NationStates Jolt Archive

Navigation:

GPS3
http://img78.photobucket.com/albums/v245/vetobob/gps3.jpg
have the capabilities to autonomously navigate (AUTONAV) themselves and generate their own 50 Hz navigation message data
11,000-mile circular orbits. While orbiting the earth, the systems transmit signals on two different L-band frequencies. Their design life is six years.
ability to determine its own position by performing inter-satellite ranging with other space vehicles
features reprogrammable processors that enable problem fixes, upgrades in flight, and increased satellite autonomy and radiation hardness.
requires fewer ground contacts to maintain the constellation
Weight: 1,860 pounds (in orbit)
Orbit altitude: 10,900 miles
Power plant: Solar panels generating 700 watts
2 NiH batteries
Dimension: 5 feet wide, 17.5 feet long (length includes wingspan)
Launch vehicle: Delta II
Primary contractor: Lockheed-Martin - Block IIR
PAYLOAD additional radiation hardening
cross link ranging
reprogrammable micro-processor
two atomic clocks on at all times (hot backup)
600 million

weather:
Gaia2
http://img78.photobucket.com/albums/v245/vetobob/gaia2.jpg
Operational Linescan System which provides continuous visual and infrared imagery of cloud cover over a swath 1,800 miles wide. Additional satellite sensors measure atmospheric vertical profiles of moisture and temperature.
monitor and predict regional and global weather patterns; including the presence of severe thunderstorms, hurricanes, and typhoons.
also measure local charged particles and electromagnetic fields to assess the impact of the ionosphere on ballistic-missile early warning radar systems and long-range communications. Additionally, these data are used to monitor global auroral activity and to predict the effects of the space environment on military satellite operations.
200 million

Remote Sensing:

FY-1
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137 MHz band
powered by two solar arrays (about 3.5 m long each) with a combined rating of more than 800 W. Nickel-cadmium batteries were used for electrical power storage. Attitude control was maintained by a combination of nitrogen cold gas thrusters and reaction wheels, although both spacecraft suffered serious malfunctions in this system
Very High Resolution Scanning Radiometers (VHRSR) with a combined mass of 95 kg. These optical-mechanical scanners operated at 360 rpm with a 20-cm diameter primary mirror. The five spectral bands used were 0.58-0.68 µm, 0.725-1.1 µm, 0.48-0.53 µm, 0.53-0.58 µm, and 10.5-12.5 µm. The system swath was 2,860 km with a 1.08-km resolution in the High Resolution Picture Transmission (HRPT) mode and 4-km resolution in the Automatic Picture Transmission (APT) mode.
20 billion

ROCSAT-2
http://img78.photobucket.com/albums/v245/vetobob/rocsat2.jpg
designed to perform near realtime remote sensing of the ocean and landmass
data from the ROCSAT-2 can be applied towards land use, agriculture and forestry, natural disaster evaluation, environmental monitoring, education, and foster international cooperation in various scientific researches. In addition to the remote sensing mission, the scientific mission of investigating the upper atmospheric lighting phenomena is included
Satellite Orbital Characteristics:

1. sun-synchronous orbit with satellite altitude = 891 km
2. inclination 98.99
3. orbit adjustment: after drifting 400 km from assigned orbit (about every 6 months)
# life span 5 years (over 70% reliability)
# figure of satellite tracks
Sensors:

1. Pan Chromatic pushbroom CCD:¡@ 60 km swath with 2m - 5m resolution
2. MSS at 15 m resolution
3. stereo capability

Data and coverage:

1. swath¡@ 60 km,¡@ maximal nadir angle = 30-degrees
2. downlink with X-band 50 Mbps ~ 100 Mbps, spot beam antenna
3. on-board recorder¡@ 10 Gb, plus spare
25 billion



