Method for rapidly predicting aerodynamic characteristics of low-orbit spacecraft having complex shape

A technology of aerodynamic characteristics and prediction methods, applied in instruments, special data processing applications, electrical digital data processing, etc.

Active Publication Date: 2016-09-28
CHINA ACAD OF AEROSPACE AERODYNAMICS
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AI Technical Summary

Problems solved by technology

[0006] The technical problem of the present invention is: to overcome the deficiencies of the prior art, according to the needs of the calculation of the aerodynamic characteristics of the existing complex-shaped low-orbit spacecraft, based on the free molecular flow theory in r

Method used

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  • Method for rapidly predicting aerodynamic characteristics of low-orbit spacecraft having complex shape
  • Method for rapidly predicting aerodynamic characteristics of low-orbit spacecraft having complex shape
  • Method for rapidly predicting aerodynamic characteristics of low-orbit spacecraft having complex shape

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Embodiment Construction

[0059] The specific solution examples for the prediction of aerodynamic characteristics of low-orbit spacecraft are as follows:

[0060] First consider the Gravity field and steady state Ocean Circulation Explorer (GOCE) of the European Space Agency (ESA), figure 2 A schematic diagram of its model. In order to maximize the sensitivity to the Earth's gravitational field, the satellite's flight altitude is as low as 250-300 km, Table 1 is the calculation conditions, and the gas molecule reflection model is diffuse reflection.

[0061] Table 1 Calculation conditions of GOCE satellite verification example

[0062]

[0063] image 3 The GOCE satellite drag coefficient vs. speed ratio (the ratio of the satellite flight speed to the most probable molecular thermal motion speed of the incoming flow) is given, and compared with the results published by the German HTG (Göttingen Hypersonic Institute), the solid line Represents program calculation results, and scatter points repre...

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Abstract

The invention relates to a method for rapidly and accurately predicting aerodynamic characteristics of a low-orbit spacecraft having a complex shape. The method comprises the following steps of: firstly, constructing a big enough computational domain, wherein the spacecraft is positioned in the computational domain; and a test particle is generated at the boundary; then, tracking and simulating the movement locus and the collision process after the test particle till the test particle flies out the computational domain or collides the surface of the spacecraft, and computing momentum and energy exchange of the test particle and the surface of the object and continuously tracking the test particle if the test particle is collided with the surface; and finally, repeating the process till the number of the test particles is large enough, such that convergence of a computing result is ensured, and counting an aerodynamic characteristic rule of the spacecraft in a flying environment, such that design of the spacecraft is carried out.

Description

technical field [0001] The invention relates to a fast prediction method for the aerodynamic characteristics of low-orbit spacecraft with complex shapes, and belongs to the technical field of aircraft aerodynamic characteristics design. Background technique [0002] In order to obtain a detailed full-band Earth gravity field and centimeter-level geoid, on-orbit spacecraft, such as GOCE (Gravity field and steady state Ocean Circulation Explorer) designed by the European Space Agency, must Get as close to the Earth's surface as possible to maximize sensitivity to Earth's gravitational field. However, when the spacecraft flies in the earth's orbit, it will be greatly affected by non-conservative forces, such as thin atmospheric drag, solar light pressure and earth albedo pressure, among which the influence of atmospheric drag is the most obvious. In order to obtain accurate data of the earth's gravity field, it is necessary to offset these non-conservative forces, especially t...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/367
Inventor 靳旭红黄飞程晓丽王强俞继军
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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