monitor-E
Monitor-E
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Moz 5/Safir/Rubin 5
Publications
NSSDC ID: 2005-043G
Maps
New/Updated Data
Alternate Names
Description
Moz 5/Safir/Rubin 5 are three of the microsatellites that did not
separate from the Cosmos 3M rocket that was launched from
Plesetsk at 06:52 UT on 27 October 2005. The full name for
the Russian MOZ 5 is MOZHAYETS 5, developed by the
cadets in Mozhaisky Military Space Academy. But RUBIN 5
was in fact intended to remain attached to the rocket, to
monitor its dynamical performance.
Mozhayets 5
28898
Facts in Brief
Launch
Vehicle: Cosmos
Russia
Funding Agency
Unknown (Russia)
Discipline
Engineering
Additional
Information
Launch/Orbital
information for Moz
5/Safir/Rubin 5
Experiments on Moz
5/Safir/Rubin 5
Data collections from Moz
5/Safir/Rubin 5
Office.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2005-043G[18/10/2010 0:12:50]
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MSG 2
Publications
NSSDC ID: 2005-049B
Maps
New/Updated Data
Alternate Names
Description
MSG 2 (Meteosat Second Generation 2) is a European (ESA)
geostationary weather satellite, with operational control by the
EUMETSAT organization. It was launched by an Ariane 5G
rocket from Kourou at 22:33 UT on 21 December 2005. The
two tonne, spin-stabilized craft carries two main instruments.
SEVIRI (Spinning Enhanced Visible and InfraRed Imager) will
provide images taken in four visible and eight infrared
channels every 15 minutes, at a resolution of 1 km in visible
light and 3 km in infrared. GERB (Geostationary Earth
Radiation Budget) will monitor the energy balance between the
incoming solar flux, and the outgoing infrared radiation. The
craft will be renamed Meteosat 9 when it becomes operational
in June 2006, after parking over 0.0° longitude. (There have
been eight Meteosats in the first generation Meteosat series)
Meteosat Second
Generation 2
Meteosat 9
28912
Facts in Brief
5GS
French Guiana
Mass: 2000.0 kg
Funding Agency
European Meteorological
Satellite Agency
(International)
Discipline
Earth Science
Additional
Information
Launch/Orbital
information for MSG 2
Experiments on MSG 2
Data collections from MSG
2
Office.
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Mtsat-1R
Publications
NSSDC ID: 2005-006A
Maps
New/Updated Data
Alternate Names
Description
Mtsat-1R is a Japanese geostationary weather satellite that
was launched by a H-2A rocket from Tanegashima Space
Center in Kagoshima prefecture at 09:25 UT. The 1.78 tonne,
satellite will make continuous observations of Earth's surface
and cloud cover. Another package on-board will relay
transmissions from mobile telephones. It is expected to replace
HIMAWARI 5 after parking over 140 deg-E longitude.
28622
Facts in Brief
Launch Vehicle: H-2A
Launch
Site: Tanegashima, Japan
Funding Agency
Unknown (Japan)
Discipline
Earth Science
Additional
Information
Launch/Orbital
information for Mtsat-1R
Experiments on Mtsat-1R
Mtsat-1R
Office.
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Navstar 57
Publications
NSSDC ID: 2005-038A
Maps
New/Updated Data
Alternate Names
Description
Navstar 57, also known as USA 183 and as GPS 2R-M1 (and
as GPS 2R-14), was launched by a Delta 2 rocket from Cape
Canaveral AFS at 03:37 UT on 26 September 2005. It has
three more frequency channels (with two more military and one
more civilian), and is more secure against jamming and
radiation than the older models. It will be positioned in Slot 4 of
Plane C, taking over the duties of the aging GPS 2A-20 (that
was launched in May 1993). It is planned to replace all the
older members of the 28-satellite fleet with the updated 2R-M
versions in a few years. (The perigee will be raised from 266
km to about 20,000 km soon.)
USA 183
GPS 2R-M1
GPS 2R-14
28874
Facts in Brief
II
Launch Site: Cape
Funding Agency
Discipline
Navigation & Global
Positioning
Additional
Information
Launch/Orbital
information for Navstar 57
Experiments on Navstar 57
Navstar 57
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NOAA 18
Publications
NSSDC ID: 2005-018A
Maps
New/Updated Data
Description
NOAA 18 continues the fourth-generation of operational, polar
orbiting, meteorological satellite series (NOAA K-N) operated
by the National Environmental Satellite Service (NESS) of the
National Oceanic and Atmospheric Administration (NOAA).
NOAA 18 also continues the series of Advanced TIROS-N
(ATN) spacecraft begun with the launch of NOAA 8 (NOAA-E)
in 1983 but with additional new and improved instrumentation
over the NOAA A-J series and a new launch vehicle (Titan II).
NOAA 18 will be in an afternoon equator-crossing orbit and is
intended to replace NOAA 17 as the prime afternoon
spacecraft.
The goal of the NOAA/NESS polar-orbiting program is to
provide output products used in meteorological prediction and
warning, oceanographic and hydrologic services, and space
environment monitoring. The polar orbiting system
complements the NOAA/NESS geostationary meteorological
satellite program (GOES).
The NOAA 18 Advanced TIROS-N spacecraft is based on the
Defense Meteorological Satellite Program (DMSP) Block 5D
spacecraft and is a modified version of the ATN spacecraft
(NOAA 6-11, I-J) to accomodate the new instrumentation,
supporting antennas and electrical subsystems. The spacecraft
structure consists of four components: (1) the Reaction System
Support (RSS); (2) the Equipment Support Module (ESM); (3)
the Instrument Mounting Platform (IMP); and (4) the Solar
Array (SA). All of the instruments are located on the ESM and
the IMP. The spacecraft power is provided by a direct energy
transfer system from the single solar array which is comprised
of eight panels of solar cells. The in-orbit Attitude
Determination and Control Subsystem (ADACS) provides
three-axis pointing control by controlling torque in three
mutually orthogonal momentum wheels with input from the
Earth Sensor Assembly (ESA) for pitch, roll, and yaw updates.
The ADACS controls the spacecraft attitude so that orientation
of the three axes is maintained to within +/- 0.2 degrees and
pitch, roll, and yaw to within 0.1 degree. The ADACS consists
of the Earth Sensor Assembly (ESA), the Sun Sensor
Assembly (SSA), four Reaction Wheel Assemblies (RWA), two
roll/yaw coils (RYC), two pitch torquing coils (PTC), four gyros,
and computer software for data processing. The ATN data
handling subsystem, consists of the TIROS Information
Processor (TIP) for low data rate instruments, the Manipulated
Information Rate Processor (MIRP) for high data rate AVHRR,
digital tape recorders (DTR), and a cross strap unit (XSU).
The NOAA 18 instrument complement consists of: (1) an
improved six-channel Advanced Very High Resolution
Alternate Names
Advanced TIROS-N
(ATN)
NOAA-N
28654
Facts in Brief
II
Launch
United States
Mass: 1457.0 kg
Nominal
Power: 330.0 W
Funding Agencies
National Oceanic and
Atmospheric
Administration (United
States)
NASA-Office of Space
Science Applications
(United States)
Disciplines
Engineering
Earth Science
Solar Physics
Space Physics
Additional
Information
Launch/Orbital
information for NOAA 18
NOAA 18
Telecommunications
information for NOAA 18
Radiometer/3 (AVHRR/3); (2) an improved High Resolution
Infrared Radiation Sounder (HIRS/3); (3) the Search and
Rescue Satellite Aided Tracking System (S&R), which consists
of the Search and Rescure Repeater (SARR) and the Search
and Rescue Processor (SARP-2); (4) the French/CNESprovided improved ARGOS Data Collection System (DCS-2);
(5) the Solar Backscatter Ultraviolet Spectral radiometer
(SBUV/2); and (6) the Advanced Microwave Sounding Unit
(AMSU), which consists of three separate modules, A1, A2,
and B to replace the previous MSU and SSU instruments.
