Methods of spacecraft impulsive relative hovering and trajectory safety analysis

CHENG ， YUAN Jianping， QIAN Yingjing， MA Weihua

1.School of Astronautics, Northwestern Polytechnical University, Xi′an 710072, China
2.Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China
3.National Key Laboratory of Aerospace Flight Dynamics, Xi′an 710072, China
4.College of Mechanical Engineering and Applied Electronics Technology, Beijing University of Technology,
Beijing 100124, China

Methods of spacecraft impulsive relative hovering and trajectory safety analysis

CHENG ， YUAN Jianping， QIAN Yingjing， MA Weihua

1.School of Astronautics, Northwestern Polytechnical University, Xi′an 710072, China
2.Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China
3.National Key Laboratory of Aerospace Flight Dynamics, Xi′an 710072, China
4.College of Mechanical Engineering and Applied Electronics Technology, Beijing University of Technology,
Beijing 100124, China

摘要 Based on the analytical solutions of TH equations and its state transition matrix form, the openloop control method of spacecraft impulsive relative hovering was studied, which is promising for practical engineering use. The true anomaly intervals of the hovering impulse were optimized by the nonlinear mathematical programming. Based on the calculation of collision probability, the method of safety analysis and risk management was proposed. The numerical simulations show that the introduced relative hovering method can be used for circular and elliptical reference orbits hovering. Furthermore,the local optimal solution can be obtained by applying the true anomaly intervals optimization method. The maximum collision probability and the minimum relative distance nearly appear at the same time. And, the smaller the relative distance is, the larger the collision probability.

Abstract：
Based on the analytical solutions of TH equations and its state transition matrix form, the openloop control method of spacecraft impulsive relative hovering was studied, which is promising for practical engineering use. The true anomaly intervals of the hovering impulse were optimized by the nonlinear mathematical programming. Based on the calculation of collision probability, the method of safety analysis and risk management was proposed. The numerical simulations show that the introduced relative hovering method can be used for circular and elliptical reference orbits hovering. Furthermore,the local optimal solution can be obtained by applying the true anomaly intervals optimization method. The maximum collision probability and the minimum relative distance nearly appear at the same time. And, the smaller the relative distance is, the larger the collision probability.

CHENG ,
YUAN Jianping,
QIAN Yingjing等
.Methods of spacecraft impulsive relative hovering and trajectory safety analysis[J] 中国空间科学技术, 2017,V37(6): 89-

CHENG ,
YUAN Jianping,
QIAN Yingjing etc
.Methods of spacecraft impulsive relative hovering and trajectory safety analysis[J] Chinese Space Science and Technology , 2017,V37(6): 89-