A spacecraft is subjected to very large dynamic forces from its launch vehicle during its ascent into orbit. These large forces place stringent design requirements on the spacecraft and its components to assure that the trip to orbit will be survived. The severe launch environment accounts for much of the expense of designing qualifying, and testing satellite components. Reduction of launch loads would allow more sensitive equipment to be included in missions, reduce risk of equipment or component failure, and possibly allow the mass of the spacecraft bus to be reduced. These benefits apply to military as well as commercial satellites. This paper reports the design and testing of a prototype whole-spacecraft isolation system which will replace current payload attach fittings is passive-only in nature, and provides lateral isolation to a spacecraft which is mounted on it. This isolation system is being designed for a medium launch vehicle and a 65O0 lb spacecraft but the isolation technology is applicable to practically all launch vehicles and spacecraft, small and large. The feasibility of such a system on a small launch vehicle has been demonstrated with a system-level analysis which shows great improvements. The isolator significantly reduces the launch loads seen by the spacecraft Follow-on contracts will produce isolating payload attach fittings for commercial and government launches.
Payload Isolation System for Launch Vehicles
1997
13 pages
Report
Keine Angabe
Englisch
Space Launch Vehicles & Support Equipment , Unmanned Spacecraft , Vibration , Payload , Launch vehicles , Spacecraft , Requirements , Environments , Risk , Loads(Forces) , Failure , Fittings , Isolation , Prototypes , Costs , Artificial satellites , Launching , Attenuation , Dynamic loads , Sbir(Small business innovation research) , Sbir reports , Launch loads , Payload isolation
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