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An Adaptive Rapid Optimal Controller for Lunar Soft Landing Orbit

A controller and lander technology, applied in the aerospace field, can solve problems such as waste of fuel

Inactive Publication Date: 2019-10-11
ZHEJIANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

But inappropriate optimization algorithms lead to planning non-optimal trajectories, wasting a lot of fuel

Method used

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  • An Adaptive Rapid Optimal Controller for Lunar Soft Landing Orbit
  • An Adaptive Rapid Optimal Controller for Lunar Soft Landing Orbit
  • An Adaptive Rapid Optimal Controller for Lunar Soft Landing Orbit

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Embodiment Construction

[0065] The present invention is specifically described below with an example according to the accompanying drawings.

[0066] An adaptive fast optimization controller for lunar soft landing orbit, referring to image 3 , the track fast optimization controller consists of an optimization module, a simulation module, and an execution module; where:

[0067] 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):

[0068]

[0069] 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.

[0070] 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, rand...

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Abstract

The invention discloses a self-adaptive moon soft landing orbit rapid optimization controller. The orbit rapid optimization controller comprises a simulation module, an optimization module and an execution module. In the simulation module, a moon soft landing orbit is separated into a plurality of small segments, a thrust direction angle of each node of segmentation parts and a corresponding moment are utilized to obtain a thrust direction angle changing curve through fitting, and a whole soft landing orbit is obtained through soft landing kinetic model simulation. The optimal thrust direction angle and the optimal soft landing terminal moment of each node are obtained through optimization by the optimization module. The optimization module adopts an improved intelligent algorithm, an improved intelligent optimization method controls the size of a subgroup, adds disturbance factors, increases diversity of search, and improves convergence performance of the algorithm according to an inertia weight which is self-adaptively changes according to an evolution state The controller can rapidly obtain a moon soft landing orbit which enables fuel consumption to be minimum through optimization, and finally realize optimal control of the orbit.

Description

technical field [0001] The invention relates to the field of aerospace, in particular to an adaptive fast-optimizing controller for lunar soft landing orbit. Background technique [0002] When conducting unmanned lunar surface exploration or manned missions to the moon, it is necessary to make the lander achieve a soft landing on the lunar surface to ensure the safety of instruments, equipment and astronauts. In a typical lunar soft landing process, the descent from the orbit around the moon to the surface of the moon can be mainly divided into two stages: the Hohmann transfer stage and the power descent stage. Among them, the Hohmann transfer section means that the lander enters the elliptical orbit around the moon from the mooring orbit through the Hohmann orbit, and runs to the perilunar point; the power decline section refers to the engine braking of the lander from the perilunar point to offset the horizontal speed. And finally landed on the moon at a slower speed. Du...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
Inventor 刘兴高蒋雅萍
Owner ZHEJIANG UNIV