Analysis of trajectory sensitivity in restricted three-body problem

Author

Zhang Han-qing ; Lu Yu-ping ; Gao You-tao

Author_Institution

Nanjing Univ. of Aeronaut. & Astronaut., Nanjing, China

fYear

2014

fDate

28-30 July 2014

Firstpage

2493

Lastpage

2496

Abstract

In the context of circular restricted three-body problem, the trajectory sensitivity to disturbances of different kinds, different magnitude, and different direction are analyzed. Firstly, a method based on eigenvalues of state transition matrix is improved to achieve computational efficiency. Secondly, a method based on error in configuration space is proposed to calculate trajectory local stability in detail. Based on this method, the maximum unstable direction of any point on the trajectory can be decided. As an example, the trajectory sensitivity of Earth-Moon L1 point Lyapunov orbit is calculated and discussed in detail. Finally, this method is extended to calculate the sensitivity of a non-periodical trajectory, and the result is presented. Information gained from the trajectory sensitivity analysis can be used to guide the measurement and navigation process in practical space missions.

Keywords

Lyapunov methods; aerospace control; matrix algebra; sensitivity analysis; space vehicles; stability; trajectory control; Earth-Moon L1 point Lyapunov orbit; calculate trajectory local stability; computational efficiency; configuration space; different direction; different magnitude; eigenvalues; nonperiodical trajectory; restricted three-body problem; space missions; spacecraft dynamical behavior; state transition matrix; trajectory sensitivity analysis; Eigenvalues and eigenfunctions; Numerical stability; Orbits; Sensitivity; Stability analysis; Trajectory; Vectors; Lyapunov orbits; circular restricted three-body problem; trajectory sensitivity;

fLanguage

English

Publisher

ieee

Conference_Titel

Control Conference (CCC), 2014 33rd Chinese

Conference_Location

Nanjing

Type

conf

DOI

10.1109/ChiCC.2014.6897026

Filename

6897026