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High-surface-mass ratio spacecraft orbit dynamics analysis method

A dynamic analysis and spacecraft technology, applied in the direction of instruments, special data processing applications, electrical digital data processing, etc., can solve problems such as difficult solutions and reduced calculation accuracy, and achieve a wide range of effects

Inactive Publication Date: 2016-06-29
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

On the other hand, traditional orbital dynamics analysis is based on the Gaussian perturbation equation. However, for high surface-to-mass ratio spacecraft, the Gaussian perturbation equation can only be used for Orbital Analysis in Special Cases
The current orbital dynamics analysis method for spacecraft with high surface-to-mass ratio is mainly based on the analysis method of Gaussian perturbation equation. decrease and as the perturbation force increases, it becomes very difficult to solve the equation

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Embodiment Construction

[0025] The technical solution adopted by the present invention to solve its technical problems comprises the following steps:

[0026] (1) To establish a dynamic model, the specific steps are as follows:

[0027] Step 1: Referring to "Fundamentals of Orbital Mechanics of Long-Range Rockets and Satellites", it can be seen that the gravitational potential energy function model of the earth in the earth's inertial coordinate system can be expressed as Among them, U represents the gravitational potential field of the earth, φ represents the latitude of the earth center, and P n Represents the nth order Legendre polynomial, R represents the radius of the earth, μ represents the gravitational coefficient, J n Represents the harmonic coefficient, and r represents the distance from the center of the earth at the position of the spacecraft.

[0028] Step 2: Refer to BongWie.SolarSailAttitudeControlandDynamics, Part 1 (Journal of Guidance, Control, andDynamics, Vol.27, No.4, July-Aug...

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Abstract

The invention provides a high-surface-mass ratio spacecraft orbit dynamics analysis method and belongs to the field of spacecraft orbit dynamics. The high-surface-mass ratio spacecraft orbit dynamics analysis method comprises the following steps: respectively modeling solar radiation pressure, atmospheric resistance, earth shadow and other perturbative forces; then establishing a dynamic model of a whole system based on a Hamilton's principle. According to the high-surface-mass ratio spacecraft orbit dynamics analysis method provided by the invention, the effects of the solar radiation pressure and the atmospheric resistance on a high-surface-mass ratio spacecraft are respectively analyzed, and meanwhile, an equilibrium orbit under the combined action of the perturbative forces is also obtained via analysis. Orbit elements are not needed to suffer from average processing; therefore, the precision is higher, and the understanding is easy. The high-surface-mass ratio spacecraft orbit dynamics analysis method provided by the invention can be used for not only high-surface-mass ratio spacecraft orbit analysis around the ground, but also high-surface-mass ratio spacecraft orbit analysis around other planets, so that the application scope is wide.

Description

technical field [0001] The invention relates to a spacecraft orbital dynamics analysis method, which belongs to the field of spacecraft orbital dynamics. Background technique [0002] On October 4, 1957, the Soviet Union successfully launched the first artificial satellite, ushering in the space age. With the continuous development of the human space field, a large number of spacecraft oriented to different mission requirements were sent into space. However, in the early days of human beings entering space, they only used the near-Earth orbit around the Earth to complete a single mission. In recent decades, with the rapid development of aerospace technology and the continuous progress of human society, various aerospace applications and research fields have emerged, as well as various spacecraft, high surface-to-mass ratio spacecraft It is one of them, such as solar sails, inflatable satellites, and chip satellites currently under development are all spacecraft with high su...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 宁昕李琪袁建平岳晓奎
Owner NORTHWESTERN POLYTECHNICAL UNIV
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