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A hybrid continuous small thrust trajectory design method adopting electric propulsion/solar sail propulsion

A hybrid continuous, design method technology, applied in the field of aerospace technology development, can solve problems such as difficulty in applying space maneuvering orbit design, without considering thrust constraints, etc.

Active Publication Date: 2019-01-11
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

However, this method is an indirect optimization method and does not consider the thrust constraint problem, so it is difficult to apply to the actual space maneuver orbit design

Method used

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  • A hybrid continuous small thrust trajectory design method adopting electric propulsion/solar sail propulsion
  • A hybrid continuous small thrust trajectory design method adopting electric propulsion/solar sail propulsion
  • A hybrid continuous small thrust trajectory design method adopting electric propulsion/solar sail propulsion

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Embodiment Construction

[0064] The present invention is described in further detail below:

[0065] The present invention adopts the electric propulsion / solar sail propulsion hybrid continuous low-thrust track design method, comprising the following steps: a. The method combines the track average method and the virtual gravitational potential field method to parameterize the maneuvering track under the action of small thrust, And be able to solve the analytical solution to realize orbital maneuvering; b. On the basis of analyzing the orbital error characteristics, determine the error factor of the orbital analytical solution, and obtain a high-precision analytical solution under the condition of ensuring that the error factor constraint is met; based on the above The optimization algorithm of the design method includes the following steps: a1. Using the shape method, express the attitude angle of the solar sail as a polynomial form of the transfer angle; b1. Given the energy consumption as the objecti...

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Abstract

The invention discloses a hybrid continuous small thrust trajectory design method adopting electric propulsion / solar sail propulsion. Firstly, a virtual gravitational field dynamics model is established. Secondly, the dynamic model of tangential thrust orbit in virtual gravitational field is established and its analytical solution is solved. Then the accuracy of the analytical solution is analyzed. Finally, the orbit optimization model is established, and the hybrid continuous small thrust method of electric propulsion / solar sail propulsion is used to optimize the orbit. Under the condition ofguaranteeing the accuracy, the invention can greatly reduce the calculation amount, can reduce the thrust required for realizing the orbit transfer, and expands the application range of the small thrust orbit.

Description

technical field [0001] The invention belongs to the field of aerospace technology development, and in particular relates to a hybrid continuous low-thrust track design method using electric propulsion / solar sail propulsion. Background technique [0002] Continuous low-thrust orbit design is widely used in space maneuver orbit design. Compared with traditional pulse thrust or high thrust, continuous low-thrust orbital maneuvering is easy to control and has strong maneuverability; in addition, its specific impulse is small, and the fuel required for orbital maneuvering is very small, so it has become a research hotspot. Mcinnes proposed the use of solar sails to change the size of the gravitational field for the first time, designed the levitation orbit, and deduced the analytical solution of the thrust required to realize the levitation orbit. Further, Malcolm et al. used solar sails to generate tangential fixed thrust, designed a transfer orbit from Earth orbit to solar pol...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F2111/04G06F2119/06G06F30/20Y02T90/00
Inventor 孙冲袁建平任仲靖陈建林
Owner NORTHWESTERN POLYTECHNICAL UNIV
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