Research on Landing Control Scheme of Mars Probe Based on Differential Equation

Abstract

In this paper, a mathematical model is established to study the movement of the detector under different conditions. Firstly, in order to determine the control scheme with the shortest landing time, this paper analyzes the motion changes of the probe in each stage, and establishes the differential equations of velocity and angle changes in each stage, that is, the motion differential model of the landing process of the Mars probe. Then, before entering the Martian atmosphere, simplify the decision variables in the first stage as incident angle and incident velocity. After entering the Martian atmosphere, take the end time of pneumatic deceleration section and the end time of the second part of parachute deceleration section as decision variables, and take the minimum value of the end time of dynamic deceleration section as the objective function. A multivariate optimization model based on the motion differential model of the landing process of Mars probe is established. Finally, the optimal value of the probe after entering the Martian atmosphere is obtained by ergodic solution.