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Ultra-low rail resistance coefficient determination method, device and equipment and storage medium

A drag coefficient and measurement method technology, which is applied in the field of aerodynamic force between ultra-low orbit rare gas and aircraft, can solve the problems of immaturity, limited application range, and difficulty in the measurement of ultra-low orbit drag coefficient, and achieve the effect of convenient and simple measurement

Active Publication Date: 2020-08-28
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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  • Ultra-low rail resistance coefficient determination method, device and equipment and storage medium
  • Ultra-low rail resistance coefficient determination method, device and equipment and storage medium
  • Ultra-low rail resistance coefficient determination method, device and equipment and storage medium

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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

The invention discloses an ultra-low orbit resistance coefficient determination method, device and equipment and a storage medium, and the method comprises the steps: firstly calculating the resistance coefficient of incoming flow atmosphere at a preset speed based on the obtained aerodynamic force of the incoming flow atmosphere forming a preset incident angle with a measurement plane; and calculating the resistance coefficients at different incoming flow speeds based on the expressions of the resistance coefficients at different incoming flow speeds and the resistance coefficients of the flowing atmosphere to the measurement plane at the preset speed. The resistance coefficient of the flowing atmosphere of the measuring plane at the preset speed is convenient and simple to measure, the resistance coefficient under the incoming flow speed condition which cannot be achieved by the test condition can be conveniently obtained by popularizing a formula, and the ultralow-orbit atmosphericresistance actually borne by the aircraft can be easily obtained.

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...

Claims

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Application Information

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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
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