Experiments on NOAA 18
NOAA 18
Office.
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E-mail
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OICETS
Publications
NSSDC ID: 2005-031A
Maps
New/Updated Data
Alternate Names
Description
OICETS (Optical Inter-orbit Communications Engineering Test
Satellite) is a Japanese (JAXA) technology demonstration
satellite that was launched by a Dnepr booster from Baikonur
at 21:10 UT on 23 August 2005. The 600 kg satellite carries an
optical communications instrument called LUCE (LaserUtilizing Communications Equipment) which has a 10-inch
telescope that acts as a transmitter and receiver to
communicate with the European (ESA) satellite, Artemis.
OICETS will study the effect of the irreducible vibrations in a
satellite in maintaining a pointing accuracy of one millidegree
that is required to communicate with another satellite 32,000
km away.
Optical Inter-orbit
Communications
Engineering Test Satellite
Kirari
28809
Facts in Brief
Launch Vehicle: Dnepr
Kazakhstan
Mass: 600.0 kg
Funding Agency
Japan Aerospace
Exploration Agency
(Japan)
Discipline
Communications
Additional
Information
Launch/Orbital
information for OICETS
Experiments on OICETS
OICETS
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Progress M-52
Publications
NSSDC ID: 2005-007A
Maps
New/Updated Data
Alternate Names
Description
Progress M-52 is a Russian automatic cargocraft that was
launched by a Soyuz-U rocket from Baikonur at 19:09 UT on
28 February 2005. It carried 2.5 tonnes of food, fuel, water and
equipment to the International Space Station (ISS). Also onboard were 50 snails to test the effect of microgravity. It is to
dock with the ZARYA module of the ISS at 20:15 UT on 2
March 2005. In anticipation of the docking, the earlier
Progress-M51 was vacated from its port on 27 February at
16:06 UT to deorbit eventually after 10 days in free orbit.
28624
Facts in Brief
Launch
Vehicle: Soyuz-U
Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Resupply/Refurbishment/Repair
Additional
Information
Launch/Orbital
information for Progress
M-52
Experiments on Progress
M-52
Progress M-52
Office.
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Progress M-53
Publications
NSSDC ID: 2005-021A
Maps
New/Updated Data
Alternate Names
Description
Progress M-53 is a Russian automatic cargo craft that was
launched at 23:09 UT on 16 June 2005 by a Soyuz-U rocket
from Baikonur. The craft carried 2.5 tonnes of food, water, fuel,
and supplies to the International Space Station (ISS). It docked
with the Zvezda module of the ISS "manually" (after a glitch in
communications link) at 00:44 UT on 18 June, with commands
from the Russian astronaut on board the ISS. In anticipation of
the docking, the previously docked Progress-M 52, carrying
over a tonne of garbage from the station, was evicted from its
port to deorbit into the Pacific Ocean.
28700
Facts in Brief
Launch
Vehicle: Soyuz-U
Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Additional
Information
Launch/Orbital
M-53
M-53
Progress M-53
Office.
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Progress M-54
Publications
NSSDC ID: 2005-035A
Maps
New/Updated Data
Alternate Names
Description
Progress M-54 is a Russian automatic cargo transportation
satellite that was launched by a Soyuz-U rocket from Baikonur
at 13:08 UT on 8 September. It carried 2.4 tonnes of food,
water, oxygen, fuel, and equipment to supply the International
Space Station (ISS). It docked with Zvezda module of the ISS
automatically at 14:50 UT on 10 September, and delivered the
cargo. In preparation for the docking, the previously docked
Progress M-53, carrying a full load of trash was undocked and
allowed to deorbit and burn away.
28866
Facts in Brief
Launch
Vehicle: Soyuz-U
Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Additional
Information
Launch/Orbital
M-54
M-54
Progress M-54
Office.
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Progress M-55
Publications
NSSDC ID: 2005-047A
Maps
New/Updated Data
Alternate Names
Description
Progress M-55 is a Russian automatic cargo craft that was
launched by a Soyuz-U rocket from Baikonur at 18:38 UT on
21 December 2005. The 5.7 tonne craft (including 880 kg of
propellant) carried 210 kg of water, 83 kg of air, and 1.4 tonne
of equipment and spare parts to the International Space
Station. Some of propellant will be transferred to the ISS for its
maneuvering thrusters. It docked with the PIRS module of the
ISS automatically at 19:56 UT on 23 December, and delivered
the cargo.
28906
Facts in Brief
Launch
Vehicle: Soyuz-U
Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Additional
Information
Launch/Orbital
M-55
M-55
Progress M-55
Office.
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Reimei
Publications
NSSDC ID: 2005-031B
Maps
New/Updated Data
Alternate Names
Description
Reimei, with a prelaunch name of Index, is a Japanese (ISAS)
microsatellite that was launched by a Dnepr booster (which is a
converted RS-20 ICBM) from Baikonur at 21:10 UT on 23
August 2005. The 70 kg experimental satellite carries
components and technologies such as fiber optic gyroscope to
improve attitude control, more efficient solar panels, and a
manganese lithium ion battery that will be exposed to the
radiation environment in space to test ruggedness. It also
carries energetic ions/electrons detectors to derive the energy
spectra of the particles that cause auroras. (Also launched by
that Dneper into orbit was a container with a book of spiritual
guidance written by the Turkmenistan's President Niyazov, to
confirm that his country has "entered the Space Age".)
28810
Facts in Brief
Launch Vehicle: Dnepr
Kazakhstan
Mass: 70.0 kg
Funding Agency
Unknown (Japan)
Disciplines
Engineering
Space Physics
Additional
Information
Launch/Orbital
information for Reimei
Experiments on Reimei
Reimei
Office.
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Rodnik
Publications
NSSDC ID: 2005-048B
Maps
New/Updated Data
Alternate Names
Description
Rodnik, also listed as Cosmos 2416, is a Russian military
satellite that was launched by a Kosmos-3M rocket from
Plesetsk at 18:34 UT on 21 December 2005.
Cosmos 2416
28909
Facts in Brief
Launch
Vehicle: Kosmos-3M
Russia
Funding Agency
Unknown (Russia)
Discipline
Military
Additional
Information
Launch/Orbital
information for Rodnik
Experiments on Rodnik
Rodnik
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Shenzhou 6
Publications
NSSDC ID: 2005-040A
Maps
New/Updated Data
Alternate Names
Description
Shenzhou 6 (meaning Divine Ship) is a Chinese passenger
craft that was launched by a Long March 2F rocket from
Jiuquan in northwest China at 01:00 UT on 12 October 2005. It
carried two Chinese astronauts in the re-entry capsule, also
named as SHENZHOU 6, to orbit around for about five days.
The re-entry capsule separated from the orbiter module and
parachuted down on Inner Mongolia on 16 October 2005 at
20:32 UT. The orbiter module continued to do scientific
research.
28879
Facts in Brief
March 2F
Funding Agency
China National Space
Administration (Peoples
Republic of China)
Discipline
Human Crew
Additional
Information
Launch/Orbital
information for Shenzhou
6
Experiments on Shenzhou
6
Shenzhou 6
Office.
