A Boundary Control Method for Bounded Accompanying Satellites in Circular Reference Orbit

Abstract

The present invention provides a boundary control method for bounded accompanying flight of a satellite in a circular reference orbit. The boundary quantitative analytical relationship between the boundary of the satellite's bounded accompanying flight under orbit and the satellite's orbit element difference is solved to obtain the expected orbit element difference corresponding to the given boundary accompanying flight task; using a predetermined quantitative analytical control model Calculate and obtain the pulse speed increment that needs to be applied to the tracking satellite at the initial moment and the terminal moment. Using the boundary analysis model to solve the difference in expected orbital elements expands the space for the design of accompanying flight configurations and brings certain flexibility to the selection of formation or cluster flight mission configurations. The pulse velocity increment requirement with a given boundary is accurately calculated by the quantitative analytical control model, which has the advantages of high control precision and simple control process.

Description

technical field [0001] The invention belongs to the technical field of orbital dynamics and control of spacecraft, and in particular relates to a boundary control method for bounded accompanying flight of a satellite in a circular reference orbit. Background technique [0002] Space missions where multiple satellites work together in orbit, such as satellite formation gravity field measurement, on-orbit service, and non-cooperative target monitoring, need to keep the formation or cluster flying satellites within a limited distance from each other. Accompanied flight is a kind of periodic relative movement with a closed trajectory centered on the reference satellite. When the initial relative state is given, the accompanying flight configuration will have a definite inter-satellite distance boundary, which can be used as the first choice for multi-satellite cooperative space missions with boundary constraints. Traditionally, due to the lack of a theoretical model of the boun...

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Problems solved by technology

The main problem of this method is: because the traditionally known accompanying configuration types with analytical boundary expressions are few, the set satellite control objectives are relatively conservative, making it costly to maintain the relative motion of the desired boundary. Big disadvantage; in addition, due to the need for multiple attempts to perform pulse thrust control or continuous thrust control, that is to say, multiple thrusts need to be applied to the controlled satellite, which has the problem of complicated control process

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