Near-earth minor planet rendezvous task orbit optimization method based on hybrid power

A technology of hybrid, optimization methods, applied in the direction of constraint-based CAD, multi-objective optimization, design optimization/simulation, etc., can solve problems such as low feasibility and high cost

Active Publication Date: 2020-12-01
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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Problems solved by technology

However, the current multi-planet rendezvous detection has the defects of high cost and low feasibility. Therefore, how to solve th

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  • Near-earth minor planet rendezvous task orbit optimization method based on hybrid power
  • Near-earth minor planet rendezvous task orbit optimization method based on hybrid power
  • Near-earth minor planet rendezvous task orbit optimization method based on hybrid power

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[0044] In order to make the purposes, technical solutions and points of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only It is a part of the embodiments of this application, not all of them. The components of the embodiments of the application generally described and illustrated in the figures herein may be arranged and designed in a variety of different configurations. Accordingly, the following detailed description of the embodiments of the present application provided in the accompanying drawings is not intended to limit the scope of the claimed application, but merely represents selected embodiments of the present application. Based on the embodiments of the present application, all other embodiments obtained by those skilled in th...

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Abstract

The invention relates to a near-earth asteroid rendezvous task orbit optimization method based on hybrid power. The orbit optimization method comprises the following steps: establishing an asteroid detector kinetic model of solar pressure and solar photovoltaic hybrid propulsion power; an asteroid detection orbit optimization method is designed based on physical planning and a Gaussian pseudo-spectral method. The method has the advantages that a physical planning framework is adopted, and the multi-objective orbit optimization problem can be converted into a single-objective optimization problem reflecting the preference of a designer. An iterative optimization strategy based on a Gaussian pseudo-spectral method can effectively solve the problem of initial values of multiple variables in rendezvous orbit optimization. A multi-objective optimization simulation result shows that the hybrid small-row detector can generate different orbital forms to realize the minimum fuel consumption andthe shortest flight time. Simulation also shows that the task period of the hybrid power detector for continuously crossing the four near-earth asteroids is about five years, and is saved by about one and a half years compared with a solar sail detector for completing the same crossing task.

Description

technical field [0001] The invention relates to the technical field of near-Earth asteroid detection, in particular to a method for optimizing the orbit of a near-Earth asteroid probe rendezvous mission based on hybrid power. Background technique [0002] Near-Earth asteroid detection is of great significance to the study of the origin of the solar system. In addition, near-Earth asteroids are also in danger of colliding with the earth. In order to remove the potential danger of being collided, many countries have carried out asteroid detection research in recent years; Even a number of continuous asteroid detection plans and near-Earth asteroid observation missions have been proposed, so as to improve the understanding of near-Earth asteroids and eliminate the threat of collision to the earth. However, the current multi-planet rendezvous detection has the defects of high cost and low feasibility. Therefore, how to solve the problems existing in multi-planet rendezvous throu...

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Application Information

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IPC IPC(8): G06F30/20G06F30/15B64G1/24G06F119/14G06F111/10G06F111/04G06F111/06
CPCG06F30/20G06F30/15B64G1/242G06F2119/14G06F2111/10G06F2111/04G06F2111/06B64G1/245Y02T90/00
Inventor 雍恩米刘滔郑凤麒
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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