Method and device for controlling prober to land on object outside earth

A detector and detector ring technology, applied in the aerospace field, can solve problems such as large landing deviation of detectors

Active Publication Date: 2019-08-09
中国人民解放军63920部队
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The embodiment of the present application provides a method and device for controlling the landing of a probe on a...

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  • Method and device for controlling prober to land on object outside earth
  • Method and device for controlling prober to land on object outside earth
  • Method and device for controlling prober to land on object outside earth

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Embodiment Construction

[0050] In order to solve the problem of relatively large landing deviation of the probe in the prior art, the embodiments of the present application provide a method and device for controlling the landing of the probe on an extraterrestrial body.

[0051] The preferred embodiments of the application will be described below in conjunction with the accompanying drawings. It should be understood that the preferred embodiments described here are only used to illustrate and explain the application, and are not used to limit the application, and in the absence of conflict, the application The embodiments and the features in the embodiments can be combined with each other.

[0052] In order to facilitate understanding of the application, in the technical terms involved in the application:

[0053] Extraterrestrial celestial bodies refer to celestial bodies other than the earth, such as the moon and Mars.

[0054] The orbital inclination refers to the angle between the orbital plane ...

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Abstract

The invention discloses a method and device for controlling a prober to land on an object outside the earth, and belongs to the technical field of spaceflight. The method comprises the steps that midcourse correction control parameters at set control points are determined according to the set height and the set orbit inclination when a target point is reached, a transfer orbit of the prober is controlled according to the midcourse correction control parameters, brake control parameters are determined according to the controlled transfer orbit and the set orbit semi-major axis, and the prober is controlled to conduct braking according to the brake control parameters; inbound pass control parameters are determined according to the braked orbit and target power lowering parameters, and the prober is controlled to conduct inbound pass according to the inbound pass control parameters; power lowering parameters are determined according to the orbit subjected to inbound pass, the landing deviation is determined according to the power lowering parameters and the target power lowering parameters, and the orbit inclination and/or the orbit semi-major axis are/is corrected according to the landing deviation; the landing position deviation is larger than the set position deviation, the step of determining the midcourse correction control parameters is executed; and when only the landing time deviation is larger than the set time deviation, the step of determining the brake control parameters is executed.

Description

technical field [0001] The present application relates to the field of aerospace technology, in particular to a method and device for controlling a probe to land on an extraterrestrial body. Background technique [0002] In the field of aerospace technology, the detection of extraterrestrial celestial bodies, such as lunar surface surveys, manned moon landings, and Mars landings, is of great significance to human activities. Due to limited conditions, the probe is generally required to land at a fixed point at a fixed time. [0003] Taking landing on the moon as an example, in practical applications, the flight process of the probe landing on the moon can be divided into the launch section, the earth-moon transfer section, the lunar orbit section, the power descent section, and the lunar surface working section. On the other hand, the full flight time and flight process of the probe are fixed. In the prior art, after the detector is put into orbit, if there is a deviation ...

Claims

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Application Information

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IPC IPC(8): B64G1/24
CPCB64G1/24B64G1/242
Inventor 刘勇李革非陈明郝大功马传令
Owner 中国人民解放军63920部队
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