基于蒙特卡洛法的卫星分离姿态计算方法

为了计算以弹簧作为分离动力源的卫星在星箭分离时刻的分离姿态,建立了六自由度动力学方程,并采用龙格库塔法求解了该方程,算例结果表明:通过该方法计算得到的分离角速度与ADAMS仿真计算结果相比,最大偏差小于0.77%。基于以上研究,针对卫星、弹簧装置多个设计偏差对卫星分离姿态的影响,提出基于蒙特卡洛法的卫星分离姿态分析方法。飞行试验结果表明,由该方法得到的分离角速度与常规保守算法相比,计算精度提高35%左右,解决了工程中由于采用将各个偏差取最大值进行保守计算而导致计算结果偏差较大的问题,可为卫星设计、弹簧装置设计提供参考。

Calculation Method of Satellite Separation Attitude Based on Monte Carlo Method

In order to calculate the separation attitude of the satellite which is separated by spring device,the 6 degrees of freedom dynamic equation is established and solved by the Runge-Kutta Method.The numerical examples indicate that the maximum deviation of separation angular velocity obtained by this method and the ADAMS simulation is less than 0.77％.Based on the above studies,a analysis method based on Monte Carlo Method is proposed to calculate satellite separation attitude considering the satellite and spring device design deviations.The results of flight test indicate that the proposed method can improve the accuracy by 35％ compared with the conventional conservative algorithm.The method solves the problem that the deviation of the calculation result is large due to the conservative calculation of the maximum value of each deviation.This method can provide a reference for satellite design and spring device design.