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Graded low-power-consumption thermal control method of deep-space high-speed impactor

A technology for impactors with low power consumption, which can be applied to auxiliary controllers with auxiliary heating devices, devices for controlling the living conditions of spaceflight vehicles, and temperature control using electric methods, which can solve the weight limit and limited energy of impactors and other issues to achieve the effect of reducing power consumption

Active Publication Date: 2020-08-25
SHANGHAI SATELLITE ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to the weight limit of the impactor, the energy carried by itself is extremely limited, and the internal energy needs to focus on ensuring the operation of the impactor's functional realization devices

Method used

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  • Graded low-power-consumption thermal control method of deep-space high-speed impactor
  • Graded low-power-consumption thermal control method of deep-space high-speed impactor
  • Graded low-power-consumption thermal control method of deep-space high-speed impactor

Examples

Experimental program
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Effect test

Embodiment 1

[0037] A low-power hierarchical thermal control method for deep-space high-speed impactors. Based on the impactor thermal control and low power consumption requirements, different measures such as overall heating, module temperature control, and chip-level temperature control are used for different stages of the impactor mission cycle. Thermal control design.

[0038] The low-power thermal control method of the deep-space high-speed impactor divides the working period into three stages: cruise flight segment, autonomous flight segment, and post-collision survival segment for low-power thermal control.

[0039] The thermal control method for the cruising flight section is mainly represented as the cruising flight section in which the impactor 2 is mounted on the orbiter 1 . At this stage, the heater 5 of the impactor 2 is powered by the surrounder 1, and the heater 5 is powered by the surrounder 1 through a detachable joint. The impactor 2 adopts integral thermal control coati...

Embodiment 2

[0043]A low-power hierarchical thermal control method for a deep-space high-speed impactor, which mainly includes low-power thermal control design in three stages: cruising flight stage, autonomous flight stage, and post-collision survival stage. Among them, the cruising flight section adopts the overall temperature control design, and the orbiter 1 supplies power and heat to all the modules of the impactor 2; , propulsion module 4 and high reinforcement module 7 are heated. The post-collision survival section adopts a chip-level temperature control design, and the battery in the high-reinforcement module 7 supplies power and heats the high-reinforcement heater 10 next to each potting chip in the high-reinforcement module 7 .

[0044] Such as Figure 1~3 Shown is the diagram of the impactor installation, the overall assembly structure diagram of the impactor, and the internal diagram of the impactor body. The impactor 2 is mounted on the surrounder 1, and is powered by the s...

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Abstract

The invention discloses a graded low-power-consumption thermal control method of a deep-space high-speed impactor. The impactor (2) sequentially works in a cruise flight section, an autonomous flightsection and an after-impact survival section. In the cruise flight section, the impactor (2) is mounted on a surrounding device (1); the impactor (2) comprises a high-integration module (3), a propelling module (4), an impactor body (6) and a high-reinforcement module (7), wherein the high-reinforcement module (7) is mounted in the impactor body (6); in the cruise flight section, the surrounding device supplies power to and heats the high-integration module (3), the propelling module (4) and the impactor body (6); in the autonomous flight section, a battery in the high-integration module (3) supplies power to and heats the high-integration module (3), the propelling module (4) and the high-reinforcement module (7); and in the after-impact survival section, the battery in the high reinforcing module (7) supplies power to electronic equipment (8) for heating. According to the method, a low-power-consumption temperature control requirement of all stages in an impactor task period can be met.

Description

technical field [0001] The invention relates to a thermal control method with graded low power consumption for a high-speed impactor in deep space, and belongs to the technical field of thermal control of deep space exploration aircraft. Background technique [0002] The detection of high-speed impacts in deep space is an important means of detecting the interior of celestial bodies. In the impact mission, the impactor is carried by the probe into the outer space environment. After the probe is close to hitting the target celestial body, the impactor and the probe will separate and hit the target celestial body through autonomous flight and penetrate into the interior of the target celestial body. After that, the impactor will Keep a long-term survival probe for a certain period of time. During the whole process, if the impactor does not provide any protection, it will be directly exposed to the deep and cold environment of outer space, and the electronic equipment inside i...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/50G05D23/30
CPCB64G1/50G05D23/30
Inventor 方宝东彭玉明陆希王伟黄帆王海鹏耿志卿
Owner SHANGHAI SATELLITE ENG INST
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