论文部分内容阅读
主要研究了小卫星姿控/热控一体化执行机构的设计问题。首先,根据流体回路中液体流速变化对小卫星产生力矩实现姿态控制、液体流动吸/散废热实现热控制的原理,提出一种姿控/热控一体化执行机构设计方案。然后针对该设计方案,利用以电机转速为变量的流体回路内压强和电磁力矩方程,推导了一体化执行机构姿控力矩模型;利用散热量随流体回路流速的变化,建立了一体化执行机构热控模型。最后,针对某小卫星设计了基于姿控/热控一体化执行机构的闭环控制系统,并针对该一体化执行机构设计了一种姿控/热控解耦算法,对其姿控/热控能力进行数学仿真验证,仿真结果证明了该一体化执行机构的有效性。
Mainly studied the design of small satellite attitude control / thermal control integrated actuator. First of all, based on the principle of controlling the moment of the small satellite and controlling the flow of liquid in the fluid circuit, the principle of thermal control is realized by liquid flow suction / exhaust heat. A design scheme of the integrated control system with attitude control and thermal control is proposed. Then according to the design scheme, using the equation of the pressure and the electromagnetic torque in the fluid circuit with the motor rotation speed as the variable, the attitude control torque model of the integrated actuator is deduced. By using the variation of the heat flux with the flow rate of the fluid circuit, an integrated actuator heat is established Control model. Finally, a closed-loop control system based on attitude control / thermal control integrated actuator is designed for a small satellite. An attitude control / thermal control decoupling algorithm is designed for the integrated actuator. The attitude control / thermal control The ability to carry out mathematical simulation verification, the simulation results demonstrate the effectiveness of the integrated actuator.