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对于在大气层外采用直接侧向力控制的飞行器来说,由于推力偏心以及质心漂移的存在,飞行器轨控发动机在工作时,会在滚转、俯仰、偏航等通道中产生附加的姿态干扰力矩。若干扰力矩过大,就会导致姿态失稳。首先建立了一个完整的基于直接侧向力控制的飞行器仿真模型,以动力学模型为基本方程,分别采用扩展卡尔曼滤波(EKF)和无迹卡尔曼滤波(UKF)推导出了飞行器推力偏心和质心漂移的滤波模型。最后给出了仿真算例,验证了滤波模型的正确性并对2种滤波模型的特性进行了对比。
For aircraft with direct lateral force control outside the atmosphere, due to the thrust eccentricity and the center of mass drift, the aircraft orbit-controlled engine will generate additional attitude disturbance torque in roll, pitch, yaw and other channels during operation . If the interference torque is too large, it will lead to instability. Firstly, a complete simulation model of aircraft based on direct lateral force control is established. Taking the dynamic model as the basic equation, the EKF and UKF are respectively used to derive the aircraft thrust eccentricity and Filter model of center of mass drift. Finally, a simulation example is given to verify the correctness of the filtering model and to compare the characteristics of the two filtering models.