Midway correction strategy making and implementing method suitable for Mars detection

Abstract

The invention relates to a midway correction strategy making and implementing method suitable for Mars detection. The method comprises the following steps that: S1, an error transfer model of a detector from any moment to the moment when the detector enters a Mars influence ball is established according to a limited three-body gravity orbit kinetic model, the orbit deviation of the detector arriving at the Mars at the current moment is calculated according to the error transfer model, and when the orbit deviation exceeds a deviation preset value, the method shifts to S2; S2, the speed error ofthe detector is corrected at the current moment by adopting a differential correction method with the parameter of entering the B-plane of the orbit of the Mars taken as a target, and iterative computation is performed with the error transfer model in the S1 to obtain pulse speed increment at the current moment; and S3, according to the pulse speed increment in the step S2, an orbit control duration and an orbit control ignition direction are obtained. With the method adopted, the autonomous formulation and implementation of a midway correction strategy under limited computing resources are realized. The method is simple and feasible, and Mars detection reliability under the condition of the absence of ground support is improved.

Description

technical field [0001] The invention relates to a formulating and implementing method for a midway correction strategy suitable for Mars exploration, in particular to an online formulating and autonomous implementation method for a midway correction strategy suitable for Mars exploration, and belongs to the technical field of Mars exploration orbit control. Background technique [0002] Our country will launch a Mars probe in 2020, and realize the conventional three-step process of "circling", "falling" and "patrolling" at one time. After the Mars probe is put into orbit, due to the orbital errors of the rocket, navigation errors, maneuver execution errors, and various perturbation forces that the probe receives during its flight, the actual flight track of the probe will deviate from the nominal track. In order to reach the planned To capture the aiming point, multiple mid-course track corrections (TCM) must be completed on the detector during the ground fire cruise. [00...

AI Technical Summary

Problems solved by technology

[0003] Traditional halfway corrections are based on ground orbit determination data, and a large number of simulation iterative calculations are performed on the ground to finally formulate a halfway correction capture strategy. This method is limited by ground measurement and control and orbit measurement; The strategy cannot be generated independently on the Internet, resulting in the failure to reach Mars in the end

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