Target selection method for flying over small celestial body from driven balance point track

A technology for target selection and small celestial bodies, applied in the aerospace field, it can solve the problems of difficulty in defining the target selection range and low calculation efficiency, and achieve the effects of rapid selection, small calculation amount and high efficiency

Inactive Publication Date: 2013-06-19
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention takes the orbit of the dynamic balance point as the starting point, overcomes the problems of low calculation efficiency and difficulty in defining the range of target selection

Method used

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  • Target selection method for flying over small celestial body from driven balance point track
  • Target selection method for flying over small celestial body from driven balance point track
  • Target selection method for flying over small celestial body from driven balance point track

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Embodiment Construction

[0016] The implementation of the method of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0017] In this embodiment, the time to fly over the small celestial body from the orbit of the dynamic balance point is from November 2012 to March 2013; the measurement and control communication distance during the flyover is limited to 10 million kilometers; Orbital ephemeris; probe imaging requires asteroids with a diameter greater than 1 km; target star library 470,000; the speed increment that the probe can provide is 100m / s; the orbit of the dynamic balance point is the Lissajous orbit at the L2 point of the sun and the earth , its x-direction and z-direction amplitudes are assumed to be 290,000 and 390,000 km, respectively.

[0018] A target selection method for flying over small celestial bodies starting from the orbit of the dynamic balance point, the basic process is as follows figure 1 As shown, the specific steps of th...

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Abstract

The invention relates to a target selection method for flying over a small celestial body, in particular to a target selection method for flying over the small celestial body from a driven balance point track and belongs to the technical field of aerospace. The method comprises: firstly, carrying out primary election on flyover targets according to timing constraint and measurement and control communication distance constraint; then, further carrying out screening on targets according to physical properties of small celestial bodies and detector flyover imaging constraint; and lastly, choosing out alternative targets according to speed increment constraint provided by a detector. The method carries out layered screening step by step on targets of a small celestial body star bank according to the mission time and the measurement and control communication distance constraint, the physical properties of small celestial bodies and the detector flyover imaging constraint, and at last estimates the speed increment, provides the alternative targets, can achieve fast choosing, and has the advantages of being little in calculated amount, high in efficiency and the like.

Description

technical field [0001] The invention relates to a method for selecting a target for flying over a small celestial body, in particular to a method for selecting a target for flying over a small celestial body starting from the orbit of a dynamic balance point, and belongs to the technical field of aerospace. Background technique [0002] Target selection is a key link in the design of small celestial body exploration missions. Among the developed target selection methods for deep space exploration, the prior art [1] (see LauC.O, HulkowerN.D.Accessibility of near-earth asteroids, Journal of Guidance, Control and Dynamics, 1987, 10:225-232) proposed a method based on the global optimal Two-pulse target approachability evaluation and selection method, that is, to evaluate the approachability of the target celestial body by solving the speed increment required for the optimal two-pulse transfer between the earth and the target celestial body, and then according to the total speed...

Claims

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Application Information

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IPC IPC(8): B64G99/00
Inventor 乔栋崔平远尚海滨朱圣英徐瑞
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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