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Rocket boosting section trajectory optimization method based on particle swarm optimization

A particle swarm algorithm and optimization method technology, which is applied in design optimization/simulation, calculation, calculation model and other directions, and can solve problems such as few parameters

Pending Publication Date: 2022-03-01
BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The particle swarm optimization algorithm is also an optimization tool based on iteration, but there is no operation such as selection, crossover, and mutation in the algorithm implementation process, and it has the advantages of few parameters to be set, fast convergence speed, and easy implementation. Applications in the field are gaining more and more attention

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  • Rocket boosting section trajectory optimization method based on particle swarm optimization
  • Rocket boosting section trajectory optimization method based on particle swarm optimization
  • Rocket boosting section trajectory optimization method based on particle swarm optimization

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Embodiment Construction

[0023] Various exemplary embodiments, features, and aspects of the present disclosure will be described in detail below with reference to the accompanying drawings. The same reference numbers in the figures indicate functionally identical or similar elements. While various aspects of the embodiments are shown in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.

[0024] The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as superior or better than other embodiments.

[0025] In addition, in order to better illustrate the present disclosure, numerous specific details are given in the following specific implementation manners. It will be understood by those skilled in the art that the present disclosure may be practiced without some of the specific details. In some instances, methods, means, componen...

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Abstract

The invention discloses a rocket boosting section trajectory optimization method based on a particle swarm algorithm. The method comprises the following steps: establishing a three-degree-of-freedom motion model of a rocket boosting section trajectory according to motion parameters of a rocket boosting section; constructing a rocket boosting section flight program angle model according to the rocket boosting section three-degree-of-freedom motion model; establishing a rocket boosting section trajectory optimization model based on the rocket boosting section flight program angle model; and based on a particle swarm algorithm and the preset initial value of the rocket, calculating to obtain an optimal solution of the rocket boosting section trajectory optimization model. The solid carrier rocket trajectory optimization design problem can be effectively solved, the consumption of the last boosting stage liquid propellant is reduced by 11.1%, the convergence speed is high, the number of configuration parameters is small, and engineering implementation is easy.

Description

technical field [0001] The disclosure belongs to the technical field of ballistic optimization, and in particular relates to a particle swarm algorithm-based ballistic optimization method for booster section of a rocket. Background technique [0002] Ballistic optimization is an important part of the overall optimal design of solid launch vehicles, and plays an extremely important role in the entire life cycle of the launch vehicle. In the actual flight trajectory design stage, trajectory optimization design can effectively improve the quality of payloads entering orbit and reduce launch costs. As the trajectory optimization design of the ascent section of solid launch vehicles is a complex nonlinear programming problem, there are many equality constraints and inequality constraints, and the constraint conditions and objective functions often have no clear analytical expressions, which makes traditional optimization algorithms face severe challenges. Unable to maximize the ...

Claims

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Application Information

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IPC IPC(8): G06F30/20G06N3/00G06F119/14
CPCG06F30/20G06N3/006G06F2119/14
Inventor 张敏刚王永海徐春铃付秋军巩英辉姜智超杨丁刘辉孙精华杨缙曹轶王锦涛冯建林闫颖鑫陈志刚刘明刘建辉杨明张宁宁
Owner BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST