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Overall parameter design method for extraterrestrial celestial body penetrator

A design method and technology of overall parameters, applied in the aerospace field, can solve problems such as unseen penetrators

Pending Publication Date: 2022-03-04
SICHUAN AEROSPACE SYST ENG INST
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  • Application Information

AI Technical Summary

Problems solved by technology

At present, penetrators are all researched on a certain subsystem of the penetrator, such as structural configuration, high overload resistance, energy, guidance and control, etc., and there is no technology related to the overall design of the penetrator.

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  • Overall parameter design method for extraterrestrial celestial body penetrator

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Embodiment

[0024] The extraterrestrial penetrator mainly includes structural mechanism, electrical system, attitude control power system, thermal control system, detection load system, communication system and other subsystems.

[0025] The overall parameters of the extraterrestrial body penetrator include quality characteristic parameters, external dimension parameters, working hours, power characteristic parameters of each core component, and total thrust of the attitude control power system, etc. The design of the above overall parameters is determined by the input conditions and technical indicators of the penetrator, including the launch method of the penetrator, flight distance, mass and size constraints, penetration depth, space-soil force / thermal / electrical parameters, in-situ detection targets, communication mode etc. In the preliminary design process of the overall scheme of the penetrator, it is necessary to sort out the coupling relationship between various systems. This embo...

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Abstract

The invention discloses a general parameter design method for an extraterrestrial celestial body penetrator. The method comprises the following steps: determining design input parameters of the penetrator; detecting load mass, size, power, working time and data volume; communication module quality, size, communication time and power; the quality, the size, the working time and the power of the controller are controlled; thermal control power and thermal control power consumption; total capacity, mass and size of the battery pack; the penetration-level appearance parameters, the initial penetration speed and the penetration-level shell mass of the penetrator are determined; weight of a penetrator attitude control power system; the penetration device orbit control power total impulse, the penetration device orbit control power mass, the thrust deviation, the thrust line deflection and the thrust line transverse movement are determined; attitude control power total rushing; re-determining the weight of the penetrator attitude control power system according to the attitude control power total impulse; carrying out satellite soil penetrating process dynamics simulation; according to the invention, rapid design of the extraterrestrial celestial body penetrator can be realized.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a method for designing overall parameters of an extraterrestrial celestial body penetrator. Background technique [0002] As an important method of in-situ detection of the surface of extraterrestrial objects, penetrating detectors for extraterrestrial objects have been carried out by various space powers. At present, penetrators are all researched on a certain subsystem of the penetrator, such as structural configuration, high overload resistance, energy, guidance and control, etc., and there is no technology related to the overall design of the penetrator. Contents of the invention [0003] In order to solve the problems existing in the prior art, the object of the present invention is to provide a method for designing general parameters of an extraterrestrial celestial body penetrator, which can realize rapid design of the extraterrestrial celestial body penetrator. [0...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15
CPCG06F30/15
Inventor 杨宇彬钱成左易王鑫剑陈粤海郭芸芸邓李圣聂献东
Owner SICHUAN AEROSPACE SYST ENG INST