ADEOS
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Advanced Earth Observation Satellite
polar orbiting
perform Earth, atmospheric, and oceanographic remote sensing.
3-Axis stabilized, zero momentum biased control system with 0.3 deg control and 0.003 deg/sec stability using reaction wheels. Single solar array generates 4.5 kW for a 34 to 52 volt floating bus with 5x35 AHr NiCd batteries. Hydrazine propulsion system (135 kg fuel) for orbit maintenance. S-Band TT&C (S-Band, Uplink: 500 bps, Downlink: 4 Mbps). Ka-Band data crosslink at 120 Mbps to COMETS. X-Band direct downlink (40W and 8W, QPSK). System reliability is 0.7 at 3 years.
Payload
ADEOS-1 Payload Description: AVNIR (Advanced Visible and Near-Infrared Radiometer): five visible/near-infrared bands (0.42 to 0.89 µm); 16- or 8-m resolution; 80 km swath; +/- 40 deg cross-track pointing; stereo capability (from NASDA). ILAS (Infrared Limb Atmospheric Spectrometer): infrared occultation device (from Japan's Environmental Agency). IMG: nadir-looking Fourier transform infrared spectrometer (from MITI). NSCAT: active Ku-band scatterometer (from NASA). OCTS: Ocean Color Temperature Scanner (from NASDA). POLDER: (from CNES). RIS: (from Japan's Environmental agency). TOMS: Total Ozone Mapping Spectrometer (from NASA). ADEOS-2 Payload Description: AMSR (Advanced Microwave Scanning Radiometer), GLI (Global Imager), Sea Winds, POLDER (Polarization and Directionality of the Earth's Reflectances), ILAS-II (Improved Limb Atmospheric Spectrometer-II)
Size 4 x 4 x 5 m bus with 3 x 26 m solar array
Orbit LEO, 797 km, sun-synchronous polar with 10:30 equatorial crossing, with a 41 day repeating ground track. (98.6 deg inclination). ADEOS-2 will have a 4 day repeat orbit.
Design Life 3 years
ADvanced Earth Observation Satellite; ocean wind and temperature monitoring, atmospheric gas monitoring
320 billion

Space Probes:

Magellan
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used to study asteroids up close
help answer fundamental questions about the nature and origin of near-Earth objects, as well as provide clues about the how Earth itself was formed
designed to rendevous with a chosen asteroid
perform up-close observations for about one year. The primary scientific goals are to measure the asteroid's: (1) bulk properties (size, shape, volume, mass, gravity field, and spin state); (2) surface properties (elemental and mineral composition, geology, morphology, and texture); and (3) internal properties (mass distribution and magnetic field).
Spacecraft
3-axis stabilized. 4 deployed, non-articulating fixed solar panels provide 1600 watts at 1 AU. Fixed 1.5 m diameter high gain antenna. X-band communications using via DSN with selectable data rates between 1 and 27 kbps. Passive thermal control. 1 Gbit solid state data storage. Hydrazine propulsion system with one 100 lbf, four 5 lbf, and seven 1 lbf thrusters provide a total delta-V of 1425 m/s. Mission control provided by JHU APL with navigation support from JPL.
Payload
The instrument payload totals 55 kg and 48 watts. MultiSpectral Imager (MSI) - a refractive telescope with passively cooled Si CCD array (244 x 537) that will determine the overall size, shape, and spin characteristics of the asteroid, map the morphology and composition of the surface, and search for satellites of Eros. 2.25 x 2.9 deg FOV, 10-16 meter resolution from 100 km altitude, sensitive between 400 and 1100 nm. X-Ray/Gamma-Ray Spectrometer (XGRS) - containing two sensors (an X-ray fluorescence spectrometer and a gamma-ray spectrometer), XGRS will be used to determining the surface/near-surface elemental composition of the asteroid. Near-Infrared Spectrograph (NIS) - a spectrometer covering 800-2700 nm, NIS is designed to map the mineralogic composition of the asteroid. Magnetometer - a three-axis fluxgate sensor that will be used to measure the asteroid's magnetic field. These measurements will help determine the internal composition of the asteroid. NEAR Laser Rangefinder (NLR) - an altimeter that uses a solid-state pulsed laser to measure the distance between the spacecraft and the surface of the asteroid. It will be used to make will make accurate measurements of the asteroid's shape and detailed surface structure. Nd-YAG laser operating at 1.064 mm wavelength, 6 meter resolution, 50 km range. Radio Science - uses the satellite's telemetry system to map the asteroid's gravity field.
Size 1.7 x 1.7 x 2.75 meter
Orbit Variable, ranging from 1000 x 1000 km to 35 x 35 km
Design Life 4 years
400 billion

The Mercury Probe:

Axis
http://img78.photobucket.com/albums/v245/vetobob/Axis.gif
Spacecraft
Octagonal structure of magnesium and aluminum. 3-axis stabilized using cold gas thrusters. Solar panels produce 540 W max. NiCd batteries (20 AHr). Communications using S-Band and X-Band.
Payload
Cameras, magnetometer, plasma science experiment, charged particle telescope, ultraviolet spectrometer, and infrared radiometer.
Can be used to study Mercury
100 million


Sun Probe:
Aolia
http://img78.photobucket.com/albums/v245/vetobob/Aolia.gif
Spacecraft
3-axis stabilized using cold gas thrusters. Four deployed solar panels were kept oriented toward the Sun. S-Band communications using LGA or HGA.