Shenzhou 6
Launch, orbit and landing data
Launch date:
Launch time:
Launch site:
Launch pad:
Altitude:
Inclination:
Landing date:
Landing time:
Landing site:
25.09.2008
13:10 UT
Jiuquan Satellite Launching
Center
1 (?)
330 - 340 km
42,4°
Crew
No.
Surname Given name
Job
Flight No.
Duration
Orbits
3d 08h 13m
1
Zhai
Zhigang
Commander
1
3d 08h 13m
2
Liu
Buoming
Operator
1
3d 08h 13m
3
Jing
Haipen
Operator
1
Crew seating arrangement
Launch
1 Zhai
2 Liu
3 Jing
Landing
1 Zhai
2 Liu
3 Jing
Flight
Launch from Jiuquan Satellite Launching Center; third Chinese manned spaceflight.
Zhai performed the the first spacewalk of a Chinese on 27.09.2008 (22m). He was assisted by Liu who
made a stand-up EVA. Two hours later the crew released a small satellite with the name "BanXing".
Photos / Drawings
SZ 3
Historic flights of the chinese Shenzhou (SZ) manned spacecraft:
#
1
2
3
4
5
6
Date
20.11.1999
09.01.2001
25.03.2002
29.12.2002
15.10.2003
12.10.2005
Flight
Shenzhou 1
Shenzhou 2
Shenzhou 3
Shenzhou 4
Shenzhou 5
Shenzhou 6
Crew
--------Cdr
Cdr
Plt
Crew
--------Yang Liwei
Fei Junlong
Nie Haisheng
Payload
1
1
1
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Shijian 7
Publications
NSSDC ID: 2005-024A
Maps
New/Updated Data
Alternate Names
Description
Shijian 7 is a Chinese (PRC) satellite that was launched by a
Long March 2D rocket from Jiuquan Satellite Launch Center at
22:40 UT (at 06:40 a.m.) on 05 July 2005. "It will monitor the
space environment and conduct other special scientific and
technological experiments during a three year time-span.",
according to Xinhua News agency.
SJ 7
28737
Facts in Brief
March 2D
Funding Agency
Unknown (Peoples
Republic of China)
Disciplines
Engineering
Space Physics
Additional
Information
Launch/Orbital
information for Shijian 7
Experiments on Shijian 7
Shijian 7
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Sinah 1
Publications
NSSDC ID: 2005-043D
Maps
New/Updated Data
Alternate Names
Description
Sinah 1 is an Iranian microsatellite (170 kg) that was launched
by a Cosmos 3M rocket from Plesetsk at 06:52 UT on 27
October 2005. Iranian press reports that it is intended for
"telecommunications and research". There are also a few
reports where its name is spelled as Sina 1.
Sina 1
28893
Facts in Brief
Launch
Vehicle: Cosmos
Russia
Funding Agency
Iranian Space Agency
(Iran)
Discipline
Earth Science
Additional
Information
Launch/Orbital
information for Sinah 1
Experiments on Sinah 1
Data collections from Sinah
1
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Sloshsat
Publications
NSSDC ID: 2005-005C
Maps
New/Updated Data
Alternate Names
Description
Sloshat is a Dutch experimental mini-satellite that was
launched by an Ariane 5-ECA rocket from Kourou at 21:03 UT
on 12 February 2005. The 127 kg satellite will test for 10 days
in the transfer orbit the dynamics of fluid (33.5 liters of
deionized water) in orbit with the help of many embedded
sensors and a few thrusters and accelerometers. It is also
known as SLOSHSAT-FLEVO (Facility for Liquid
Experimentation and Verification in Orbit. Flevo is also the
name for the latest province in Netherlands that was reclaimed
from the sea.)
28544
Facts in Brief
5 ECA
French Guiana
Discipline
Engineering
Additional
Information
Launch/Orbital
information for Sloshsat
Experiments on Sloshsat
Sloshsat
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Soyuz-TMA 6
Publications
NSSDC ID: 2005-013A
Maps
New/Updated Data
Description
Soyuz-TMA 6 is a Russian automatic passenger transport craft
that was launched by a Soyuz-U rocket from Baikonur at 00:46
UT on 15 April 2005. It transported a crew of three astronauts
(a Russian, an American, and an Italian) to the International
Space Station (ISS). The automatic docking took place at
02:19 UT on 17 April, as planned. During a 10-day visit, the
Italian astronaut carried out experiments in human physiology,
biology, technology, and education, and returned to earth in
the previously docked Soyuz-TMA 5 (along with the two
astronauts who had endured six months in the ISS). The other
two astronauts on TMA-6 will spend the next six months in the
station.
Alternate Names
28640
Facts in Brief
Launch
Vehicle: Soyuz-U
Kazakhstan
Funding Agencies
(United States)
Russian Space Agency
(Russia)
Disciplines
Human Crew
Life Science
Additional
Information
Launch/Orbital
information for SoyuzTMA 6
Experiments on SoyuzTMA 6
Soyuz-TMA 6
Office.
Soyuz TMA-6
15.04.2005
00:46 UT
Baikonur
1
198,55 - 245,50 km
51.66°
11.10.2005
01:09 UT
50° 44' 00" N, 67°
25' 41" E
Launch date:
Launch time:
Launch site:
Launch pad:
Altitude:
Inclination:
Landing date:
Landing time:
Landing site:
Crew
No
.
Surname
Given name
1
Krikalyo Sergei
v
Konstantinovich
2
Vittori
Roberto
3
Phillips
John Lynch
Job
Commander
Flight
Engineer
Flight
Engineer
Flight No.
6
2
2
Duration
Orbit
s
179d 00h 23m 2818
9d 21h 22m
155
179d 00h 23m 2818
Launch
1 Krikalyov
2 Vittori
3 Phillips
Landing
1 Krikalyov
2 Phillips
3 Olsen
Flight
Launch from Baikonur; landing 68 km northeast of Arkalyk.
ISS Expedition 11; "caretaker" crew; docking to ISS; crew replaced expedition 10 crew. The crew
performed routine maintenance, repairing work (for example a faulty restraint cable on the exercise
treadmill), scientific research, as FOOT-experiment (Foot/Ground Reaction Forces During Spaceflight
experiment) the Miscible Fluids in Microgravity (MFMG) investigation and so on, practicing
photography techniques with digital cameras; this techniques were used to capture high resolution
images of Space Shuttle Discovery before docking on the station to control the heat shield of the
Shuttle.
On June 18, 2005 the unpiloted ISS Progress 18 docked on the Station to deliver more than two tons of
food, fuel, oxygen, water, supplies and spare parts including repair efforts on the Elektron oxygen
generation system. The Elektron, one of multiple sources of oxygen available on the Station, derives
oxygen from water. The system had been inoperable for a few months. As the Progress approached the
Station, Commander Sergei Krikalyov had to take over manual control of the docking of the Progress
due to a Russian ground station problem that prevented commands to be uplinked to the cargo ship for
its final approach for an automated docking.
On July 18, 2005 the crew relocated their Soyuz return spacecraft from one docking port to another to
free up a Russian airlock for a future spacewalk.
On July 28, 2005 the Space Shuttle Discovery (STS-114) docked on the Station after doing a planned
back flip so Station crewmembers could photograph its thermal protection system, there were some
damages. Undocking of STS-114 was on 06.08.2005.
EVA by Krikalyov and Phillips on 18.08.2005 (4h 58m) to change out a Russian biological
experiment, retrieve some radiation sensors, remove a Japanese materials science experiment,
photograph a Russian materials experiment, install a television camera and relocate a grapple fixture.
Vittori performed several scientific experiments during the Eneide-mission.
