Anti-interference composite online guiding method of atmosphere entering period of Mars lander

Abstract

The invention provides an anti-interference composite online guiding method of the atmosphere entering period of a Mars lander. The method includes the following steps of a, establishing a Mars lander atmosphere entering period kinetic model, and introducing Mars atmosphere density uncertainty interference into the Mars lander atmosphere entering period kinetic model; b, establishing an interference observer, wherein the interference observer estimates the Mars atmosphere density uncertainty interference; c, designing a prediction-correction guiding rule, wherein the prediction-correction guiding rule updates to-be-determined parameters of the heel angle amplitude; d, compositing the interference observer in the step b with the prediction-correction guiding rule in the step c to obtain an anti-interference composite guiding rule, wherein the anti-interference composite guiding rule complements for the Mars atmosphere density uncertainty interference through the estimation value of the Mars atmosphere density uncertainty interference.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to an anti-interference composite online guidance method for the atmosphere entry section of a Mars lander. Background technique [0002] In recent years, with the rapid development of aerospace technology, deep space exploration has become a space activity that the world is eager to carry out. In the process of human deep space exploration, the most important task is to explore life, and Mars, as the closest star to the earth that may have signs of life, has also become the first stop for human beings to start their deep space journey. Judging from the Mars missions that humans have already carried out, future Mars exploration will have higher and higher requirements for landing accuracy. However, considering the distance between Mars and the Earth, as well as the unforeseen uncertainties on Mars, it has brought great challenges to the improvement of the accuracy of Mars landin...

AI Technical Summary

Problems solved by technology

However, the prediction-correction guidance method requires extremely high model accuracy of the lander, and the harsh Martian environment has a great impact on the accuracy of the guidance method

Relevant research has been carried out on the guidance method of the Mars atmosphere entry stage in China. The patent application number is 201510303486.0. A precise control method for the lander entry stage based on feed-forward compensation is proposed, but there is a problem: in the current stage of Mars landing mission planning , the requirements for the integration of orbit-land-patrol make the lander need to carry out online guidance law design without relying on the nominal trajectory to achieve the requirement of reaching the predetermined parachute opening point, and then ensure the landing accuracy. The autonomy of this method is relatively weak

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