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Autonomous self-adaptive remote guidance method and system for space rendezvous interception

A space rendezvous, self-adaptive technology, used in transportation and packaging, space navigation vehicle guidance devices, space navigation equipment, etc.

Active Publication Date: 2021-06-25
BEIJING INST OF CONTROL ENG
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Problems solved by technology

[0008]Technical problem solving of the present invention: overcome the deficiencies of the prior art, provide a space rendezvous and intercept autonomous self-adaptive long-distance guidance method and system, aim at solving the existing Lambert Problems in the guidance scheme to meet the mission requirements of autonomy, adaptability and high-precision guidance for future space maneuvers

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Embodiment Construction

[0063] In order to make the objects, technical solutions, and advantages of the present invention, the embodiments disclosed in the present invention will be further described in detail with reference to the accompanying drawings.

[0064] The present invention discloses a spatial intersection to intercept independent adaptive remote guidance scheme, and one of its core ideas is that real-time closed-loop guidance is performed based on speed gain guidance principles, introducing earth gravitational self-compensation, based on predicted shutdown point status Control, rail control adaptive estimation, independent choice of shutdown conditions, etc., solve the problem of finite thrust independent guidance and traditional method rail precision, and stiffness changes. This program can be applied to the remote rendezvous task of various space aircraft to meet the spatial motor platform full self-autonomous, adaptive, high reliability, high-precision remote guidance task requirements.

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Abstract

The invention discloses an autonomous self-adaptive remote guidance method and system for space rendezvous interception. The method comprises the steps of carrying out the primary calculation according to flight parameters, and obtaining a primary speed calculation result; meanwhile, obtaining an orbit control acceleration aT; according to the primary speed calculation result and the orbit control acceleration aT, calculating to obtain a predicted ideal shutdown point position rK; performing secondary calculation according to the predicted ideal shutdown point position rK to obtain a secondary speed calculation result; performing guidance target correction according to the predicted ideal shutdown point position rK and the secondary speed calculation result, obtaining a corrected guidance target, performing tertiary calculation according to the corrected guidance target, and obtaining a tertiary speed calculation result; and carrying out self-adaptive remote guidance control according to the tertiary speed calculation result. The invention aims to solve the problems of the existing Lambert guidance scheme so as to meet the task requirements of autonomy, adaptivity and high-precision guidance of future space maneuver.

Description

Technical field [0001] The present invention belongs to the high-precision technical field of space mobile platform, in particular to a space intersection intercepted self-adaptive remote guidance method and system. Background technique [0002] The current space deliberation interception is mostly nominal guidance schemes, ground testing, and formulating rail policies, and spacecraft performs program rails according to the on-argument. Nominally guided autonomous and anti-interference ability, the task is time-free, and the autonomous and rapid needs of space machine tasks cannot be adapted. Lambert guidance can realize the self-defined remote guidance of space intersection, but it is still facing the following questions: [0003] (1) There is a long time to transfer a large-scale track transfer, and the Lambert guidance is based on the biocomy model, and the Earth gravitational model error (mainly J2) has a greater impact on the accuracy of the rail control; [0004] (2) If the...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
CPCB64G1/244B64G1/245
Inventor 黄盘兴刘磊汤亮石恒马雪
Owner BEIJING INST OF CONTROL ENG
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