Note
Vittori landed on 24.04.2005 at 22:08 UT with Soyuz TMA-5-spacecraft.
Photos / Drawings
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Soyuz-TMA 7
Publications
NSSDC ID: 2005-039A
Maps
New/Updated Data
Alternate Names
Description
Soyuz-TMA 7 is a Russian passenger transportation craft that
was launched by a Soyuz-FG rocket from Baikonur at 03:55
UT on 1 October 2005. It carried a Russian and an American
astronaut, and a tourist from America to the International
Space Station (ISS). It docked with the Pirs module at 05:30
UT on 3 October automatically. The astronauts did some
space-walks; the tourist grew some crystals. The previously
docked Soyuz-TMA 6 separated from the ISS, and soft-landed
in Kazakhstan at 04:08 UT on 10 October, returning that tourist
and the two previous astronauts who had inhabited the ISS for
six months.
28877
Facts in Brief
Launch Vehicle: Soyuz
FG
Kazakhstan
Funding Agency
Unknown (Russia)
Disciplines
Human Crew
Additional
Information
Launch/Orbital
information for SoyuzTMA 7
Experiments on SoyuzTMA 7
Soyuz-TMA 7
Office.
Soyuz TMA-7
Launch date:
Launch time:
Launch site:
Launch pad:
Altitude:
Inclination:
Landing date:
Landing time:
Landing site:
01.10.2005
03:54 UT
Baikonur
1
193 - 245 km
51,66 °
08.04.2006
23:47 UT
50° 40' 03.42" N,
67° 21' 22.32" E
Crew
No
.
Surnam
e
Given name
Job
Flight No.
Duration
Orbit
s
1
Tokarev Valeri Ivanovich
Commander
2
189d 19h 53m 2991
2
McArth William Surles, Jr.
ur
"Bill"
Flight Engineer
4
189d 19h 53m 2991
3
Olsen
Gregory Hammond
"Greg"
Spaceflight
Participant
1
9d 21h 15m
155
Launch
1 Tokarev
2 McArthur
3 Olsen
Landing
1 Tokarev
2 McArthur
3 Pontes
Flight
Launch from Baikonur; landing 55 km northeast of Arkalyk.
ISS Expedition 12; "caretaker" crew; docking to ISS; crew replaced expedition 11 crew.
First EVA by McArthur and Tokarev on 07.11.2005 (5h 22m) to install a television camera on the
station's part truss, needed for future assembly work, to remove the 5 year-old FPP-experiment
(Floating Potential Probe) from the top of the P6 truss and to remove and replace other equipment; on
18.11.2005 the Soyuz TMA-7 spacecraft was relocated from the Pirs docking port to the Nadir
Docking port of the Zarya module; that was necessary to start the second EVA from out the the Pirs
Docking Compartment airlock.
Second EVA by McArthur and Tokarev on 03.02.2006 (5h 43m) to deploy SuitSat, an unneeded
Russian spacesuit with an amateur radio transmitter. The SuitSat provided recorded greetings in six
languages to ham radio operators for about two orbits of the Earth before it stopped transmitting,
perhaps due to its batteries failing in the cold environment of space. They then removed a grapple
fixture adapter for the Strela crane to the PMA-3 on the Unity module. Then they tried to securely
install a safety bolt in a contingency cutting device for one of two cables that provide power, data and
video to the Mobile Transporter rail car, but this failed. Finally they retrieved an experiment to study
the effect of the space environment on microorganisms from the Russian Pirs airlock and
photographed the exterior of Zvezda.
On 20.03.2006 the Soyuz TMA-7 spacecraft was relocated again, now from the Zarya module to the
Zvezda port. Additional work during this mission included different research programs as FootGround Reaction Forces during Space Flight experiment (FOOT), Protein Crystal Growth Monitoring
by Digital Holographic Microscope for the International Space Station (PROMISS-4), Binary
Colloidal Alloy Test, but also “housekeeping”, repairing work, unload and reload of Progressfreighters and more.
Note
Olsen landed on 11.10.2005 at 01:09 UT with Soyuz TMA-6-spacecraft.
Photos / Drawings
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Spaceway 1
Publications
NSSDC ID: 2005-015A
Maps
New/Updated Data
Alternate Names
Description
Spaceway 1 is an American geostationary communications
satellite that was launched at 07:32 UT on 26 April 2005 by a
Zenit 3SL rocket from the floating platform, Odyssey parked at
154 deg-W longitude on the equatorial Pacific Ocean. The
satellite belongs to the well-known fleet of DIRECTV. The 3.8
tonne, 12.3 kW, 3.4 m x 3.2 m x 5.1 m satellite will provide
high-speed internet connections along with digital TV and
other channels to all of North America through its 17 Ku-band
transponders after parking over 102.8 deg-W longitude.
28644
Facts in Brief
3SL
Funding Agency
Discipline
Communications
Additional
Information
Launch/Orbital
information for Spaceway
1
Experiments on Spaceway
1
Spaceway 1
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Spaceway 2
Publications
NSSDC ID: 2005-046A
Maps
New/Updated Data
Alternate Names
Description
Spaceway 2 is an American geostationary communications
satellite that was launched by an Ariane-5 ECA rocket from
Kourou at 23:46 UT on 16 November 2005. The six tonne,
12.3 kW satellite carries 48 Ka-band transponders to provide
high-speed, high-definition video and internet services to
DIRECTV customers in North America after parking over 99
deg-W longitude.
28902
Facts in Brief
5 ECA
French Guiana
Funding Agency
Discipline
Communications
Additional
Information
Launch/Orbital
information for Spaceway
2
Experiments on Spaceway
2
Spaceway 2
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SSETI-Express
Publications
NSSDC ID: 2005-043E
Maps
New/Updated Data
Description
SSETI-Express (Student Space Exploration and Technology
Initiative-Express) is a student-built microsatellite of mass 62
kg that was launched by a Cosmos 3M rocket from Plesetsk at
06:52 UT on 27 October 2005. It will take pictures of the Earth
and facilitate amateur radio links. It carried and released three
picosatellites, each of mass 1 kg.
Alternate Names
Student Space
Exploration and
Technology InitiativeExpress
OSCAR 53
28894
Facts in Brief
Launch
Vehicle: Cosmos
Russia
Mass: 62.0 kg
Funding Agency
Student Space
Exploration and
Technology Initiative
(International)
Disciplines
Communications
Earth Science
Additional
Information
Launch/Orbital
information for SSETIExpress
Telecommunications
information for SSETIExpress
Experiments on SSETIExpress
SSETI-Express
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2005-043E[18/10/2010 0:29:54]
Office.
http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=2005-043E[18/10/2010 0:29:54]
Wednesday, 20 October 2010
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STP-R1
Publications
NSSDC ID: 2005-037A
Maps
New/Updated Data
Alternate Names
Description
STP-R1, also known as USA 185, is an American military
(DARPA) technology test/demonstration satellite that was
launched by a Minotaur 1 rocket (which is a modified
Minuteman 2 ICBM) from Vandenburg AFB at 02:24 UT on 23
September 2005.
The satellite was fitted with two instruments:- an ion gauge and
an atomic oxygen sensor. The vehicle will characterize the
orbital regime, demonstrate operational feasibility from a
command and control standpoint and also from a platform
perspective for future DoD missions.
