System anti-impact method suitable for Mars landing task

An impact-resistant, Mars-resistant technology, applied in the field of satellite control, can solve the problems of short Mars landing process time, large measurement and control delay, and inability to manually intervene on the ground, so as to reduce the impact resistance index, reduce the frequency of acquisition, and reduce hardware complexity. Effect

Active Publication Date: 2021-12-10
BEIJING INST OF CONTROL ENG
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AI Technical Summary

Problems solved by technology

The Mars landing process takes a short time (about 9 minutes), and the measurement and control time delay is long (20 minutes one way). The EDL process cannot be manually intervened on the ground, and can only be executed by the system on orbit.

Method used

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  • System anti-impact method suitable for Mars landing task
  • System anti-impact method suitable for Mars landing task
  • System anti-impact method suitable for Mars landing task

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Embodiment Construction

[0030] In order to make the object, technical solution and advantages of the present invention clearer, the implementation manner of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0031] The Mars entry module (lander) consists of a back cover, a heat release outsole, and a landing platform ( figure 1 ), the back cover is equipped with trim wings and parachutes, and the landing platform is equipped with landing legs. Before the probe enters the Martian atmosphere, the landing legs are in a compressed state and the trim wings are in a closed state. The landing platform is wrapped in an airtight cabin composed of a back cover and a heat-resistant outsole, forming an entry cabin configuration. The GNC subsystem of the entry module completes the attitude and position control of the entry module during the Mars landing process, and realizes the safe landing of the probe on the surface of Mars. The GNC sub-system of ...

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Abstract

The invention discloses a system anti-impact method suitable for a Mars landing task. The system anti-impact method comprises relay anti-impact, balancing wing state autonomous diagnosis and processing and grounding switch state autonomous diagnosis and processing. The electromagnetic coil in the relay is continuously powered up from the time before an initiating explosive device is detonated to the time after the initiating explosive device is detonated, so that the relay works normally; the balancing wing state autonomous diagnosis and processing comprises the following steps: before the initiating explosive device is detonated, if a signal that a certain path of balancing wing is unfolded in place is effective, considering that a switch of the path is in fault, and not using the signal of the path subsequently; after the initiating explosive device is detonated, if one or more paths of balancing wing unfolding in-place signals are collected to be effective, considering that the balancing wing is unfolded in place, and otherwise, considering that the balancing wing is not unfolded; the grounding switch state autonomous diagnosis and processing comprises the following steps: before grounding, if a certain grounding switch is in a grounding state, considering that the grounding switch is in a fault state, and no longer using the signal in the subsequent process; and after grounding, judging whether grounding exists or not according to the states of the remaining grounding switches.

Description

technical field [0001] The invention relates to a system shock resistance method suitable for Mars landing mission, which belongs to the field of satellite control technology. Background technique [0002] During the landing process, the Mars rover needs to go through aerodynamic deceleration, parachuting and power deceleration. During this period, it has successively experienced the detonation process of the pyrotechnic device such as trimming the wing, the parachute, throwing the outsole, spreading the landing legs, and throwing the back cover, and the process of deploying the parachute. Reach 2200g. Each product of the GNC sub-system needs to withstand this mechanical environment, and the system's working sequence is normal and uninterrupted. The Mars landing process takes a short time (about 9 minutes), and the measurement and control time delay is long (20 minutes one way). The EDL process cannot be manually intervened on the ground, and can only be executed by the sy...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0808G05D1/101
Inventor 赵宇刘旺旺徐李佳郝策王云鹏陈尧王晓磊何健李茂登张琳余志鸿黄翔宇
Owner BEIJING INST OF CONTROL ENG
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