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Spacecraft different-plane orbital transfer trajectory planning method

A trajectory planning, spacecraft technology, applied in the direction of aerospace vehicles, aerospace vehicle guidance devices, aircraft, etc.

Active Publication Date: 2021-01-08
BEIHANG UNIV +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Purpose of the invention: The purpose of the present invention is to provide a trajectory planning method for spacecraft different-plane orbit changes to solve the problem of space vehicle trajectory planning for different-plane orbit changes, so that the spacecraft can enter the circle with the largest orbital radius in the event of a failure. track

Method used

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  • Spacecraft different-plane orbital transfer trajectory planning method
  • Spacecraft different-plane orbital transfer trajectory planning method
  • Spacecraft different-plane orbital transfer trajectory planning method

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Embodiment

[0028] like figure 1 As shown, the present invention provides a method for planning orbits of different planes of a spacecraft, the method comprising the following steps:

[0029] (1) Step 1: Obtain the corresponding parameters of the trajectory planning method according to the actual parameters of the spacecraft and the mission situation;

[0030] (2) Step 2: Establish a convex optimization problem for spacecraft orbit change;

[0031] (3) Step 3: Given the initial guess, the model compensation method is used to iteratively solve the convex optimization problem of the spacecraft's orbit change in different planes;

[0032] The "actual parameters and mission conditions of the spacecraft" described in step 1 are specifically:

[0033] The maximum thrust T of the spacecraft, the initial mass of the spacecraft m 0 , the second consumption of the spacecraft Δm, the flight time of the spacecraft t f .

[0034] The "corresponding parameters of the trajectory planning method" de...

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Abstract

The invention provides a spacecraft different-plane orbital transfer trajectory planning method, which comprises the following steps of: 1, obtaining corresponding parameters of a trajectory planningmethod according to actual parameters and task conditions of a rocket; 2, establishing a convex optimization problem under the rocket fault condition; and 3, giving an initial conjecture, and iteratively solving a convex optimization problem under the rocket fault condition by adopting a model compensation method. By means of the steps, the near-circular orbit planning method based on convex optimization under the rocket fault condition can effectively solve the problem of rocket orbit injection under the fault condition, and a circular orbit with the largest radius into which a rocket can enter and a corresponding track can be quickly generated within a certain period of time; the method is scientific and good in manufacturability and has wide application and popularization value.

Description

technical field [0001] The invention provides a trajectory planning method for a spacecraft changing orbits in different planes, and belongs to the technical field of trajectory planning in aerospace technology. Background technique [0002] In recent years, with the increasing development of science and technology, the demand for satellite launch resources is increasing. Therefore, the spacecraft is required to have online autonomous trajectory planning capabilities, so as to reduce the workload of mission design before the launch of the spacecraft, reduce the launch cycle, and improve the success rate of the mission. For the traditional launch mode, a lot of pre-mission design work is required, and it is difficult to deal with flight trajectory deviation and some emergencies after launch. For the traditional control method of spacecraft orbit change in different planes, it cannot plan the trajectory of the spacecraft. When the spacecraft trajectory deviates greatly from t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
CPCB64G1/242
Inventor 张冉郝泽明李惠峰师鹏程晓明禹春梅
Owner BEIHANG UNIV