Study of the degree of controllability of a spacecraft during flight along a reference trajectory in the atmosphere of Mars

The process of landing a spacecraft on Mars or another planet is studied. During the descent of the aircraft in the atmosphere, a test mathematical model of guidance is chosen. The criterion of the controllability degree is applied to determine the degree of controllability when moving along various trajectories. Mathematical modeling of the spacecraft guidance process during descent in the Martian atmosphere according to tracking scheme of the program trajectory by using a control algorithm with active disturbance compensation and a proportionalintegralderivative (PID) adjuster is considered. Based on the results of the simulation, it is possible to evaluate and compare the optimality of various reference trajectories by using a criterion that is used as an indicator to study the influence of trajectory parameters on the landing process from the point of view of controllability. Keywords spacecraft, degree of controllability criterion, linear non-stationary system, reference trajectory guidance, control with active disturbance compensation