A Disturbance Observer-Based Optimal Control Method for Lander Dynamic Descent

Abstract

Provided is a lander power descending branch optimal control method based on a disturbance observer. For a system state spatial model of a lander with the disturbance at the power descending branch, the anti-interference optimal control method is designed. Firstly, the system state spatial model of the power descending branch lander with the disturbance is built; secondly, based on the state space model with the disturbance, the disturbance observer is designed; then, based on a system nominal model, a lander fuel optimal controller is designed; finally, based on the disturbance observer and the optimal controller, a compound control method is designed. The method has the advantages of being high in anti-interference performance and high in working reliability, the fuel consumption of the lander is optimized, and the method is applicable to accurate optimal control over the planet lander at the power descending branch in the spaceflight field.

Description

technical field [0001] The invention relates to an optimization control method for a lander's power descent section based on a disturbance observer, which is mainly applied to a planetary lander's precise anti-interference landing in a fuel-optimized manner in the power descent section. Background technique [0002] As one of the closest planets to the earth, Mars has many similarities with the earth, and has become the preferred target star for human deep space exploration. In recent decades, planetary exploration activities, especially landing exploration activities, have become more and more frequent. With the advancement of science and technology and the accumulation of engineering experience, the landing accuracy of the Mars rover on the surface of Mars has been continuously improved in the past forty years, from 200km of the "Viking" to 150km of the "Pathfinder" to The 35km range of the Mars Rover and, most recently, the 10km landing range of Curiosity. On these Mars...

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Problems solved by technology

[0005] The technical solution of the present invention is to provide a control method for the disturbance observer to estimate the disturbance and optimize the fuel for the disturbance received by the planetary lander during the power descent phase, and to solve the problem caused by the disturbance caused by the planetary lander during the power descent process. The problem of reduced landing accuracy improves the landing accuracy of the planetary lander, and at the same time realizes the optimal control of fuel

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