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A preset performance control method without initial error sign for orbital intersection of translation point

A technology of initial error and orbit rendezvous, which is applied to space navigation equipment, motor vehicles, space navigation equipment, etc., and can solve problems such as the inability to provide speed measurement information.

Active Publication Date: 2022-03-01
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] Aiming at the problem that the speed measurement sensor fails to provide speed measurement information in the orbital intersection of the translation point, and the preset performance control method needs to predict the cumbersome operation of the initial error sign, a new method that only requires relative position information and the initial error sign is unknown Translation point orbit proximity rendezvous control law, used to realize high-precision real-time control of the rendezvous mission between the tracking spacecraft and the target spacecraft

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  • A preset performance control method without initial error sign for orbital intersection of translation point
  • A preset performance control method without initial error sign for orbital intersection of translation point
  • A preset performance control method without initial error sign for orbital intersection of translation point

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Embodiment Construction

[0078] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0079] Based on a high-order integral chain observer and preset performance control, the present invention proposes an autonomous rendezvous control method of a translation point track that only requires relative position measurement information, and verifies the effectiveness of the proposed method by examples. The implementation of this invention mainly comprises following four steps:

[0080] Step 1: Establish a nonlinear translation point-orbit relative dynamics model

[0081] The circular restricted three-body problem describes two main celestial bodies P 1 ,P 2 Make a circular motion around their common center of mass, and analyze the third spacecraft P with negligible mass 3 Motion problems in this system. with P 1 ,P 2 The center of mass O is the origin, and the two main celestial bodies P 1 ,P 2 The connecting line of is the x-axis, the positive ...

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Abstract

The invention relates to a preset performance control method that does not require an initial error sign for the intersection of translation point orbits, including: establishing a nonlinear translation point orbit relative dynamics model, establishing a disturbance and uncertainty model, and designing a third-order integral chain differentiator The design of preset performance control law for orbital rendezvous at the horizontal translation point; the proposed preset performance control method based on the third-order integral chain differentiator can guarantee the system state at the end of the rendezvous in the case of disturbance, relative navigation error and thruster failure Satisfying the actual preset performance means that the safe and precise rendezvous between the tracking spacecraft and the target spacecraft can be realized, which provides a feasible control strategy for future translation point orbit rendezvous missions.

Description

technical field [0001] The invention belongs to the technical field of autonomous rendezvous of deep-space spacecraft, and relates to an autonomous control method for orbital rendezvous of a translation point based on a third-order integral chain differentiator with missing velocity information and unknown initial error sign of a controller. Background technique [0002] In recent years, with the deepening of research on the dynamic properties of translation points, translation point orbits have shown great application prospects. Countries around the world have launched and are planning multiple translation point observation platforms and manned space stations. The cost of these large spacecraft is high, and it will be too expensive to abandon them directly if they fail. Therefore, it is necessary to study the rendezvous and docking of the translation point orbiting spacecraft It is crucial for the interception, repair and rescue of spacecraft near the orbit of the translati...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24
CPCB64G1/242
Inventor 罗建军郑丹丹殷泽阳党朝辉王明明马卫华
Owner NORTHWESTERN POLYTECHNICAL UNIV
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