Payload
Magnetometer, charged particle sensors, cosmic-ray telescope, television camera. Tape recorder stored 21 pictures.
takes video of planet being studied
used for studying the sun
100 million

Probe to the planet Sedna:
Shegon
http://img78.photobucket.com/albums/v245/vetobob/Shegon.gif
Spacecraft
Octagonal bus structure with four solar panels. 3-axis stabilized using cold gas thrusters. S-Band communications via LGA and HGA. Thermal shield.
Payload
Instruments examine planets atmosphere with radio waves and ultraviolet scanners and sampled the solar particles and magnetic fields in the region of the planet.
100 million


Probe to Pluto:
Shintaka
http://img78.photobucket.com/albums/v245/vetobob/Shintaka.gif
Spacecraft
The eight sided magnesium structure contained seven electronics compartments. One small hydrazine rocket engine used for trajectory corrections. Solar panels generated 830 W maximum (450 watts at Mars). AgZn batteries. Dual S-Band transmitters provided telemetry at 8.33 and 16200 bps. 3-axis stabilized to 0.05 deg using 12 cold gas jets. 157 Mbits data storage.
Payload
The planetary experiments (59 kg) includes two television cameras, an infrared radiometer, an infrared spectrometer, and an ultraviolet spectrometer. These sensors takes color TV pictures of planet and measures the ratio of refractivity and UV and IR emissions of the atmosphere.
also study the planet's atmosphere and profiled its chemical composition
74 million (really cheap)

Nuclear Missile Launch Detector: (detects nuclear launches anywhere in the world)

Missile Launch Detector:

DSP
http://img78.photobucket.com/albums/v245/vetobob/dsp.gif
180M per spacecraft.
Spacecraft
Spacecraft spin slowly (6 rpm) about the nadir axis to permit scanning of the Earth by the detector system. Zero momentum stabilized using a reaction wheel to counter the spacecraft spin. Four solar panels deploy to generate roughly 1300 W. Radiation hardened.

Payload
Payload classified, but thought to include telescope with 6000 element IR array, nuclear explosion detectors, particle detection monitors.
Size 33 ft long, 14 ft diameter
Orbit Geosynchronous
Design Life 7 to 9 years
early warning system for the detection of long range ballistic missile launches and nuclear detonations

Pollution Monitoring:
Clark
http://img78.photobucket.com/albums/v245/vetobob/clark.gif
Spacecraft
3-Axis stabilized, zero momentum biased control system with 0.05 deg control and 0.03 deg knowledge. Two solar arrays generate 289W orbit average power. Two 15-Ahr NiH2 CPV batteries. Hydrazine propulsion system with 12.5 kg propellant. 2 Gbit solid state storage. UHF command and telemetry links. 25 Mbps X-band image data downlink. Graphite composite structure.

Payload
Worldview Imaging Corp's panchromatic 3-m resolution, 15-m multispectral resolution with cloud editing capability. Micro-Measuring Air Pollution from Satellites (µMAPS). X-Ray Spectrometer (soft and gamma). Atmospheric Tomography (3D pollution mapping).
Size 36.5 in. hex by 69.5 in
Orbit 475 km, circular, polar, sun synchronous i=97.3 deg
Design Life 3 years (required life is 1 year)
$60 million

Lewis
http://img78.photobucket.com/albums/v245/vetobob/lewis.gif
Spacecraft
3-Axis stabilized, zero momentum biased control system with 0.004 deg knowledge. Single solar array generates 600W power at 1 year. Hydrazine propulsion system with eight 1-lbf thrusters. System reliability is 0.86 at 5 years.
Data archive accessible on Internet, T1 line
Payload
Earth imaging Hyperspectral Imager (HSI) with 384 bands (0.4 - 2.5 µm, 30 m pixels, 7.7 km swath, panchromatic: 0.45 - 0.75 µm, 5 m pixels, 13 km swath). Linear Etalon Imaging Spectral Array (LEISA), from NASA GSFC (1.0 - 2.5 µm, 256 channels, 300 m pixels, 77 km swath). Ultraviolet Cosmic Background (UCB), from UC Berkely (35 - 85 nm). In addition to the above instruments, several spacecraft systems technologies will be flown. A partial list of planned technology demonstrations is: pulse tube cryocooler, solid state recorder, fiber optic data bus, GPS attitude determination, wide FOV star tracker, magnetically suspended reaction wheel, lightweight structure with integrated thermal control, GFRP overwrapped propellant tank.
Size 36.5 in. hex by 69.5 in
Orbit 523 km, circular, sun synchronous
Design Life 3 years (required life is 1 year)
60 million

