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在轨航天器执行机构一般具有典型的非线性特性,直接影响飞行姿态控制性能。基于姿态控制系统模型,应用相平面分析方法,建立含继电器和时延两类非线性特性的执行机构开关线模型。以开关线模型为基础,根据相轨迹图求解极限环参数,获得姿态控制的稳态特性。仿真结果表明非线性姿态控制系统特性的计算模型和方法正确、有效。
Orbiting spacecraft actuators typically have typical nonlinearities that directly affect flight attitude control performance. Based on the attitude control system model, phase-plane analysis method is used to establish switch line model of actuator with two kinds of nonlinear characteristics including relay and delay. Based on the switch line model, the parameters of the limit cycle are solved according to the phase locus diagram, and the steady state characteristics of the attitude control are obtained. The simulation results show that the calculation model and method of nonlinear attitude control system are correct and effective.