CAJ | 학술논문

本文研究利用气浮台上的动量轮执行机构,模拟卫星上挠性附件振动产生的干扰力矩的卫星物理仿真实验方法,以克服三轴气浮台不能直接安装挠性附件进行仿真的局限性.本实验方法通过设计一个跟踪控制器,令气浮台的姿态角速度跟踪挠性卫星参考动力学,并由动量轮产生控制力矩,该力矩即是实验模拟的挠性振动干扰力矩.理论和仿真研究表明:(1)本文提出的挠性干扰力矩模拟方法可以较好地模拟低阶挠性振动干扰力矩;(2)理论上当控制器的增益参数越大,系统能够模拟的干扰力矩频率就越大,但是由于测量噪声的影响,反馈增益不能选得过大;(3)本方法模拟的干扰力矩与真实干扰力矩存在一定的相位延迟,这是由于控制器和执行机构的固有延迟造成的.通过引入超前-滞后校正网络可以有效减小延迟的影响.
본문연구이용기부태상적동량륜집행궤구,모의위성상뇨성부건진동산생적간우력구적위성물리방진실험방법,이극복삼축기부태불능직접안장뇨성부건진행방진적국한성.본실험방법통과설계일개근종공제기,령기부태적자태각속도근종뇨성위성삼고동역학,병유동량륜산생공제력구,해력구즉시실험모의적뇨성진동간우력구.이론화방진연구표명:(1)본문제출적뇨성간우력구모의방법가이교호지모의저계뇨성진동간우력구;(2)이론상당공제기적증익삼수월대,계통능구모의적간우력구빈솔취월대,단시유우측량조성적영향,반궤증익불능선득과대;(3)본방법모의적간우력구여진실간우력구존재일정적상위연지,저시유우공제기화집행궤구적고유연지조성적.통과인입초전-체후교정망락가이유효감소연지적영향.
Because of the Earth gravity, flexible appendages cannot be fixed on the table, three-axis air-bearing table cannot be used to simulate attitude dynamics of a flexible satellite, a method is developed by using momentum wheels to simulate the vibrational disturbance torque of satellite flexible appendages on three-axis air-bearing table. By designing a tracking controller, the air-bearing table' s angular velocity is used to track reference dynamics of the flexible satellite, the momentum wheel provide the control torque, i.e. the vibration disturbance torque to be simulated. The theory and mathematial simulations show: ( 1 ) This method can simulate low-order flexible vibration disturbance torque well; (2) In theory, the greater the controller gain, the higher frequency of disturbance torque can be simulated. However, because of measurement noise, the feedback gain cannot be too great; (3) Due to the inherent de]ay of controller and actuator, there is phase delay between the emulational disturbance torque and real disturbance torque. Therefore, a lead-lag correction network is introduced to reduce the effect of phase delay.