The Pulsed Plasma Thruster (PPT) Experiment on the Earth Observing 1 (EO-1) spacecraft has been designed to demonstrate the capability of a new generation PPT to perform spacecraft attitude control. The PPT is a small, self-contained pulsed electromagnetic Propulsion system capable of delivering high specific impulse (900-1200 s), very small impulse bits (10-1000 micro N-s) at low average power (less than 1 to 100 W). EO-1 has a single PPT that can produce torque in either the positive or negative pitch direction. For the PPT in-flight experiment, the pitch reaction wheel will be replaced by the PPT during nominal EO-1 nadir pointing. A PPT specific proportional-integral-derivative (PID) control algorithm was developed for the experiment. High fidelity simulations of the spacecraft attitude control capability using the PPT were conducted. The simulations, which showed PPT control performance within acceptable mission limits, will be used as the benchmark for on-orbit performance. The flight validation will demonstrate the ability of the PPT to provide precision pointing resolution. response and stability as an attitude control actuator.
Design of the EO-1 Pulsed Plasma Thruster Attitude Control Experiment
2001
11 pages
Report
No indication
English
Space Launch Vehicles & Support Equipment , Design analysis , Pulsed plasma thrusters , Attitude control , Plasma control , Experiment design , Actuators , Algorithms , Controllability , Derivation , Electromagnetic propulsion , High impulse , Pointing control systems , Reaction wheels , Simulation , Spacecraft control , Stability
New Attitude Control Strategies Using Pulsed Plasma Thruster Systems (AAS 98-065)
British Library Conference Proceedings | 1998
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