ANALYSIS AND DESIGN OF A FIXED-WHEEL ATTITUDE STABILIZATION SYSTEM FOR A STATIONARY SATELLITE

摘要

The dynamics of a spacecraft with an ungimballed momentum wheel is reexamined. Possible methods of compensation are analyzed, and a practical design procedure for a satellite with single channel control (no yaw sensor) is proposed. In the following more novel part, the analysis is applied to the general case of a satellite with two channel control (with yaw sensing). Performance comparisons between the systems with and without yaw sensors are made, and effects of various system parameters are studied for the purposes of an engineering optimization. Linearized time-domain responses are derived and total impulse computations carried out at an important indicator of the projected fuel consumption. The data generated in the analytical and computational parts are used to draw conclusions applicable to the attitude control system design. Recommendations are made for engineering optimization of a control system based on weight, power, performance, total impulse and fuel consumption, reliability, redundancy, mission life and other engineering considerations.