Design of a three-axis stabilized ORION satellite using an all-thruster attitude control system
Dee, Suzanne M.
Titus, Harold A.
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An all-thruster three-axis stabilized attitude control system has been designed for the Naval Postgraduate School (NPS) satellite bus, ORION. The satellite is a cylinder, 19 inches in diameter, 35 inches in length, 250 pounds maximum mass with 32 pounds for payloads. ORION will be ejected from an extended Get-Away-Special (GAS) canister. Launch from any GAS can configure expendable booster or the space shuttle is assumed. The minimization techniques of Pontryagin have been used to derive control laws that support fuel efficient operation. A minimum time cost function is applied in the acquisition phase to reduce rates to acceptable levels. A weighted minimum fuel-time cost function is used during the on-station phase. Bang-Off-Bang control with two switching curves is employed outside of a boundary region. Inside the boundary region, four pulse limit cycle control with time constants on the order of 100 seconds is applied
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