Whittier military Sats:

DSCS II
Defense Satellite Communications System II
http://img78.photobucket.com/albums/v245/vetobob/dscs2.gif
DSCS provides secure voice and data communications for the military
Spacecraft
Spin stabilized with a despun antenna platform. Body mounted solar cells produced 535 watts. Three NiCd batteries provide 36 AHr total. Hydrazine propulsion system.

Payload
Two 20 watt X-Band transponders with 500 MHz bandwidths. Steerable narrow beam antennas and drive mechanism for communications privacy. Capacity is 1300 voice channels or 100 Mbps of data. Compatible with ground-portable units.
Size Cylinder 3 m dia., 4 m high
Orbit Geosynchronous
Design Life 5 years
5 million

FLTSATCOM
Fleet Satellite Communications
http://img78.photobucket.com/albums/v245/vetobob/fltsatcom.gif
Spacecraft
3-Axis stabilized. Two solar arrays (13.2 m across) generate >1400 W. Three hexagonal modules with aluminum structure. Hydrazine propulsion system for stationkeeping (120 kg fuel).

Payload
Twelve transponders with UHF/SHF uplink and UHF downlink. Large 4.9 meter diameter UHF receive antenna of silver-filled mesh. Offset mast UHF transmit antenna. Flights 6 and 7 carried experimental EHF transponder (20 W) to evaluate new ground terminals.
Size 2.5 m dia. x 1.3 m high
Orbit Geosynchronous
Design Life 7 years
100 million

Whittier SDI defense sats: (Part of the Pandora's Box system)

Warhawk
http://img78.photobucket.com/albums/v245/vetobob/warhawk.gif
identify and track ballistic missiles during flight
In addition, it will perform scientific investigations of the composition and dynamics of the Earth's atmosphere by observing ozone, chloroflourocarbons, carbon dioxide and methane.
Spacecraft
3-axis stabilized to 0.01 deg using reaction wheels with knowledge to 9 µ rad (post-processed). 108 Gbits data storage. Steerable X-band antennas with 2 kbps uplink and downlink up to 25 Mbps. Dual solar arrays (single-axis articulation) provide 1200 W BOL. NiH2 batteries.

Payload
The instruments consist of 11 optical sensors making observations at a wide range of infrared, visible and ultraviolet wavelengths from 110 nm to 28 µ m. Primary instruments: SPIRIT III (Space Infrared Imaging Telescope), UVISI (Ultraviolet and Visible Imagers and Spectrographic Imagers), SBV (Space-Based Visible instrument), OSDP (On-board Signal and Data Processor), and reference objects (2 cm spheres to be deployed from MSX).
Size 1.5 x 1.5 x 5.1 meters
Orbit 900 km, high inclination, circular, near-sun-synchronous
Design Life 4 years (with 18-20 months of coolant for IR sensors), 5 year goal
$320 million


Vigilence
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24-inch mirror deflects ground based lasers back to target points on earth.
Payload
The precision relay mirror was 24 in. (61 cm) and had a pointing accuracy of 0.2 arcsec. (at least one foruth of a city block)

Orbit 457x478 km, include.=43.1 deg
Design Life 6 months
120 million


HLS
HotLine Sattelite
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Emergency Communications Sattalite
Allows emergency communications between the leaders on of various nations in times of international crises, to facilitate bilateral talks between heated adversaries with the purpose of completing peace talks from bunkers and and other safe zones.
Communication through the sat. takes place as if the participants are in the same room.
Can be used only by national leaders.
900 billion


Navajo
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military communications sattalite
encodes and encrypts military comms. which must be uncoded and unencrypted at the target point with a specially made instrument.
Top Secret.
500 billion

And finally, the probe to Alpha Centauri:

Dagos 1.
Interplanetary Probe
http://img78.photobucket.com/albums/v245/vetobob/Dagos_1.gif
Used to study interstellar space.
5 million

These are not for sale.

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