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Spacecraft formation flight method on small-thrust suspension orbit

A formation flight, small thrust technology, applied in the direction of instruments, three-dimensional position/course control, non-electric variable control, etc., can solve the problems of difficulty in maintaining large space span and low accuracy of results

Active Publication Date: 2018-10-02
BEIHANG UNIV
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Problems solved by technology

However, the existing formation flights in suspension orbits all derive the first-order analytical solutions of relative orbits through the method of linearizing the dynamic model. Maintain the stability of formation configuration with large space span and long period

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  • Spacecraft formation flight method on small-thrust suspension orbit
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  • Spacecraft formation flight method on small-thrust suspension orbit

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Embodiment Construction

[0057] The implementation of the method of the present invention will be further described below in conjunction with the accompanying drawings.

[0058] like figure 1 Shown, the concrete steps of the present invention are as follows:

[0059] (1) Establish the mapping from the orbital parameters of the bounded levitation orbit to the formation parameters: f:(h z ,κ,α,ΔE,Δr)→(ΔT,ΔΩ), compressing the five-dimensional space into a two-dimensional space. The levitation orbit can be determined by the orbit parameter vector (h z , κ, α, ΔE, Δr) unique representation, where h z is the momentum moment, κ is the thrust acceleration, α is the thrust pitch angle, ΔE is the difference between the system energy and the potential energy of the stable equilibrium point, and its value is positive, and Δr is the distance between the apogee of any orbit Poincaré map and the periodic orbit Poincaré map point the distance. Δr=0 ​​is a suspended periodic orbit, and Δr≠0 is a suspended pseudo-...

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Abstract

The invention discloses a spacecraft formation flight method on a small-thrust suspension orbit. Mapping of orbital parameters (hz, k, alpha, delta E, delta r) of a bounded suspension orbit to formation parameters (delta T, delta omega) is established, wherein the following formula is met: f:(hz, k, alpha, delta E, delta r) to (delta T, delta omega); formation conditions of three kinds of formation types are determined; and then suspension orbits of main satellites and salve satellites meeting all formation conditions are searched in a two-dimensional(delta T, delta omega) plane to realize bounded formation flight of the main satellites and salve satellites. Therefore, three different kinds of bounded relative orbits are obtained and the orbit precision is high. The method is suitable forlong-period large-scale formation flight; and implementation of a near-surface mission or a deep-space exploration formation mission is ensured.

Description

technical field [0001] The invention relates to a formation flight method of spacecraft on a low-thrust suspension orbit, in particular to a two-star formation flight method on a small-thrust suspension orbit, which is applied to the field of deep space exploration or polar observation. Background technique [0002] Suspension orbit is the orbit formed by the spacecraft relying on the external power provided by the new propulsion system and deviating from the natural trajectory. With the opening of the Earth's Arctic shipping lanes and the increase in Antarctic exploration activities, there is an increasingly urgent need to launch observation satellites that stay over the polar regions for a long time. The low-thrust geocentric suspension orbit is located in the area above the earth. With its special spatial location, it has become an ideal platform for detection tasks such as polar monitoring and communication relay. [0003] On the other hand, with the development of elec...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/10
CPCG05D1/104
Inventor 徐明潘晓马越辰伍涛郑亚茹和星吉
Owner BEIHANG UNIV
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