Math simulation of attitude stabilization accuracy and performance for an earth remote sensing spacecraft

The paper discusses a math simulation of an Earth remote sensing spacecraft attitude control loop dynamics during imaging. The spacecraft is intended for imaging a swath along the flight path, stereo imaging, area and corridor imaging at an angle to the flight path. To provide the spacecraft with high maneuverability during imaging it is assumed that the control loop uses as its effectors one-axis powered gyros. Studies were conducted of the feasibility of using this spacecraft for performing a series of area and corridor surveys. Selected for the attitude control loop were the control parameters which allow meeting the specified performance. Simulation results have confirmed that the spacecraft is capable of performing these kinds of surveys and meeting the specified accuracy levels. Key words: Earth remote sensing spacecraft, control moment gyros, single-axis powered gyros, kinetic momentum, stabilization, angular rate, precession.