A Study on the Method of Spacecraft Deorbit Return Orbit Optimization

The return trajectory optimization of spacecraft is a typical problem on optimal control. The spacecraft is affected by quality, kinetic energy, aerodynamics, thermal flux, overload and so on, which determines it difficult to attain the analytical solutions to the return trajectory problem. Currently, most of numerical methods on trajectory optimization mainly reduce indirect and direct methods. Because the spacecraft problem is a non-linear optimization problem containing terminal and procedure constraints, it is solved by Gauss pseudo-spectral method, which could attain higher precision by using fewer scattered points, and the estimation accuracy on boundary values is also higher. Optimize the return trajectory using Gauss pseudo-spectral method to obtain the optimal value satisfies terminal and process constraint, and the inaccuracy of the opening point is smaller, the estimation accuracy is higher.