Whittier--
30-07-2005, 20:19
This information is secret IC so your nations cannot and will not know the make up of the Pandora's Box sattelite system.
I've seen too many people grabbing my stuff. PB being one thing that has been appropriated by a certain person in past posts.
As you will see, the costs of Pandora's Box runs into the high trillions.
Pandora's Box is composed of a constellation of Sattelites that surrounds the earth.
Ground Operation Station:
Number: 100
Capricorn
Type of Service............... 500000KF9W (multilink, multivoice, and data)
Frequency Range:
Transmit............... 7.9 to 8.4 GHz
Receive............... 7.25 to 7.75 GHz
Planning Range............... 16,093 km (10,000 mi)
Power Input............... 115/230 V AC, 50 to 60 Hz
Power Source............... Any appropriate AC power source
Power Output............... Up to 20 kW
Antenna............... System Paraboloid surface, 18.29 m (60 ft) in diameter, weight 172.3 MT (190 t)
Cost: 125 billion each
50 FSC-78's
a fixed SHF SATCOM heavy SGT operating in the X-band frequency range
11.6 m (38 ft) diameter, DE-222/G, parabolic dish
The terminal is composed of six subsystems, including antenna tracking, transmitter, receiver, frequency reference, control, and monitoring. The antenna is a 60- foot diameter, high-efficiency, parabolic reflector providing an antenna gain-to-noise temperature ratio (G/ T) of 39 dB/ K. The reflector is mounted on an elevation-over-azimuth-configured pedestal. Cryogenically cooled, parametric amplifiers provide 30 dB of gain and an antenna G/ T ratio of 39 dB/ K. The antenna terminal equipment has a tracking converter, 15 down-converters, and 9 up-converters. Only 10 of the down-converters are normally active at one time; the remaining 5 are in hot standby. The output signals from the up-converters are fed to a 5-kW TWTA, providing a radiated antenna signal of 500-MHz bandwidth at an EIRP of 124 dB referenced to one watt (dBW). A redundant 5 kW power amplifier can be operated in parallel with the primary power amplifier to provide an output equivalent to 10 kW at an EIRP of 127 dBW. The down-converters translate the receive signal of 7.25 to 7.75 GHz to 70-MHz IF (40-MHz bandwidth) or a 700-MHz IF (125-MHz bandwidth). The up-converters translate the 70 or 700-MHz IF input signal, with bandwidths of 40 or 125 MHz, to the transmit frequency of 7.9 to 8.4 GHz. The Army Heavy Terminal/ Medium Terminal (HT/ MT) modernization of the AN/ FSC-78/ 79 and AN/ GSC-39 Earth terminal will increase the total number of the uplink and downlink converters.
Cost: 125 billion each
500 STAR-T Mobile Ground Stations
SHF Tri-Band Advanced Range Extension Tactical Terminal
HMMWV mounted multichannel satellite terminal. It has a tri-band capability in the SHF range. The STAR-T terminal will operate over commercial and military SHF systems and will interface with both commercial and military switching systems. It will provide the required range extension for TRI-TAC systems at EAC and non-terrestrial communications connectivity between EAC and ECB.
operate over military and commercial SHF satellites and will provide range extension for both commercial and military switching systems. The terminal will provide data, imagery, and voice communications at various data rates up to total aggregate data rate of 8.192 Mb/s
Frequency Range:
3.9 GHz-6.2 GHz (C Band)
6.2 GHz-10.9 GHz (X Band)
15.25 GHz-17.25 GHz (Ku BAND)
Characteristics:
Four T-1 (1.54 Mb/s) circuits or four E-1 (2.048 Mb/s)
Circuits for a total aggregate of 8.192 M/bs
STAR-T will provide communications connectivity for split based operations between the theater and the sustaining base. DSCS SHF satellites will be used as much as possible to provide anti-jam protected links for all users. If current and future DSCS satellites cannot provide the total required throughput, then selected links will use commercial satellites to satisfy the requirement.
