Calculation method for evaluating intersection between carrier rocket and space target before launching

A technology for launch vehicles and space targets, which is applied in the calculation field for rendezvous evaluation of launch vehicles and space targets before launch, can solve problems such as difficulty in meeting high timeliness and high precision requirements, and achieve high timeliness and high precision effects

Active Publication Date: 2021-06-04
中国人民解放军63768部队
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  • Abstract
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AI Technical Summary

Problems solved by technology

If the traditional spacecraft collision assessment method is still used to carry out the rendezvous assessment before the launch of the launch vehicle, it is difficult to meet the requirements of high timeliness and high precision

Method used

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  • Calculation method for evaluating intersection between carrier rocket and space target before launching
  • Calculation method for evaluating intersection between carrier rocket and space target before launching
  • Calculation method for evaluating intersection between carrier rocket and space target before launching

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Embodiment

[0029]It is set that a carrier rocket will be launched from the Baiknur launch site on December 26, 2020. The maximum altitude of the rocket is 660 kilometers, the flight time is 607 seconds, and the launch window is from 12:00 to 12:30 Beijing time. Assuming that the safety threshold of the rendezvous distance between the launch vehicle and the space target is 20 kilometers, the catalog data of the space target is selected from the number of TLEs published on the SPACE-TRACK website of the United States Alliance Space Operations Center on December 26, 2020, a total of 20,578. The flight altitude of the rocket changes with time as figure 1 shown;

[0030] Using the calculation method of the present invention, the rendezvous evaluation is carried out for the launch vehicle and the space target before launch. During the launch window from 12:00 to 12:30 on December 26, 2020, the rendezvous evaluation results are shown in Table 1:

[0031] Table 1 Safe launch window period for r...

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Abstract

The invention discloses a calculation method for evaluating rendezvous between a carrier rocket and a space target before launching. The method comprises the following steps: in a given launch window time period, screening a calculation method of a safe launch window time meeting a condition, wherein the screening condition is that an intersection distance between a carrier rocket and all space targets is smaller than a given safety threshold. The invention provides a calculation method for carrying out rendezvous evaluation with a space target by utilizing a theoretical flight path of a carrier rocket before launching according to the theoretical flight path characteristics of the carrier rocket and the on-orbit operation rule of the space target. According to the method, the requirements of high timeliness and high precision of rendezvous evaluation of the carrier rocket and the space target before launching are effectively met.

Description

technical field [0001] The invention relates to the field of aerospace measurement and control, in particular to a calculation method for evaluating the rendezvous between a carrier rocket and a space target before launch. Background technique [0002] With the accelerated development of human spaceflight and the increasingly intense space activities, the number of space objects in orbit (spacecraft, rocket bodies and space debris, etc.) is increasing, and the space debris environment has a tendency to deteriorate further. As of December 2020, the SPACE-TRACK website of the United States Alliance Space Operations Center announced that the total number of trackable space targets in orbit is close to 21,000. According to statistics, there are more than 100,000 space objects with a diameter greater than 1 cm in orbit, and millions of tiny fragments with a diameter of less than 1 cm. The sharp increase in the number of space targets has significantly increased the risk of colli...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20G06Q10/06
CPCG06F30/20G06Q10/0639
Inventor 赵治崔文张炜罗朗马鑫陈治科卢欣王梁
Owner 中国人民解放军63768部队
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