Uncertainty Propagation And Maneuver Optimization Of Spacecraft Orbit

In recent years,with the continuous development of space technology and the increasing number of space missions,the safety operation of spacecraft in orbit and the accuracy assurance of rendezvous missions have been paid more and more attention by relevant personnel in the space field.Therefore,it is necessary to analyze the uncertain propagation and optimize the robust maneuver of the spacecraft orbit.Under the influence of navigation error and control error,this thesis mainly studies the error propagation rule by using linear covariance analysis method,and robust optimization of spacecraft orbit is carried out.The specific research contents are as follows:In the case of impulse thrust,the fixed-time fuel-optimal multi-impulse rendezvous model is constructed under the condition of absolute motion and relative motion respectively.The terminal error covariance matrix is solved by linear covariance analysis under navigation error and control error.On this basis,the terminal robust performance optimization index is added,and the corresponding multi-objective optimization problem is obtained.By optimizing the impulse time and corresponding impulse vector,the fuel and terminal error covariance can reach the optimal state simultaneously.For the J2 perturbed case,the fixed-time fuel-optimal problem is studied based on the analytic state transfer matrix of elliptical orbit.The propagation of navigation error and control error is analyzed.In the case of constant thrust,based on the state transition matrix of constant thrust acceleration,the fixed-time fuel-optimal multi-stage constant thrust rendezvous problem is constructed under relative motion conditions.The propagation of navigation error and constant thrust control error is analyzed by linear covariance analysis method.On this basis,the Pareto optimal solution set of fuel and terminal state error is obtained by optimizing the switching time of constant thruster.For the J2 perturbed case,in the presence of control error,the sensitivity matrix is used for error propagation analysis.In the case of continuous small thrust,based on the relative motion equation of circular orbit,the discrete covariance control problem is constructed.When the terminal state error constraint is an equality constraint,the solution of the fuel optimization problem is obtained by solving a matrix equation.When the constraint is an inequality constraint,the original problem is transformed into a convex optimization problem,and the convex optimization algorithm is used to solve this problem.