Cost 175 BILLIOn each
Tracking Satellites
20 ATDRS
Advanced Tracking and Data Relay Satellite
provide communications coverage to satellites and manned vehicles in low Earth orbit.
Ku-Band communications services as the original TDRS vehicles, and will also add Ka-band links
Spacecraft
Based on Hughes HS-601 series bus, with modifications to meet NASA requirements. Upgraded attitude control system, telemetry and command system based on other government satellite systems. Deployable solar arrays provide 2040 W EOL.
Payload
Two Single Access (SA) antennas - each antenna is a lightweight 4.5 m steerable dish incorporating new springback reflector technology. Each dish can have simultaneous S/Ku- or S/Ka-band communications with a single user spacecraft. Maximum receive data rates through these antennas are 300 Mbps for Ku and Ka bands and 6 Mbps for S-band. Transmit data rates are 25 Mbps for Ku/Ka and 300 kbps for S-band. One Multiple Access (MA) S-band receive array - an electronically steerable phased array antenna consisting of patch antennas. The MA array can receive data from up to 5 user satellites simultaneously, with each link supporting up to 3 Mbps. One S-band transmit array - an electronically steerable phased array antenna consisting of patch antennas. This array can transmit data to a single user satellite at a rate of 300 kbps. One Space to Ground Link antenna (SGL) - a parabolic antenna operating at Ku-band that provides the communications link between the satellite and the ground. All customer data is sent through this dish, as are all regular TDRS command and telemetry signals. The antenna is gimballed on two axes.
Size 21 m x 14 m (deployed)
Must be launched on an atlas rocket
Orbit Geosynchronous
Design Life 15 years
Cost: $486.1M each
Intelligence Sattelites
10 Sirius sats
photographic intelligence satellite
perational life of about three years, would be in orbit at all times
sun-synchronous orbits, which repeat their ground tracks at four day intervals, and are synchronized to provide two day overlaps in coverage.
$450 billion
5 E-300 Enhanced Collection System
very large, Lightweight optics
large version of Sirius
$300 billion
Geo sattelites
LandSat 45
10 sats
Structure of aluminum with graphite struts. Hydrazine propulsion system. Single solar array with 1-axis articulation produces 1430 W (BOL), Two NiCd batteries provide 100 AHr total. Retractable boom (4 m long) with 2 powered joints supports the articulated HGA which downlinks data via TDRSS. Communications system uses S, X, L, and Ku-Bands. 3-axis stabilized, zero momentum with control to 0.01 deg using reaction wheels.
Payload
Carried Multi-Spectral Scanner (MSS) and Thematic Mapper ™ imaging sensors. TM provides 7 bands of coverage and the MSS has 4 bands. The MSS covers 0.5 to 12.6 µ m and provides 80 m resolution with a 185 km swath width. TM covers 0.45 to 12.5 µ m with resolution of 30 meters in the VIS/IR bands and 120 m in the thermal/IR bands.
size 4.3 m high, 2.2 wide (with HGA and array deployed)
Orbit 705 km circular, polar, sun-synchronous, repeating every 16 days (9:45 am crossing time)
Design Life 5 years
$5 billion each
Remote Sensors:
12 FY-1's
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 is 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 operates at 360 rpm with a 20-cm diameter primary mirror. The five spectral bands used are 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 is 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 each
10 Haiyang-1's
340kg and have two solar panels
equiped with a 10-band IR ocean color scanner and a 4-band CCD camera.
$20 billion each
10 Zi Yuan 2's
4-channel CCD sensors capable of 400-km swath widths and 100-m ground resolution.
cooled, multi-channel infrared camera system with a mass of 40-50 kg
$20 billion each
Missile Launch Detectors:
10 DSPs
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
SDI Sats:
20 Warhawks
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 each
5 Vigilence sats
24-inch mirror deflects ground based lasers back to target points on earth.
