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Formation configuration reconstruction optimization using finite element method

A finite element and configuration technology, applied in the field of satellite formation flight, can solve problems such as control frequency limitation, and achieve the effect of avoiding collision, reducing optimization time, and reducing energy consumption

Active Publication Date: 2019-09-17
BEIHANG UNIV
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Problems solved by technology

[0008] Compared with traditional spacecraft orbit maintenance, the orbit control of high-precision formation flight has higher requirements for control accuracy, and also has certain restrictions on control frequency

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  • Formation configuration reconstruction optimization using finite element method
  • Formation configuration reconstruction optimization using finite element method
  • Formation configuration reconstruction optimization using finite element method

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Embodiment 1

[0127] Such as image 3 As shown, the satellite formation is composed of a master star and five slave stars (namely, slave star 1, slave star 2, slave star 3, slave star 4, and slave star 5). The reference orbit of the primary star is given by the orbital elements: the semi-major axis of the orbit is 29948.478 kilometers, the eccentricity is 0.001, the orbital inclination is 63.31 degrees, the right ascension of the ascending node is 243.00 degrees, the argument of perigee is 214 degrees, and the mean point The angle is 180 degrees. Assume that the five slave stars in the formation are initially distributed along the orbital direction, centered on the master star, and separated by 50m. Then the initial states of the five slaves are as follows:

[0128] in, Indicates the first initial motion state quantity transformed from star coordinates; Indicates the second initial motion state quantity transformed from star coordinates; Indicates the third initial motion state qu...

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Abstract

The invention discloses a formation configuration reconstruction optimization using a finite element method. The finite element method is used for dividing the formation reconstruction time into a series of equally spaced intervals, and the problem of solving the reconstruction path is transformed into an optimization problem; therefore, the limitation problem of the traditional reconstruction method is overcome, and the reconstruction of a satellite formation is realized. In the optimization process, the optimal orbit control quantity and the corresponding reconstructed orbit state quantity in each time subinterval are determined according to the numerical iterative method; and the iteration and correction are performed again on the loading of the control acceleration applied by a small thrust engine to the spacecraft in the optional subinterval and the reconstruction orbit state quantity considering the criteria of controlling the total fuel consumption to be minimum, the control opportunity, and the safety factor to avoid collision among spacecrafts.

Description

technical field [0001] The invention relates to the technical field of satellite formation flight, more particularly, refers to a formation configuration reconstruction optimization using the finite element method. Background technique [0002] As a multi-satellite system, the spacecraft formation greatly expands the limitations of a single spacecraft to complete the task, not only can realize the task function of a single spacecraft in the formation, but also the entire formation can replace a single large spacecraft to achieve more complex tasks . Under certain conditions, even if one or two spacecraft are lost in the formation, other spacecraft can cooperate to complete the mission of the lost spacecraft, which greatly improves the overall reliability of the formation system and has strong practical application value. Since the fuel carried by satellites in formation is limited and cannot be replenished, it is of great significance to study different reconfiguration stra...

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Application Information

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IPC IPC(8): G05D1/10G06F17/50
CPCG05D1/104G06F30/23
Inventor 徐明白雪郑亚茹伍涛曲庆渝
Owner BEIHANG UNIV
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