Mars machine-machine separating orbit design method

Abstract

The invention discloses a Mars machine-machine separating orbit design method. The method comprises the following steps: S1. under a near focus coordinate system, establishing a Mars machine-machine separating orbit design equation taking landing orbit eccentricity as independent variable; and S2. by taking the minimum speed increment during orbit transfer of a landing machine as a target function, solving the Mars machine-machine separating orbit design equation by adopting a preset solving algorithm to obtain the landing orbit of the landing machine, thus completing the Mars machine-machine separating orbit design. According to the method, the minimum speed increment during orbit transfer as the target (landing through the shortest starting time of an engine), the constraint condition of an entrance angle when the landing machine enters Mars atmosphere can be met, and the method is simple and feasible and provides support for deep space detection machine-machine separation.

Description

technical field [0001] The invention relates to a Mars exploration orbit control technology, in particular to a method for designing a Mars vehicle separation orbit. Background technique [0002] my country will launch a Mars probe in 2020 to achieve orbiting, landing, and inspection tasks. The orbiter carries the lander to achieve capture and braking. After orbit adjustment, it enters the parking orbit. 5 hours before the near fire point, the orbiter descends orbit and maneuvers into the collision. In the fire track, the orbiter and the lander are separated from the actuators on the fire track, and then the orbiter chooses an opportunity to ascend into the ring fire track, such as figure 1 shown. The landing trajectory is usually designed with the constraint of the entry angle of the lander into the Martian atmosphere. The Viking probe uses the lander to descend into the landing orbit at the apogee point. It is more convenient to design the landing orbit at this point and ...

AI Technical Summary

Problems solved by technology

The Viking probe uses the lander to descend into the landing orbit at the apogee. It is more convenient to design the landing orbit at this point and the landing orbit is uniquely determined, but it is far away from the surface of Mars. Due to the influence of the orbit measurement on the ground, the landing accuracy of the lander is relatively low. Difference,

[0003] like figure 2 As shown, there are many attitude maneuvers and orbital maneuvers performed during the separation stage of the vehicle. Excessive running time in the collision orbit will increase the risk of the orbiter and increase fuel consumption. During the separation period, the ground cannot be measured and remotely controlled in real time, so the orbiter’s de-orbit time should not be too long. After separation, choose an opportunity to ascend the orbit

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