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Intelligent lunar soft landing orbit controller

A controller, soft landing technology, used in the aerospace field

Inactive Publication Date: 2017-09-26
ZHEJIANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The current optimization method does not guarantee that the optimal solution can be obtained, so there is still a lot of room for exploration in the lunar soft landing orbit control problem

Method used

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Experimental program
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Embodiment Construction

[0055] The present invention is specifically described below with an example according to the accompanying drawings.

[0056] An intelligent lunar soft landing orbit controller, referring to image 3 , the track controller consists of an optimization module, a simulation module, and an execution module; where:

[0057] refer to figure 1 , the simulation module divides the lunar soft landing orbit into n small segments, let n be 9 in this example, and input the value of n into the optimization module. The time of each node is obtained by formula (1):

[0058]

[0059] Among them, t k is the moment of the k+1th node, k=0,1,...,9, t 0 is the initial time, remember t 0 =0.

[0060] The optimization module combines the thrust direction angle ψ of the 10 nodes including the initial node and the final node with the soft landing terminal time t f as a parameter to be optimized. The initial population size is N s The particle swarm, randomly generate the initial position x ...

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Abstract

The invention discloses an intelligent lunar soft landing orbit controller. The orbit controller comprises a simulation module, an optimizing module and an execution module, wherein in the simulation module, the lunar soft landing orbit is divided into a plurality of segments, a thrust direction angle changing curve of the orbit is fitted by aid of thrust direction angles of nodes at segmentation and corresponding moments, and then the whole soft landing orbit is obtained through simulation of a soft landing dynamic model. The optimal thrust direction angles of the nodes and the optimal soft landing terminal moment are obtained through optimizing of the optimizing module. The optimizing module adopts an improved intelligent algorithm, the improved intelligent optimizing method controls the size of subgroups, disturbance factors are added, searching variety is improved, and the optimizing module has very high searching capacity and can search a lunar soft landing orbit requiring the least fuel consumption through optimizing. An optimal soft landing command signal is transmitted to the execution module, and the optimal lunar soft landing control requiring the least fuel consumption is realized finally.

Description

technical field [0001] The invention relates to the aerospace field, in particular to an intelligent moon soft landing orbit controller. Background technique [0002] my country's lunar exploration project was launched in 2004. According to the basic principles of carrying out the lunar exploration project, the lunar exploration project will be implemented in three stages: "circling", "falling" and "returning". In the two stages of "falling" and "returning", implementing a soft landing on the surface of the moon is a key technology and an important prerequisite for lunar exploration. Since there is no atmosphere on the surface of the moon, the speed of the lander must be completely offset by the braking engine to safely achieve a soft landing. This process consumes a lot of fuel. So it is necessary to optimize the design of this process. [0003] The methods for solving the lunar soft landing orbit problem can be divided into two categories: indirect method and direct meth...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04G05B17/02G06F17/50
CPCG05B13/042G05B17/02G06F30/20
Inventor 刘兴高蒋雅萍
Owner ZHEJIANG UNIV
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