Streak
USA 185
28871
Facts in Brief
Launch
Vehicle: Minotaur
Launch
United States
Mass: 417.0 kg
Funding Agency
Defense Advanced
Research Projects
Agency (United States)
Discipline
Military
Additional
Information
Launch/Orbital
information for STP-R1
Experiments on STP-R1
Data collections from STPR1
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STS 114
Publications
NSSDC ID: 2005-026A
Maps
New/Updated Data
Alternate Names
Description
STS 114 is an American shuttle craft that was launched from
Cape Canaveral at 15:39 UT on 26 July 2005. It was launched
after 29 months of post-mortem analysis of the flaws that led
to the explosive end of the previous mission. STS 114 carried
several cameras to look out for damage on its own surface
and on the foam covering the external fuel tank. Many more
ground-based cameras and radars monitored the initial
trajectory after the launch. The shuttle also carried repair kits to
fix tile-related problems and a 15 meter robotic arm to spot and
examine tile degradations. So far, a few (probably) minor
damages to the tiles have been identified.
EPILOG,9 Sep 2005: The shuttle safely landed in Edwards Air
Base near Los Angeles at 12:12 UT on 9 sep 2005.
The shuttle docked with the International Space Station on 28
July and delivered 12 tonnes of goods and equipment to the
ISS. Two of the crew of seven astronauts participated in
practicing with the caulking guns and putty-knives in the open
cargo bay for seven hours (on 30 July), in preparation for the
space walks that were entailed to repair actual faults. The
crew also replaced a defective gyroscope on the ISS. It is
expected to complete the mission and return to Earth on 08
August 2005. It has been reported that all planned near-future
shuttle launches are cancelled pending yet another reappraisal
of the safety issues. Meanwhile three Russian Soyuz-TMA
craft are on standby to rescue the crew should the shuttle be
deemed unfit for the return journey. The on-going progress of
the mission may be accessed via:
http://spaceflight.nasa.gov/
28775
Facts in Brief
Launch
Vehicle: Shuttle
Launch Site: Cape
Funding Agency
(United States)
Disciplines
Engineering
Human Crew
Additional
Information
Launch/Orbital
information for STS 114
Experiments on STS 114
Data collections from STS
114
Office.
STS-114
Insignia de la misión
Misión
Transbordador
Plataforma de
lanzamiento
Lanzamiento
Datos de la misión
STS-114
Discovery
39-B
26 de julio de 2005, 10:39 AM EDT (1439
UTC).
9 de agosto de 2005, 8:11 AM EDT (1211
Aterrizaje
UTC) en la Base Edwards.
13 días, 21 horas, 33 minutos (estaba
Duración
planeado para 11 días, 19 horas, 10
minutos)
122 millas naúticas (226 km)
Altitud orbital
Inclinación orbital 51,6 grados
Distancia recorrida 5,8 millones de millas (9.3 millones de km)
Tripulación
Detrás (I–D): Robinson, Thomas, Camarda, Noguchi
Delante (I–D): Kelly, Lawrence, Collins
La misión STS-114 del Transbordador espacial Discovery fue lanzada a las 10:39 EDT (1439 UTC), el
26 de julio de 2005. El lanzamiento se produjo 907 días después del desastre del transbordador espacial
Columbia (1 de febrero de 2003). Se realizó a pesar de no haber resuelto unas anomalías con el sensor de
fuel del tanque externo; estas anomalías habían impedido el lanzamiento desde el 13 de julio, fecha
originalmente programada.
La misión se completó el 9 de agosto de 2005. Debido a la meteorología en el Centro Espacial Kennedy,
el transbordador aterrizó en la Base Aérea Edwards, California, un lugar secundario.
El problema que causó la destrucción del Columbia - escombros separados del tanque externos durante el
ascenso - inesperadamente volvió a suceder durante el lanzamiento del Discovery. Debido a esto, la
NASA decidió el 27 de julio posponer los vuelos futuros del transbordador hasta realizar modificaciones
en el hardware.
Tripulación
•
•
•
•
•
•
•
Eileen M. Collins (4), Comandante
James Kelly (2), Piloto
Soichi Noguchi (1), Especialista de misión
Stephen K. Robinson (3), Especialista de misión
Andrew Thomas (4), Especialista de misión
Wendy Lawrence (4), Especialista de misión
Charles Camarda (1), Especialista de misión
( ) El número entre paréntesis indica el número de vuelos espaciales incluida la misión STS-114.
Parámetros de la misión
•
•
•
•
•
•
Masa:
o Del Orbiter al despegar: 121.483 kg
o Del Orbiter al aterrizar: 102.913 kg
Perigeo: Apogeo: 350,8 km
Inclinación: 51,6º
Velocidad: 27.661 km/h
Período: 91,6 minutos
La misión
Despegue del Discovery desde el Centro Espacial Kennedy, el 26 de julio de 2005
La misión STS-114 marcó el regreso a los vuelos del transbordador espacial después del desastre del
Columbia, siendo el segundo vuelo con una comandante (Eileen Collins, quien también lo fue en la
misión STS-93). La STS-114 inicialmente se iba a desarrollar a bordo del Atlantis, pero un fallo en el
sistema de frenado condujo a la NASA a elegir al Discovery como vehículo para la misión. Diecisiete
años antes, el Discovery había sido también el primer vuelo de un transborador tras el desastre del
Challenger.
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SuitSat
Publications
NSSDC ID: 2005-035C
Maps
New/Updated Data
Alternate Names
Description
SuitSat is a payload that was installed in a discarded Russian
Orlan EVA suit that was ejected from the International Space
Station. It carried an amateur radio beacon that was activated
in the two meter band.
Radioskaf
After activation SuitSat transmitted for several orbits and then
was thought to go silent. However better equipped stations
were able to continue to hear it, and it was assumed that it
somehow dropped into a very low power mode. NORAD later
identified some debris in the vicinity of SuitSat (NORAD
Number 28934) which may have been part of the payload or
possibly the SuitSat antenna.
Facts in Brief
Based on the reports the SuitSat team has received, the last
confirmed reception of the SuitSat voice audio was on
Saturday February 18 Bob King's station, VE6BLD in Canada.
The last confirmed telemetry was received by Richard Crow's
station, N2SPI in the USA.
Oscar 54
28933
Launch
Vehicle: Soyuz-U
Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Communications
Additional
Information
Launch/Orbital
information for SuitSat
Experiments on SuitSat
SuitSat
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Suzaku
Publications
NSSDC ID: 2005-025A
Maps
New/Updated Data
Description
Suzaku (Astro-E2) is a Japanese (ISAS/JAXA) astronomy
satellite. Suzaku is Japan's fifth X-ray astronomy satellite and
the third for which the US has provided a significant part of the
scientifc payload. It will monitor the universe in the 0.3-700 keV
X-ray band, in conjunction with the Chandra (NASA) and
XMM-Newton (ESA) satellites. Suzaku is designed to obtain
precise measurements of high-energy processes in stars,
supernova remnants, galaxies, clusters of galaxies, and the
environments around neutron stars and black holes. Suzaku is
equipped with X-ray telescopes and two instruments: The XIS
(X-ray Imaging Spectrometer) and the HXD (Hard X-ray
Detector). Suzaku also carries a third instrument, the XRS (Xray Spectrometer), but the XRS lost all its cryogen before
routine scientific observations could begin.
Suzaku is the recovery mission for ASTRO-E, which did not
achieve orbit during launch in February 2000. The 1,600 kg,
500 W, octagonal (2 m x 5 m), triaxially-stabilized spacecraft
carries six instruments, covering the sky between 60 degrees
and 120 degrees away from the Sun. The mission has
significant participation from NASA and MIT.
Alternate Names
Astro-E2
28773
Facts in Brief
Launch Vehicle: M-5
Launch Site: Uchinoura
Space Center, Japan
Mass: 1600.0 kg
Nominal
Power: 500.0 W
Funding Agencies
Japan Aerospace
Exploration Agency
(Japan)
(United States)
Discipline
Astronomy
Additional
Information
Launch/Orbital
information for Suzaku
Experiments on Suzaku
Suzaku
Office.
