A satellite formation configuration maintaining control method to improve payload observation efficiency

A technology for payload and maintaining control, applied in the field of satellite relative navigation, can solve problems such as theoretical or insufficient control methods with constraints, and achieve the effect of simple calculation, clear meaning, and easy self-realization

Active Publication Date: 2019-06-14
SHANGHAI XINYUE METER FACTORY
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Problems solved by technology

The common problem of these methods is that they often only start from the perspective of the control system itself, give more theoretical control methods or control methods with insufficient constraints, and fail to consider the practical engineering implementation constraints such as payload imaging requirements.

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  • A satellite formation configuration maintaining control method to improve payload observation efficiency
  • A satellite formation configuration maintaining control method to improve payload observation efficiency
  • A satellite formation configuration maintaining control method to improve payload observation efficiency

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Embodiment Construction

[0027] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several modifications and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0028] In order to describe the relative motion of the auxiliary star relative to the main star, it is necessary to define the relative orbital element vector based on the Kepler orbital element:

[0029]

[0030] In the formula, the subscript 1 indicates the absolute orbital element of the primary star, and the subscript 2 indicates the absolute orbital element of the auxiliary star.

[0031] The relative movement of the formation satellites is determined by the relative orbital elements of th...

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Abstract

The invention discloses a satellite formation keeping control method capable of improving payload observation efficiency. The method comprises the following steps that: specific constraint conditions are established according to engineering practice; formation parameter adjustment quantity (delta a and a delta e) are acquired through relative navigation information, and formation keeping control quantity is calculated; the feasible value range of gamma is determined according to the engineering constraint conditions; and gamma is optimized according to an evaluation equation, and keeping control is performed on formation configuration, and fuel consumption optimization is realized. With the satellite formation keeping control method of the invention adopted, keeping control can be performed on formation satellite configuration under a near-circle non-equatorial orbit condition, and at the same time, observation requirements of actual payload can be satisfied.

Description

technical field [0001] The invention relates to satellite relative navigation technology, in particular to a satellite formation configuration maintenance control method which improves payload observation efficiency. Background technique [0002] Due to its wide application prospects, global mapping has become an important mission requirement of earth observation satellites. Formation satellites have certain advantages in reliability, flexibility and economy, making them an important working condition for earth observation satellites. Due to the divergent influence of orbital perturbation on the formation configuration, the satellite formation needs to maintain the configuration to ensure the smooth operation of the mission during the entire life of the satellite. On the one hand, for formation satellites in near-earth and near-circular orbits, the divergence of the formation configuration is mainly manifested in the change of the relative eccentricity vector, so the argume...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/10G05B13/04
CPCG05B13/042G05D1/104
Inventor 完备杜耀珂陈敏沈阳何煜斌崔佳汪礼成郑科宇吴敬玉
Owner SHANGHAI XINYUE METER FACTORY
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