Research of Satellite Separation Attitude Based on Monte Carlo Method

Paper number

IAC-20,C2,IP,7,x56522

Author

Mr. KANG Shipeng, China, Aerospace System Engineering Shanghai, China

Coauthor

Mr. CHEN Mingliang, China, Aerospace System Engineering Shanghai, China

Coauthor

Mr. SONG Linyu, China, Aerospace System Engineering Shanghai, China

Coauthor

Mr. ZHANG Zheyuan, China, Aerospace System Engineering Shanghai, China

Coauthor

Mr. SU Xinyuan, China, Aerospace System Engineering Shanghai, China

Year

2020

Abstract

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. 

  Furthermore, the influence of 6 factors on angular velocity is studied by the sensitivity analysis. The 6 factors are satellite mass deviation, satellite centroid position deviation, satellite inertia deviation, angle deviation of the spring thrust, spring thrust deviation, and spring installation deviation. The Analysis results indicated that satellite centroid position deviation and the angle deviation of the spring thrust are the main factors affecting satellite's separation attitude, and then the spring installation deviation and spring thrust deviation, while satellite mass deviation and satellite inertia deviation have little effect on it.

Abstract document

IAC-20,C2,IP,7,x56522.brief.pdf

Manuscript document

(absent)