Personnel
Name
Role
E-mail
Dr. Nicholas
E. White
Program Scientist
NASA Goddard Space
Flight Center
[email protected]
Dr. Richard
L. Kelley
Mission Principal
Investigator
NASA Goddard Space
Flight Center
[email protected]
Mr. H. Inoue
Project Manager
Nagoya University
Dr. Hideyo
Kunieda
Program Scientist
Nagoya University
Other Sources of Suzaku Information/Data
Project Home Page (JAXA)
Suzaku Guest Observor Facility (HEASARC)
X-ray Imaging Spectrometer (XIS) (MIT)
X-Ray Spectrometer (XRS) (NASA GSFC)
Hard X-ray Detector (HXD) (U. Tokyo)
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Syracuse 3A
Publications
NSSDC ID: 2005-041B
Maps
New/Updated Data
Alternate Names
Description
Syracuse 3A is a French geostationary military
communications craft that was launched by an Ariane 5 rocket
from Kourou at 22:32 UT on 13 October 2005. No additional
information is available.
28885
Facts in Brief
5GS
French Guiana
Mass: 3725.0 kg
Funding Agency
Ministry of Defense,
France (France)
Discipline
Military
Additional
Information
Launch/Orbital
information for Syracuse
3A
Experiments on Syracuse
3A
Syracuse 3A
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Tatiana
Publications
NSSDC ID: 2005-002C
Maps
New/Updated Data
Alternate Names
Description
Tatiana, also known an Universitesky, is a Russian
microsatellite that was launched by a Cosmos-3M rocket from
Plesetsk at 03:00 UT on 20 January 2005. The 30-kg satellite
was built by the students of Lomonosov University as an
educational program to advance space physics and to
commemorate the university's 250th anniversary.
Universitesky
28523
Facts in Brief
Launch
Vehicle: Cosmos
Russia
Funding Agency
Unknown (Russia)
Discipline
Space Physics
Additional
Information
Launch/Orbital
information for Tatiana
Experiments on Tatiana
Tatiana
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Telcom 2
Publications
NSSDC ID: 2005-046B
Maps
New/Updated Data
Alternate Names
Description
Telcom 2 is an Indonesian triaxially-stabilized geostationary
telecommunications satellite that was launched by an Ariane-5
ECA rocket from Kourou at 23:46 UT on 16 November 2005.
The 1.9 tonne, satellite carries 24 C-band transponders and
spot-beams to provide high-speed communications for
Internet, data, voice, and video services to Indonesia, after
parking over 118 deg-E longitude.
28903
Facts in Brief
5 ECA
French Guiana
Funding Agency
Unknown (Indonesia)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Telcom 2
Experiments on Telcom 2
Telcom 2
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Thaicom 4
Publications
NSSDC ID: 2005-028A
Maps
New/Updated Data
Alternate Names
Description
Thaicom 4, also known as iPStar 1, is a Thai geostationary
communications satellite that was launched by an Ariane 5G
rocket from Kourou at 08:20 UT on 11 August 2005. The seven
tonne satellite, the most massive geostationary so far, carries
a solar sail power of 17.6 kW and will provide voice, video,
and broadband internet services to 14 countries including
India, Thailand, Japan, Indonesia, and Australia, through its 84
Ku-band and 18 Ka-band spot beams after parking over 120
degrees E longitude.
iPStar 1
28786
Facts in Brief
5GS
French Guiana
Mass: 6505.0 kg
Funding Agency
Unknown (Thailand)
Discipline
Communications
Additional
Information
Launch/Orbital
information for Thaicom 4
Experiments on Thaicom 4
Thaicom 4
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TNS-0
Publications
NSSDC ID: 2005-007C
Maps
New/Updated Data
Alternate Names
Description
TNS-0, also named Tex 42 is a Russian nanosputnik that was
released from Progress M-52 that was docked with the
International Space Station (ISS). (Its ID, 2005-007C derives
from the Progress M-52 ID, 2005-007A, which was launched
on 28 February 2005). The 5 kg nanosatellite will help validate
design of control- and orientation system on small satellites.
Tex 42
28547
Facts in Brief
Launch
Vehicle: Soyuz-U
Kazakhstan
Funding Agency
Unknown (Russia)
Discipline
Engineering
Additional
Information
Launch/Orbital
information for TNS-0
Experiments on TNS-0
Data collections from TNS0
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TopSat
Publications
NSSDC ID: 2005-043B
Maps
New/Updated Data
Alternate Names
Description
TopSat is a British microsatellite that was launched by a
Cosmos 3M rocket from Plesetsk at 06:52 UT on 27 October
2005. It will provide low-cost 2.5 m resolution, black and white
Earth images, and 5 m resolution color images.
28891
Facts in Brief
Launch
Vehicle: Cosmos
Russia
Discipline
Earth Science
Additional
Information
Launch/Orbital
information for TopSat
Experiments on TopSat
TopSat
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Tsinghua
Publications
NSSDC ID: 2005-043A
Maps
New/Updated Data
Alternate Names
Description
Tsinghua, with a prelaunch name Beijing 1, is a Chinese
(PRC) photo-imaging microsatellite (166 kg) that was launched
by a Cosmos 3M rocket from Plesetsk at 06:52 UT on 27
October 2005. It will help in planning projects for the 2008
Olympics, and monitor natural and man-made disasters.
28890
Facts in Brief
Launch
Vehicle: Cosmos
Russia
Funding Agency
Unknown (Peoples
Republic of China)
Discipline
Earth Science
Additional
Information
Launch/Orbital
information for Tsinghua
Experiments on Tsinghua
Tsinghua
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USA 181
Publications
NSSDC ID: 2005-004A
Maps
New/Updated Data
Alternate Names
Description
USA 181 is an American military satellite that was launched by
an Atlas 3B/Centaur rocket at 07:41 UT from Vandenberg AFB
on 3 February 2005. It is reported to be an NRO satellite
intended for ocean surveillance.
28537
Facts in Brief
Launch Vehicle: Altas
3B-Centaur
Launch
United States
Funding Agency
Discipline
Military
Additional
Information
Launch/Orbital
information for USA 181
Experiments on USA 181
Data collections from USA
181
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USA 182
Publications
NSSDC ID: 2005-016A
Maps
New/Updated Data
Alternate Names
Description
USA 182 is an American military reconnaissance satellite
belonging to the National Reconnaissance Office (NRO) that
was launched from Cape Canaveral by a Titan 4B rocket on 30
April 2005. The payload is strictly classified as are the orbital
parameters.
Lacrosse 5
28646
Facts in Brief
Launch Vehicle: Titan
4B
Launch Site: Cape
Funding Agency
National Reconnaissance
Office (United States)
Discipline
Military
Additional
Information
Launch/Orbital
182
Office.
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USA 186
Publications
NSSDC ID: 2005-042A
Maps
New/Updated Data
Alternate Names
Description
USA 186 is an American military reconnaissance craft that was
launched by a Titan 4B rocket from Vandenberg AFB at 18:05
UT on 19 October 2005. It marks the end of the Titan 4 era
which began in 1986 soon after the Challenger tragedy so as
to free the Pentagon from dependency on NASA's Shuttles.
Neither the payload nor the orbital information is available for
this NRO-commissioned mission.
28888
Facts in Brief
Launch Vehicle: Titan
4B
Launch
United States
Funding Agency
Discipline
Military
Additional
Information
Launch/Orbital
186
Office.
