Work/Energy Principles Applied to a Deadband Attitude Control System to Analyze Bending Limit Cycles.

摘要

An attitude control system used on a flexible spacecraft is analyzed by applying work/energy and impulse/momentum principles. The elements of one channel of control include a rate gyro;electronic components for integration,summing,filtering and switching;and gas thrusters controlled by solenoid valves. The switching device is analyzed as a standard nonlinear element with deadband and hysteresis. The solenoid time delay nonlinearity treatment accounts for the fact that no thrust occurs for short duration commands. The analysis evaluates the work done on the spacecraft by the thrusters. This work input is equated to the increase of system kinetic energy plus the structural damping dissipation.