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A composite fast non-singular terminal sliding mode control method for the atmospheric entry segment of the Mars rover

A technology for Mars probes and non-singular terminals, applied in the aerospace field, can solve problems such as system chattering, decrease in convergence speed, reduce command tracking speed and accuracy, etc., achieve fast convergence speed, eliminate discontinuous items, and improve anti-interference performance effect

Active Publication Date: 2022-08-05
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

However, relying on the existing sliding mode controller for active anti-jamming control design strategy, the convergence speed drops sharply when the error is less than a certain value, which reduces the speed and accuracy of instruction tracking; mode controller, which brings serious chattering problems to the system

Method used

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  • A composite fast non-singular terminal sliding mode control method for the atmospheric entry segment of the Mars rover
  • A composite fast non-singular terminal sliding mode control method for the atmospheric entry segment of the Mars rover
  • A composite fast non-singular terminal sliding mode control method for the atmospheric entry segment of the Mars rover

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Embodiment Construction

[0043] The accompanying drawings constituting a part of the present invention are used to provide further understanding of the present invention, and the exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention.

[0044] The simulation of the present invention is built based on the Simulink toolbox in the simulation software MATLAB R2015b; such as figure 1 As shown, this embodiment provides a composite fast non-singular terminal sliding mode control method for the atmospheric entry segment of a Mars rover, which specifically includes the following steps:

[0045] S1. Establish the disturbed dynamic model of the longitudinal motion of the Mars rover's atmospheric entry section, and obtain the dynamic equation of the height tracking error;

[0046] The disturbed dynamic model of the longitudinal motion of the Mars rover's atmospheric entry segment is as fo...

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Abstract

The invention discloses a composite fast non-singular terminal sliding mode control method for an atmospheric entry section of a Mars probe, which specifically includes the following steps: firstly establishing a longitudinal motion dynamic model of the atmospheric entry section of the Mars probe affected by multi-source interference, and establishing a height based on the model The dynamic equation of the command tracking error; secondly, aiming at the dynamics of the altitude command tracking error, an extended state observer is designed to realize the asymptotic estimation of multi-source interference; again, a fast non-singular terminal sliding mode surface is designed based on the altitude tracking error information; finally, the interference estimation information is combined Design a composite fast non-singular terminal sliding mode controller. The invention ensures the continuity of the control quantity, eliminates the chattering phenomenon, has a faster convergence speed, and significantly improves the anti-interference performance of the system.

Description

technical field [0001] The invention belongs to the technical field of aerospace. Background technique [0002] Mars exploration is a part of deep space exploration, which has scientific significance such as in-depth exploration of the solar system and cosmic space, development and utilization of space resources, and expansion of human living space. The EDL process of Mars exploration includes the atmospheric entry stage (Entry), the dynamic descent stage (Descent) and the landing stage (Landing). In the EDL process of Mars, the atmospheric entry stage is the stage with the worst aerodynamic environment and has the greatest impact on the entire EDL process. The Mars rover's atmospheric entry segment has high flight speed and obvious dynamic nonlinear characteristics, and is also subject to multi-source interference such as internal aerodynamic parameter perturbation, model mismatch, friction and other unmodeled dynamics, external gust interference, and environmental uncertai...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 赵振华王寅生曹东孙春贞
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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