Payload
The precision relay mirror was 24 in. (61 cm) and has 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
10 Pandora's Box Missile Sats
Space based nuclear missile silo.
Holds up to 50 nuclear missiles.
contains infrared and optical scanners to monitor all surrounding space
Laser Cannon W34 (anti sat/anti missile laser). This was a recent upgrade from the Q22 anti missile laser sytem and the T 2 anti sat laser system.
The W34 auto detects threats to the Pandora's Box missile silo and responds with destructive force destroying the source of the threat. Pandora's Box sats have emp shielding added to them before they are launched to protect against electromagnetic radiation.
$500 billion each
Pandora's Box Missile Silo is copyrighted January 2003 by Whittier and its subsequent incarnations: Whittier- and Whittier--.
The Pandora's Box system is copyrighted January 2003 by Whittier and its subsequent incarnations: Whittier- and Whittier--.
Though all missiles launched against Pandora's Box are destroyed less than a minute after impact, the anti sat system is imperfect and PB and may be vulnerable to blindside laser attack (can't be made invulnerable without becoming future tech, actually no sat is immune to blindside laser attacks from space, or close range missile attacks.) Well CRMA's depend on how close you are when you launch them.
There is no way any other nation out there could hope to field such a system. The only reason Whittier has it, it because Whittier-- inherited it from the original Whittier. The total system cost is over $100 trillion not including fuel costs, and launch costs, and the cost of launching and maintenance missions.
Pandora's Box was built up over time, not built in a day. Pandora's Box was built up in 2003, before any of the 2004 nations even existed and construction was started before a great many 2003 nations. PB's first component was first deployed in Jan of 03. Pandora's Box is patented technology so that no one can build it without violating the copyright. Unless I grant permission of course.
There are no space stations in the Pandora's Box constellation. Pandora's Box is no match for future tech devices, or even space fighters for that matter (not designed for it.)
But as I have noted Pandora's Box is copyrighted so please do not copy it. If you want your own system, I can help you if you ask. Not that I have to worry about the older nations but some of the new ones on the other hand.
I've seen too many people grabbing my stuff. PB being one thing that has been appropriated by a certain person in past posts.
As you will see, the costs of Pandora's Box runs into the high trillions.
Pandora's Box is composed of a constellation of Sattelites that surrounds the earth.
Ground Operation Station:
Number: 100
Capricorn
Type of Service............... 500000KF9W (multilink, multivoice, and data)
Frequency Range:
Transmit............... 7.9 to 8.4 GHz
Receive............... 7.25 to 7.75 GHz
Planning Range............... 16,093 km (10,000 mi)
Power Input............... 115/230 V AC, 50 to 60 Hz
Power Source............... Any appropriate AC power source
Power Output............... Up to 20 kW
Antenna............... System Paraboloid surface, 18.29 m (60 ft) in diameter, weight 172.3 MT (190 t)
Cost: 125 billion each
50 FSC-78's
a fixed SHF SATCOM heavy SGT operating in the X-band frequency range
11.6 m (38 ft) diameter, DE-222/G, parabolic dish
The terminal is composed of six subsystems, including antenna tracking, transmitter, receiver, frequency reference, control, and monitoring. The antenna is a 60- foot diameter, high-efficiency, parabolic reflector providing an antenna gain-to-noise temperature ratio (G/ T) of 39 dB/ K. The reflector is mounted on an elevation-over-azimuth-configured pedestal. Cryogenically cooled, parametric amplifiers provide 30 dB of gain and an antenna G/ T ratio of 39 dB/ K. The antenna terminal equipment has a tracking converter, 15 down-converters, and 9 up-converters. Only 10 of the down-converters are normally active at one time; the remaining 5 are in hot standby. The output signals from the up-converters are fed to a 5-kW TWTA, providing a radiated antenna signal of 500-MHz bandwidth at an EIRP of 124 dB referenced to one watt (dBW). A redundant 5 kW power amplifier can be operated in parallel with the primary power amplifier to provide an output equivalent to 10 kW at an EIRP of 127 dBW. The down-converters translate the receive signal of 7.25 to 7.75 GHz to 70-MHz IF (40-MHz bandwidth) or a 700-MHz IF (125-MHz bandwidth). The up-converters translate the 70 or 700-MHz IF input signal, with bandwidths of 40 or 125 MHz, to the transmit frequency of 7.9 to 8.4 GHz. The Army Heavy Terminal/ Medium Terminal (HT/ MT) modernization of the AN/ FSC-78/ 79 and AN/ GSC-39 Earth terminal will increase the total number of the uplink and downlink converters.
