A rendezvous method for any point on a space tumbling target

An arbitrary point and target technology, applied to space navigation equipment, space navigation vehicles, space navigation equipment, etc., can solve problems such as complex models and no analytical solutions

Active Publication Date: 2019-12-31
NORTHWESTERN POLYTECHNICAL UNIV
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  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the model established by it is complex and there is no analytical solution

Method used

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  • A rendezvous method for any point on a space tumbling target
  • A rendezvous method for any point on a space tumbling target
  • A rendezvous method for any point on a space tumbling target

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Embodiment Construction

[0049] see figure 1 , the invention discloses a rendezvous method for any point on a space tumbling target, comprising the following steps:

[0050] The first step is to establish a coupling model of any two relative motions.

[0051] First, establish the target spacecraft orbital coordinate system between the center of mass of the target spacecraft and the center of mass of the tracking spacecraft The relative translational equation under, where For definition see image 3 , whose expression is:

[0052]

[0053] in, is the position vector of the target spacecraft, and denote the perturbation accelerations of the target spacecraft and the tracking spacecraft, respectively, To track the control acceleration of the spacecraft. is the angular velocity vector of the relative motion coordinate system relative to the earth-centered inertial coordinate system, ω t Yes the mold, means ω t Derivative with respect to time t, x, y, z are relative position compone...

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Abstract

The present invention discloses a rendezvousing method for arbitrary points on space rollover targets. The invention aims to build a relative motion equation for arbitrary points on space rollover targets. According to the method, the relative motion coupling model of an arbitrary point on a target aircraft and an arbitrary point on a tracking aircraft is established on the basis of the relative translation equation and relative rotation equation of the centroid of the target aircraft and the centroid of the tracking aircraft so as to better describe the relative motion of the target aircraft and the tracking aircraft; the model is simplified, so that an analytical solution and a state transition matrix can be obtained; and a relative motion differential equation is utilized to perform forward trajectory design, or the state transition matrix is utilized to perform inverse trajectory design, and therefore, a rendezvousing trajectory satisfying requirements can be obtained. With the rendezvousing method of the invention adopted, the rendezvousing trajectory of two arbitrary points on the target aircraft and the tracking aircraft can be realized, and requirements of general relative trajectory design can be satisfied; and the reliability of the method of the present invention is illustrated by a simulation example.

Description

technical field [0001] The invention belongs to the technical field of space rendezvous, and in particular relates to a rendezvous method for any point on a space tumbling target. Background technique [0002] With the deepening of human exploration, development and utilization of outer space, many space missions involve non-cooperative targets, and the attitude control system of such targets is usually disabled and there is no special device for docking. In order to ensure safe and reliable docking, what is often needed during rendezvous is a relative motion model that can describe any point to any point. [0003] The problem of relative motion of spacecraft can also be called formation analysis problem for cooperative spacecraft, which mainly describes and analyzes the relative motion of spacecraft. The literature "Terminal guidance system for satelliteendezvous, Journal of the Aerospace Science", 1960" gives the classic relative motion equation of two spacecraft's close-...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 袁建平万文娅马卫华袁源张家巍
Owner NORTHWESTERN POLYTECHNICAL UNIV
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