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Relative orbit design and high-precision posture pointing control method aiming at space non-cooperative target

A non-cooperative target, relative orbit technology, applied in the field of relative orbit design and high-precision attitude pointing control, can solve the problems of difficult orbit control, affecting attitude pointing accuracy, etc. Effect

Active Publication Date: 2015-05-27
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention aims to solve the problems in the prior art that the orbit control is difficult when the tracking position range is limited, and the attitude pointing accuracy is affected during the orbit attitude coupling control, and provides a relative orbit design and high-precision attitude pointing control method for space non-cooperative targets

Method used

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  • Relative orbit design and high-precision posture pointing control method aiming at space non-cooperative target
  • Relative orbit design and high-precision posture pointing control method aiming at space non-cooperative target
  • Relative orbit design and high-precision posture pointing control method aiming at space non-cooperative target

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specific Embodiment approach 1

[0043] Specific implementation mode one: the relative orbit design and the high-precision attitude pointing control method for space non-cooperative target spacecraft of the present embodiment, it is realized according to the following steps:

[0044] 1. The design of the skimming trajectory of the tracking spacecraft relative to the non-cooperative target spacecraft in space;

[0045] 2. The design of the transfer trajectory of the tracking spacecraft relative to the non-cooperative target spacecraft in space;

[0046] 3. The attitude controller design of the tracking spacecraft relative to the space non-cooperative target spacecraft, that is, the relative orbit design and high-precision attitude pointing control method for space non-cooperative targets have been completed.

[0047]x, y, z: position components in the relative orbital coordinate system;

[0048] the velocity component in the relative orbital coordinate system;

[0049] r 0 : The relative position of the e...

specific Embodiment approach 2

[0062] Specific embodiment two: the difference between this embodiment and specific embodiment one is: the design of the flying trajectory in the step one is specifically:

[0063] 1. Establish the relative position relationship between space non-cooperative targets and the spacecraft in the relative motion coordinate system of the Hill equation. Based on the relative motion coordinate system of the Hill equation, select the appropriate entry point A information and departure point B information of the spacecraft in the relative motion based on the Hill equation. In the motion coordinate system, such as figure 1 Shown e=[e 1 ; e 2 ; e 3 ] is the sight direction vector e of the non-cooperative target hill The unit vector of e i (i=1,2,3) is the component in the relative motion coordinate system of the hill equation; the line of sight direction e hill The range of distance between the target spacecraft and the tracking spacecraft determines the allowable skimming range of t...

specific Embodiment approach 3

[0100] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is:

[0101] Orbit Transfer Optimization Algorithm

[0102] 1. Transformation of nonlinear programming problems

[0103] Assuming that there are N speed pulse points in the whole orbital transfer process (the start point and the end point are two fixed pulse points), define △t i is the time interval between the i-th speed pulse point and the i+1-th speed pulse point, t f is the total transfer time.

[0104] From the previous analysis, the following expression can be obtained:

[0105] r · ti - = Φ 21 ( Δt i ...

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Abstract

The invention discloses a relative orbit design and high-precision posture pointing control method aiming at a space non-cooperative target, and relates to a relative orbit design and a high-precision posture pointing control method. The problems that the orbit control is difficult and the posture pointing precision is influenced in orbit posture coupling control when the track position is limited in the prior art are solved. The method comprises the following steps: tracking a flying over track design of a relative space non-cooperative target spacecraft of a spacecraft; tracking a shifting track design of the relative space non-cooperative target spacecraft of the spacecraft; and tracking a posture controller design of the relative space non-cooperative target spacecraft of the spacecraft, namely, finishing the relative orbit design and the high-precision posture pointing control method aiming at the space non-cooperative target. The method disclosed by the invention is applied to the field of the space spacecrafts.

Description

technical field [0001] The invention relates to a relative track design and a high-precision attitude and pointing control method. Background technique [0002] The development of space technology has gradually been upgraded from space utilization to space control, and the research on issues such as on-orbit services, interference, and space strikes has attracted more and more attention and attention from all aerospace powers. The short-distance tracking of space targets is the premise and basic guarantee for many space technology issues such as on-orbit service, space rescue, energy transmission, and tracking and monitoring. , including space debris, invalid aircraft, and enemy aircraft, etc.), many issues such as tracking, jamming, and strikes further reflect the importance of spacecraft control. With the enhancement of spacecraft mobility, the accuracy and range of tracking and monitoring The requirements are getting higher and higher, and the difficulty of interference ...

Claims

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Application Information

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IPC IPC(8): G05D1/10G05D1/08
Inventor 孙延超凌惠祥马广富李传江李卓董振
Owner HARBIN INST OF TECH
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