Cost: 125 billion each
500 STAR-T Mobile Ground Stations
SHF Tri-Band Advanced Range Extension Tactical Terminal
HMMWV mounted multichannel satellite terminal. It has a tri-band capability in the SHF range. The STAR-T terminal will operate over commercial and military SHF systems and will interface with both commercial and military switching systems. It will provide the required range extension for TRI-TAC systems at EAC and non-terrestrial communications connectivity between EAC and ECB.
operate over military and commercial SHF satellites and will provide range extension for both commercial and military switching systems. The terminal will provide data, imagery, and voice communications at various data rates up to total aggregate data rate of 8.192 Mb/s
Frequency Range:
3.9 GHz-6.2 GHz (C Band)
6.2 GHz-10.9 GHz (X Band)
15.25 GHz-17.25 GHz (Ku BAND)
Characteristics:
Four T-1 (1.54 Mb/s) circuits or four E-1 (2.048 Mb/s)
Circuits for a total aggregate of 8.192 M/bs
STAR-T will provide communications connectivity for split based operations between the theater and the sustaining base. DSCS SHF satellites will be used as much as possible to provide anti-jam protected links for all users. If current and future DSCS satellites cannot provide the total required throughput, then selected links will use commercial satellites to satisfy the requirement.
Cost 175 BILLIOn each
Tracking Satellites
20 ATDRS
Advanced Tracking and Data Relay Satellite
provide communications coverage to satellites and manned vehicles in low Earth orbit.
Ku-Band communications services as the original TDRS vehicles, and will also add Ka-band links
Spacecraft
Based on Hughes HS-601 series bus, with modifications to meet NASA requirements. Upgraded attitude control system, telemetry and command system based on other government satellite systems. Deployable solar arrays provide 2040 W EOL.
Payload
Two Single Access (SA) antennas - each antenna is a lightweight 4.5 m steerable dish incorporating new springback reflector technology. Each dish can have simultaneous S/Ku- or S/Ka-band communications with a single user spacecraft. Maximum receive data rates through these antennas are 300 Mbps for Ku and Ka bands and 6 Mbps for S-band. Transmit data rates are 25 Mbps for Ku/Ka and 300 kbps for S-band. One Multiple Access (MA) S-band receive array - an electronically steerable phased array antenna consisting of patch antennas. The MA array can receive data from up to 5 user satellites simultaneously, with each link supporting up to 3 Mbps. One S-band transmit array - an electronically steerable phased array antenna consisting of patch antennas. This array can transmit data to a single user satellite at a rate of 300 kbps. One Space to Ground Link antenna (SGL) - a parabolic antenna operating at Ku-band that provides the communications link between the satellite and the ground. All customer data is sent through this dish, as are all regular TDRS command and telemetry signals. The antenna is gimballed on two axes.
Size 21 m x 14 m (deployed)
Must be launched on an atlas rocket
Orbit Geosynchronous
Design Life 15 years
Cost: $486.1M each
Intelligence Sattelites
10 Sirius sats
photographic intelligence satellite
perational life of about three years, would be in orbit at all times
sun-synchronous orbits, which repeat their ground tracks at four day intervals, and are synchronized to provide two day overlaps in coverage.
