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Continuous low-thrust high-orbit target orbital transfer approaching method and system

A technology with small thrust and target, which is applied in the directions of space navigation vehicle guidance devices, space navigation equipment, space navigation vehicles, etc., can solve the problem of not considering the relative position relationship, etc., and achieve the effect of strong practicability

Active Publication Date: 2021-11-12
SHANGHAI SATELLITE ENG INST
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This method does not consider the relative position relationship with the target after the phase modulation is over, as well as the lighting conditions

Method used

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  • Continuous low-thrust high-orbit target orbital transfer approaching method and system
  • Continuous low-thrust high-orbit target orbital transfer approaching method and system
  • Continuous low-thrust high-orbit target orbital transfer approaching method and system

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Embodiment Construction

[0045]The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0046] figure 1 It is a flow chart of a regional multi-target satellite detection simulation method of the present invention; as figure 1 As shown in the example, the process includes:

[0047] Step S1: Calculate the inclination vector and adjust the velocity increment of the inclination vector to determine the approach type;

[0048] Calculate the inclination vector i of the target star and the approaching star x = sin i sin Ω, i y =sin i cosΩ, if the inclination vector i x ,i y If they are consis...

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Abstract

The invention provides a continuous low-thrust high-orbit target orbital transfer approaching method and system. The continuous low-thrust high-orbit target orbital transfer approaching method comprises the following steps that S1, calculating an inclination angle vector and adjusting the speed increment of the inclination angle vector to judge the approaching type; s2, solving a continuous low-thrust orbital transfer strategy by adopting an in-plane phase modulation mode for coplanar approaching; s3, for different-plane small-dip-angle approaching, calculating a low-thrust orbital transfer strategy in the mode that the orbital plane is adjusted firstly and then in-plane phase modulation is used; and S4, and calculating a low-thrust orbital transfer strategy by approaching a target at an ascending / descending intersection point for different-plane large-dip-angle approaching. According to the method, the problems of coplanar approaching, different-plane small-dip-angle approaching and different-plane large-dip-angle continuous low-thrust approaching of the high-orbit target are effectively solved.

Description

technical field [0001] The invention relates to the field of orbit design and optimization of spacecraft, in particular to a method and system for approaching a high-orbit target with continuous low-thrust orbit change. Background technique [0002] When a satellite encounters a failure in orbit, it is difficult for ground personnel to intervene and adjust, or even determine what kind of failure has occurred. This puts high demands on on-orbit service and support. If the satellite has a strong ability to change orbit, it can conduct close observation of the service satellite to locate the problem. However, traditional chemical propulsion needs to consume more fuel, and service satellites cannot provide long-term on-orbit service capabilities. Electric propulsion engines have become a better choice. The electric propulsion engine has a high specific impulse, which can save a lot of fuel. [0003] In the Chinese patent document with the notification number CN105607478B, a me...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
CPCB64G1/242Y02T90/00
Inventor 陈占胜宋君强郑艺裕袁双朱晨聪仲惟超夏时宇邓武东
Owner SHANGHAI SATELLITE ENG INST
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