Start Date
4-1988 8:00 AM
Description
A low cost general purpose mini-satellite bus is being designed to support a wide variety of small scientific and commercial payloads. The design incorporates several innovative concepts intended to reduce construction, launch and operational costs. The design is compatible with the new NASA extended Get-Away-Special (GAS) canister and several small low-cost expendable launch vehicles. The satellite is 19 inches in diameter, 35 inches long and weighs approximately 270 Ibs. The satellite bus provides telemetry, attitude control, orbital boost/station keeping, electrical power, microprocessor and data storage for up to 50 Ibs. of user payload . The hydrazinc propulsion system provides up to 2600 ft/sec delta-V capability. The availability of on-board propulsion reduces launcher orbital insertion accuracy requirements, provides for stationkeeping and is sufficient to allow the satellite to independently achieve 800 nm circular or 2200 nm elliptic orbits from an initial 135 nm orbit. The design stresses simplicity, ingenuity, and utilization of previously proven and high quality commercial components. Manufacturing costs are reduced by "using simple design practices and simplified test procedures. Total cost for the satellite is projected to be less than $1.5 million. Orion will be ready for launch in 1990.
Orion: Design of a Small, General Purpose, Low Earth Orbit Satellite Bus
A low cost general purpose mini-satellite bus is being designed to support a wide variety of small scientific and commercial payloads. The design incorporates several innovative concepts intended to reduce construction, launch and operational costs. The design is compatible with the new NASA extended Get-Away-Special (GAS) canister and several small low-cost expendable launch vehicles. The satellite is 19 inches in diameter, 35 inches long and weighs approximately 270 Ibs. The satellite bus provides telemetry, attitude control, orbital boost/station keeping, electrical power, microprocessor and data storage for up to 50 Ibs. of user payload . The hydrazinc propulsion system provides up to 2600 ft/sec delta-V capability. The availability of on-board propulsion reduces launcher orbital insertion accuracy requirements, provides for stationkeeping and is sufficient to allow the satellite to independently achieve 800 nm circular or 2200 nm elliptic orbits from an initial 135 nm orbit. The design stresses simplicity, ingenuity, and utilization of previously proven and high quality commercial components. Manufacturing costs are reduced by "using simple design practices and simplified test procedures. Total cost for the satellite is projected to be less than $1.5 million. Orion will be ready for launch in 1990.
Comments
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