$450 billion
5 E-300 Enhanced Collection System
very large, Lightweight optics
large version of Sirius
$300 billion
Geo sattelites
LandSat 45
10 sats
Structure of aluminum with graphite struts. Hydrazine propulsion system. Single solar array with 1-axis articulation produces 1430 W (BOL), Two NiCd batteries provide 100 AHr total. Retractable boom (4 m long) with 2 powered joints supports the articulated HGA which downlinks data via TDRSS. Communications system uses S, X, L, and Ku-Bands. 3-axis stabilized, zero momentum with control to 0.01 deg using reaction wheels.
Payload
Carried Multi-Spectral Scanner (MSS) and Thematic Mapper ™ imaging sensors. TM provides 7 bands of coverage and the MSS has 4 bands. The MSS covers 0.5 to 12.6 µ m and provides 80 m resolution with a 185 km swath width. TM covers 0.45 to 12.5 µ m with resolution of 30 meters in the VIS/IR bands and 120 m in the thermal/IR bands.
size 4.3 m high, 2.2 wide (with HGA and array deployed)
Orbit 705 km circular, polar, sun-synchronous, repeating every 16 days (9:45 am crossing time)
Design Life 5 years
$5 billion each
Remote Sensors:
12 FY-1's
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 is 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 operates at 360 rpm with a 20-cm diameter primary mirror. The five spectral bands used are 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 is 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 each
10 Haiyang-1's
340kg and have two solar panels
equiped with a 10-band IR ocean color scanner and a 4-band CCD camera.
$20 billion each
10 Zi Yuan 2's
4-channel CCD sensors capable of 400-km swath widths and 100-m ground resolution.
cooled, multi-channel infrared camera system with a mass of 40-50 kg
$20 billion each
Missile Launch Detectors:
10 DSPs
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
SDI Sats:
20 Warhawks
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 each
5 Vigilence sats
24-inch mirror deflects ground based lasers back to target points on earth.
Payload
The precision relay mirror was 24 in. (61 cm) and has 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
10 Pandora's Box Missile Sats
Space based nuclear missile silo.
Holds up to 50 nuclear missiles.
contains infrared and optical scanners to monitor all surrounding space
Laser Cannon W34 (anti sat/anti missile laser). This was a recent upgrade from the Q22 anti missile laser sytem and the T 2 anti sat laser system.
The W34 auto detects threats to the Pandora's Box missile silo and responds with destructive force destroying the source of the threat. Pandora's Box sats have emp shielding added to them before they are launched to protect against electromagnetic radiation.
$500 billion each
Pandora's Box Missile Silo is copyrighted January 2003 by Whittier and its subsequent incarnations: Whittier- and Whittier--.
The Pandora's Box system is copyrighted January 2003 by Whittier and its subsequent incarnations: Whittier- and Whittier--.
Though all missiles launched against Pandora's Box are destroyed less than a minute after impact, the anti sat system is imperfect and PB and may be vulnerable to blindside laser attack (can't be made invulnerable without becoming future tech, actually no sat is immune to blindside laser attacks from space, or close range missile attacks.) Well CRMA's depend on how close you are when you launch them.
There is no way any other nation out there could hope to field such a system. The only reason Whittier has it, it because Whittier-- inherited it from the original Whittier. The total system cost is over $100 trillion not including fuel costs, and launch costs, and the cost of launching and maintenance missions.
Pandora's Box was built up over time, not built in a day. Pandora's Box was built up in 2003, before any of the 2004 nations even existed and construction was started before a great many 2003 nations. PB's first component was first deployed in Jan of 03. Pandora's Box is patented technology so that no one can build it without violating the copyright. Unless I grant permission of course.
There are no space stations in the Pandora's Box constellation. Pandora's Box is no match for future tech devices, or even space fighters for that matter (not designed for it.)
But as I have noted Pandora's Box is copyrighted so please do not copy it. If you want your own system, I can help you if you ask. Not that I have to worry about the older nations but some of the new ones on the other hand.