Anti-collision control method for safety of in-obit operation of formation-flying satellites

Abstract

The invention discloses an anti-collision control method for safety of in-obit operation of formation-flying satellites, in which influences of satellite contour dimension, various agitation errors, time forecasting error and position measurement error are seriously concerned, collision probability based description modes and determination methods for collision probability of the formation-flying satellites are systematically provided, and aiming at different operation situations of the formation-flying satellites, description indexes of integral and partial satellite collision possibility are respectively provided, so that the method is suitable for prevention of integral collision possibility of a plurality of formation-flying satellites. The method comprises the following steps: firstly, calculating collision probability density between two satellites, secondly, calculating the collision probability between the two satellites, and finally, calculating the collision probability of the formation-flying satellites. The method can be used for collision prevention for safety of in-obit operation of the formation-flying satellites, and can ensure real time and rapidity of determination of collision prevention for safety of the formation-flying satellites.

Description

Technical field [0001] The invention relates to a method for preventing collisions, and more particularly, to a method for preventing collisions for the safe operation of formation satellites in orbit. Background technique [0002] During the initialization, adjustment and reconstruction of the formation satellite formation, the collision problem caused by the change of the relative distance between the satellites cannot be ignored; even if the satellite formation does not perform orbital maneuvers, due to the impact on the formation satellites With different disturbances, the satellite formation will gradually deviate from its original configuration. Formation satellites are relatively close, and any deviation between the relative motion trajectory and the designed trajectory may cause two or more satellites to collide, which may lead to serious consequences. Therefore, when formation satellites are in orbit, in order to ensure that they can complete their tasks safely and effi...

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Problems solved by technology

[0007] In the document "Satellite Formation Flight Collision Probability Prediction and Collision Avoidance Measures Research" [Zhang Ge. [D]. Dalian: Dalian University of Technology, 2008.], a linear assumption is made for the calculation of the collision probability, and the influence of nonlinearity is not considered , but in fact, in many cases, the relative velocity between the formation satellites is relatively small, and the linear region of the relative trajectory of the satellites is relatively small compared to the entire collision calculation region. It is not suitable to use a linear algorithm that ignores the orbit curvature. Consider relative motion as non-linear to study collision probability calculation problem

[0008] Document "Distributed Satellite Collision Detection and Evaluation Method Based on Collision Probability" [Wang Jihe. [J]. Journal of Jilin University (Engineering Science Edition), 2009, 39(5): 1395-1400.] and "Research on Formation Satellite Collision Avoidance Method "[Hu Min. [J]. Shanghai Aerospace, 2010, 3:6-9.] The so-called collision probability of formation satellites only focuses on the collision probability between two satellites, and does not give the multi-satellite formation (Samsung and above) description and calculation method of overall collision probability

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