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Method, device, equipment and storage medium for measuring resistance coefficient of ultra-low orbit

A technology of drag coefficient and measurement method, which is applied in the aerodynamic field where ultra-low orbit rare gas interacts with aircraft, can solve the problems of immaturity, limited application range, and difficulty in measuring ultra-low orbit drag coefficient, and achieves the effect of convenient and simple measurement.

Active Publication Date: 2022-04-22
BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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Problems solved by technology

It can be seen that it is difficult to use the Monte Carlo simulation method to measure the drag coefficient of ultra-low orbit, and the application range is limited, and it is not mature enough

Method used

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  • Method, device, equipment and storage medium for measuring resistance coefficient of ultra-low orbit
  • Method, device, equipment and storage medium for measuring resistance coefficient of ultra-low orbit
  • Method, device, equipment and storage medium for measuring resistance coefficient of ultra-low orbit

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Embodiment Construction

[0040] The application will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain related inventions, rather than to limit the invention. It should also be noted that, for ease of description, only parts related to the invention are shown in the drawings.

[0041] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and embodiments.

[0042]As mentioned in the background art, it is easy to see that both specular reflection and diffuse reflection are extreme reflection models, which cannot well describe the interaction reflection behavior between molecules and walls. Although the object surface reflection model (CLL) is physical...

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Abstract

This application discloses a method, device, equipment and storage medium for measuring the drag coefficient of ultra-low orbit. Firstly, based on the obtained aerodynamic force of the incoming atmosphere at a preset incident angle with the measurement plane, the preset velocity is calculated as described below. The resistance coefficient of the flowing air; secondly, based on the expression of the resistance coefficient at different incoming flow speeds and the resistance coefficient of the flowing air at the preset speed to the measurement plane, the resistance coefficient at different incoming flow speeds is calculated. It is convenient and simple to measure the resistance coefficient of the air flowing downflow from the measurement plane at a preset speed. Through the extension of the formula, the resistance coefficient under the condition of the flow speed that cannot be achieved under the test conditions can be easily obtained, and then it is easy to obtain the actual supersonic force of the aircraft. Atmospheric drag in low orbit.

Description

technical field [0001] The present invention generally relates to the technical field of aerodynamic force between ultra-low orbit rare gas and aircraft, and in particular to a method, device, equipment and storage medium for measuring the atmospheric drag coefficient of ultra-low orbit. Background technique [0002] Rare gas dynamics has an important application background in the aerospace field. The atmosphere in LEO orbit and adjacent space is very thin and cannot sustain normal life activities of human beings, but it is enough to have a significant impact on spacecraft flying at high speed in orbit. The impact of high-speed moving atoms on the spacecraft will increase its aerodynamic resistance, causing the orbit of the aircraft to drop, or even crash, reducing the service life of the aircraft. [0003] Due to the rarefaction effect, the conventional continuum assumption is not valid, so the N-S equation for continuous flow is no longer applicable, resulting in the aero...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/08G01M9/06
CPCG01M9/08G01M9/06G01M9/065
Inventor 李涛姜利祥商圣飞焦子龙郑慧奇唐振宇向树红
Owner BEIJING INST OF SPACECRAFT ENVIRONMENT ENG