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UWE 1
Publications
NSSDC ID: 2005-043C
Maps
New/Updated Data
Alternate Names
Description
UWE 1 is a German picosatellite that was launched by a
Cosmos 3M rocket from Plesetsk at 06:52 UT on 27 October
2005. (It was actually released by/from SSETI-Express)
28892
Facts in Brief
Launch
Vehicle: Cosmos
Russia
Funding Agency
Unknown (Federal
Republic of Germany)
Discipline
Communications
Additional
Information
Launch/Orbital
information for UWE 1
Experiments on UWE 1
Data collections from UWE
1
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Venus Express
Publications
NSSDC ID: 2005-045A
Maps
New/Updated Data
Venus Express
Description
Venus Express is a European Space Agency (ESA) mission to
study the atmosphere and plasma environment of Venus from
orbit in 2006 and 2007. It will primarily be investigating: the
role played by the greenhouse effect in creation of the
atmosphere; the behavior and characteristics of cloud and
haze formation at different altitudes; processes at work in
atmospheric escape and its interaction with solar winds; and
the mechanism behind the super rotation in the upper
atmosphere. It will also study the weak Venus' magnetic field,
the UV absorption features at 80 km altitude, the high radio
wave reflectivity areas on the surface, the atmosphere-surface
interaction, and the possibility of volcanic or seismic activity.
The Venus Express spacecraft is based on the Mars Express
satellite bus and has a launch mass of 1240 kg, which includes
93 kg of payload and 570 kg of fuel. The main bus is a
rectangular box with dimensions of 1.65 x 1.7 x 1.4 meters.
The core structure within the box is composed of an aluminum
launch vehicle adapter ring, 90 cm in diameter and 20 cm high,
two aluminum beams embedded in the ring, aluminum braces,
two upper floors to hold the propellant tanks, an upper floor
and three shearwalls to provide stiffness. The floor and wall
panels are made of honeycomb bonded to aluminum face
sheets. Propulsion and reaction control are provided by a
bipropellant system comprising a 415-N main engine mounted
under the lower floor and eight 10-N thrusters located at the
four lower corners of the spacecraft. The two 267-liter
propellant tanks, one containing nitrogen tetroxide and one
containing mono-methyll hydrazine, are mounted in the center
of the core structure. A 35.5 liter tank contains helium for use
as a pressurant. Spacecraft attitude knowledge is provided by
two star trackers, two sun sensors, and two inertial
measurement units comprised of gyros and accelerometers.
Reaction wheels are used for attitude maintenance.
Power of 1100 W at 28 volts DC at Venus orbit is supplied by
two symmetric rotatable wings of 1056 gallium arsenide triple
junction (GaInP2/GaAs/Ge) solar cells with a total area of 11.4
square meters interlaced with aluminum strips to minimize
heating. Each wing has a mass of 20.7 kg. Power is stored in
three 24-Ah lithium-ion batteries. Communications are via
redundant dual band transponders which contain two duplicate
transmit/receive chains, each with an X-band transmitter (8419
MHz) and receiver (7166 MHz) and an S-band transmitter
(2296 MHz) and receiver (2100 MHz). The system uses a 1.3
meter high gain S- and X-band antenna, a smaller secondary
high-gain X-band antenna, and two low-gain omnidirectional Sband antennas. It also uses two 65-W travelling wavetube
amplifiers, a radio frequency distribution unit, and a waveguide
interface unit. Downlink rates of up to 262,000 kpps are
possible. Passive thermal control is achieved through the use
of radiators, Kapton multi-layer insulation, heat pipes, optical
solar reflecting covers and sulphuric anodisation coatings.
Data is stored in a 12 gigabit solid state mass memory and run
Alternate Names
28901
Facts in Brief
Launch
Vehicle: Soyuz-Fregat
Kazakhstan
Mass: 670.0 kg
Funding Agency
(International)
Discipline
Planetary Science
Additional
Information
Launch/Orbital
information for Venus
Express
Venus Express
Experiments on Venus
Express
Venus Express
Williams.
Selected References
McCoy, D., et al., The Venus
Express Mission, ESA Bull.,
124, 11, Nov. 2005.
Winton, A. J., et al., Venus
Express: The spacecraft, ESA
Bull., 124, 17, Nov. 2005.
by a control and data management unit. The scientific
instruments are based on instruments on Mars Express and
Rosetta. They are: the Venus Monitoring Camera, a wide angle
imager; ASPERA, a combined energetic neutral atom imager,
ion, and electron spectrometer, and magnetometer; PFS, an IR
Fourier spectrometer; SPICAV/SOIR, a UV/IR spectrometer;
VIRTIS, a UV, visible, IR imaging spectrometer; MAG, a suite
of two magnetometers, and VeRa, a radio science experiment.
Mission Profile
Venus Express launched successfully on 9 November 2005 at
03:33 UT (8 November 10:33 p.m. EST) on a Soyuz-Fregat
booster from the Baikonur Cosmodrome in Kazakhstan. The
original launch was to have taken place on 26 October 2005
but was postponed due to contamination of the launch fairing,
After launch the spacecraft went directly to a Venus transfer
trajectory. Cruise to Venus took 153 days and covered a
distance of roughly 400 million km. Arrival at Venus and orbit
insertion began on 11 April 2006 with the LSP start at 7:14:44
UT (3:14:44 EDT - Earth received time, one way transmission
time is about 7 minutes) and main engine start at 7:17:14 UT
(3:17 a.m. EST). The burn ended at 8:07:28 UT (4:07 a.m.
EDT) after imparting a delta-V of 1246.28 m/s. The initial orbit
was 400 x 350 000 km with a period of about 9 days, a
sequence of seven maneuvers culminating on 6 May on orbit
16 brought it into an elliptical 24 hour, 250 x 66000 km polar
orbit with the periapsis centered over the mid-northern
latitudes. The nominal mission starts on 4 June 2006 and will
last roughly two Venus sidereal days (486 Earth days). Total
budget for the mission is 220 million euros ($262 million U.S.
2005) of which 82.4 million euros is for satellite construction
and instrument integration and 37 million euros is for the
launch.
Final Go-Ahead Given For
Venus Express (ESA Press
Release, 6 November 2002)
Venus Express Fact Sheet
(European Space Agency)
Venus Express Design
Review (PDF file)
Venus Express Home Page
(European Space Agency)
Related
Information/Data at
NSSDC
Venus Page
Venus Express
· Nacionalidad: EUROPA
· Fecha de lanzamiento: 9 Noviembre 2.005
· Objetivo: Orbitador de Venus
Descripción:
La misión Venus Express será la primera misión de la Agencia Espacial Europea a nuestro vecino mas
cercano, el planeta Venus. Esta misión nació después de que la ESA recogiese propuestas, en marzo del
2001, sobre la posible reutilización del diseño utilizado para la sonda Mars Express, la cual actualmente
se encuentra funcionando correctamente orbitando el planeta rojo. Después de recoger gran cantidad de
propuestas, la ESA selecciono entre todas la misión Venus Express, ya que resulta especialmente
atractiva por varios motivos: la utilización del diseño de la Mars Express para la nave, el diseño de unos
instrumentos de investigación heredados y mejorados de otras misiones como Rosetta y de nuevo Mars
Express y el excitante objetivo de investigar a fondo la hostil e intrigante atmósfera venusiana.
