An Optimal Control Method for Mars Landing Trajectory Based on Convex Optimization

A control method and trajectory optimization technology, applied in the direction of adaptive control, general control system, control/regulation system, etc., can solve problems such as unclear convergence of algorithms, achieve the effect of reducing drift and avoiding cumulative errors

Active Publication Date: 2020-11-10
SHANGHAI JIAOTONG UNIV
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Problems solved by technology

However, when the convergence of related algorithms is unclear, the real-time airborne nonlinear programming solution obtained by general iterative algorithms may not be the desired result

Method used

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  • An Optimal Control Method for Mars Landing Trajectory Based on Convex Optimization
  • An Optimal Control Method for Mars Landing Trajectory Based on Convex Optimization
  • An Optimal Control Method for Mars Landing Trajectory Based on Convex Optimization

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Embodiment

[0067] Such as figure 1 As shown, a Mars landing trajectory optimization control method based on convex optimization, the method includes the following steps:

[0068] (1) Establish a Mars landing dynamics model and perform convex optimization;

[0069] (2) Perform a single offline optimization with the goal of fuel optimization to obtain the nominal trajectory;

[0070] (3) The model predictive control in the rolling time domain is used to track the nominal trajectory to complete the landing control.

[0071] Step (1) The Mars landing dynamics model is specifically:

[0072]

[0073]

[0074]

[0075] T c (t)=(nTcosφ)e,

[0076]

[0077] where r ∈ IR 3 , v ∈ IR 3 ,T c ∈IR 3 , r is the position vector of the spacecraft relative to the target point, v is the velocity vector of the spacecraft in the ground fixed coordinate system, T c (t) is the thrust vector received by the spacecraft, T is the thrust produced by each sub-thruster of the spacecraft, IR 3 I...

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Abstract

The present invention relates to a Mars landing track optimization control method based on convex optimization. The method comprises the following steps of: (1) establishing a Mars landing dynamical model and performing convex optimization; (2) taking fuel optimization as a target to perform single off-line optimization to obtain a nominal track; and (3) employing a moving horizon model to performprediction and control to perform track of the nominal track to complete landing control. Compared to the prior art, the convex optimization and the moving horizon model prediction and control are effectively combined to effectively reduce the accumulated errors caused by modeling errors and interferences and improve the landing precision.

Description

technical field [0001] The invention relates to a Mars landing trajectory optimization control method, in particular to a Mars landing trajectory optimization control method based on convex optimization. Background technique [0002] In recent years, with the continuous improvement of science and technology, people's demand for space resources has ushered in a peak period, and the interest in Mars exploration has been rekindled. In this context, issues such as precise landing of manned aircraft have become more and more important. more important. In the field of aviation, the problem that an aerospace lander accurately lands on a given target location with an error of less than a few hundred meters under guidance is called a precision landing problem, and trajectory optimization is a key technology in precision landing. [0003] In order to ensure a safe landing on Mars, it is necessary to comprehensively consider the scientific research value of each site and the overall t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 贾泽华张卫东陆宇孙志坚张国庆赵亚东
Owner SHANGHAI JIAOTONG UNIV
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