¿Por qué Venus?:
Venus es el planeta que esta mas cerca de la tierra, incluso mas que el planeta que suele ocupar los
titulares de los periódicos, Marte. Debido a esta proximidad podemos decir que es un objetivo natural de
le exploración humana. Aunque Venus contiene las respuestas a preguntas que actualmente se hacen los
científicos ha sido dejado a parte en la exploración espacial durante esta ultima década. La siguiente
enumeración de preguntas son las que principalmente intentara resolver la Venus Express:
- ¿Cuáles son las características de la atmósfera?
- ¿Cómo circula la atmósfera?
- ¿Qué cambios se producen en la atmósfera, y como esta compuesta a distintas profundidades?
- ¿Cómo interactúa la atmósfera con la superficie de Venus?
- ¿Cómo interactúan las capas mas altas de la atmósfera venusiana con el viento solar?
El volcán Sif Mons de Venus muestra evidencias de actividad pasada en forma
de un torrente de lava solidificada que baja por el cono del volcán.
Vista 3-D creada a partir de la información del radar de una sonda Magallanes de la NASA.
Es imposible comprender la atmósfera y el clima de Venus haciendo una comparación con la tierra. Los
científicos son incapaces de explicar algunos de los extremos fenómenos atmosféricos que se producen en
aquel planeta. Por ejemplo, el planeta Venus solo rota una vez cada 243 días terrestres, sin embargo, en
las capas altas de la atmósfera los vientos huracanados dan una vuelta completa al planeta en tan solo 4
días.
La superficie de Venus también confunde a los científicos. Los cráteres mas antiguos que se aprecian en
ella solo tienen 500 millones de años de antigüedad, lo que puede indicar que este mundo trabaja como
una olla a presión. En la tierra, la constante erupción de volcanes y los terremotos aseguran que las
presiones internas del planeta se disipan de una forma gradual. Esto probablemente no ocurre en Venus.
En cambio, la presión dentro del planeta crece hasta que todo el planeta se ve envuelto en una gran
erupción a nivel global que modifica la superficie y destruye los cráteres. Esto es lo que probablemente
ocurrió hace 500 millones de años cuando se ocultaron los cráteres mas antiguos. La nave Venus Express
nos proveerá de información científica para intentar resolver estos misterios.
El Crater Golubkina en Venus tiene 34 Kilómetros de diámetro
En definitiva, los objetivos de la nave Venus Express son:
- Estudiar el plasma del entorno venusiano
- Estudiar la atmósfera venusiana
- Estudiar la superficie del planeta Venus.
Fechas principales:
- Lanzamiento: 26 de octubre de 2005. El lanzamiento se realizara desde el cosmodromo de Baikonur en
Kazajistán por un -cohete lanzador Soyuz-Fregat.
- Tiempo del viaje: 153 días
- Tiempo para entrar en orbita operacional: 5 días
- Llegada a Venus: Aprox. – Abril del 2006
- Fin de la misión: Aprox. - Agosto del 2007
El tiempo de la misión esta estimado en 2 días venusianos, es decir 500 días terrestres
La nave:
El principal factor que se tendrá en cuenta a la hora de diseñar la nave será la reutilización del, por el
momento, exitoso diseño de la Mars Express, el cual acogerá una carga útil en su interior formada en un
principio por siete instrumentos científicos. Básicamente, la Venus Express estará construida sobre una
caja de aluminio con unas medidas de 1.7m X 1.7m X 1.4m, un poco mayor que el tamaño de un
contenedor metálico de basura. La nave, con la carga útil y cargada de combustible deberá pesar 1270 Kg.
En el momento del despegue.
Instrumentos:
La carga útil de la Venus Express estará formada por una combinación de espectrómetros y cámaras, que
cubren un rango de longitudes de onda entre ultravioleta e infrarrojo, un analizador de plasma y un
magnetómetro.
La mayoría de los instrumentos son diseños reutilizados y/o recambios del hardware original de las
sondas Rosetta y Mars Express, configurados para encajar en la estructura heredada de la Mars Express y
adaptados para soportar las radiaciones y temperaturas del entorno orbital de Venus.
Los instrumentos son fruto de la colaboración entre institutos científicos de los estados miembros de la
ESA y Rusia.
· ASPERA-4:
Analizar el plasma neutro e ionizado.
Heredado de la Mars Express (ASPERA-3)
· MAG:
Mediciones del campo magnético
Heredado de la sonda Rosetta(ROMAP)
· PFS:
Sondeo vertical de la atmósfera mediante un espectroscopio Fourier de infrarrojo
Heredado de la Mars Express(PFS)
· SPICAV:
Espectrometría de la atmósfera mediante la ocultación del sol y otras estrellas
Heredado de la Mars Express(SPICAM)
· VeRa:
Sondeo de la atmósfera por radio
Heredado de la sonda Rosetta(RSI)
· VIRTIS:
Trazar un mapa de la atmósfera y la superficie por medio de medidas espectrometricas
Heredado de la sonda Rosetta(VIRTIS)
· VMC:
Recolección de imágenes de espectro visible y ultravioleta.
Heredado de la Mars Express(HRSC/SRC) y Rosetta(OSIRIS)
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
XM 3
Publications
NSSDC ID: 2005-008A
Maps
New/Updated Data
Alternate Names
Description
XM 3 is an American geostationary radio communications
satellite that was launched by a Zenit-3SL rocket from the
floating Odyssey platform on the equatorial Pacific Ocean (at
154 deg-W longitude) at 03:51 UT on 1 March 2005. The 4.7
tonne satellite will provide music, sports, and news radio
through 130 channels to the numerous subscribers with
specially equipped receivers in their automobiles, after parking
over 85 deg-W longitude.
28626
Facts in Brief
3SL
Funding Agency
Discipline
Communications
Additional
Information
Launch/Orbital
information for XM 3
Experiments on XM 3
Data collections from XM 3
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
XSS-11
Publications
NSSDC ID: 2005-011A
Maps
New/Updated Data
Alternate Names
Description
XSS-11 (eXperimental Satellite System 11) is an American
military (AFRL) microsatellite that was launched by a Minotaur
rocket, a modified Minuteman 2 ICBM, from Vandenberg AFB
at 13:35 UT on 11 April 2005. The 100 kg satellite is equipped
with sensors to seek out and make close rendezvous with
several rocket bodies and dead spacecraft that are still in orbit.
It will approach each such object as closely as 2.5 km to
examine and image it, making sure that it will never collide. It
will be under the control of ground crews, except when it can
be confidently allowed to move autonomously. The rendezvous
exercise with the several objects will continue during the
mission life of 12 to 18 months. This experimental model
carries no projectiles.
eXperimental Satellite
System 11
28636
Facts in Brief
Launch
Vehicle: Minotaur
Launch
United States
Funding Agency
Discipline
Military
Additional
Information
Launch/Orbital
information for XSS-11
Experiments on XSS-11
Data collections from XSS11
Office.
NSSDC Master
Catalog Search
Spacecraft
Experiments
Data Collections
Personnel
XTAR-EUR
Publications
NSSDC ID: 2005-005A
Maps
New/Updated Data
Alternate Names
Description
XTAR-EUR is a Spanish geostationary military satellite that
was launched by an Ariane 5-ECA rocket from Kourou at 21:03
UT on 12 February 2005. The 3.6 tonne satellite will provide
military communications for Spain and United States through
its 12 wideband, X-band transponders after parking over an
as-yet-undetermined spot over the Atlantic or Indian Ocean
28542
Facts in Brief
5 ECA
French Guiana
Funding Agency
Unknown (Spain)
Disciplines
Communications
Military
Additional
Information
Launch/Orbital
information for XTAREUR
Experiments on XTAREUR
XTAR-EUR
Office.

NASA - NSSDC - Master Catalog

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