A Synthetic Identification Method of Spacecraft Dynamic Parameters

Abstract

The invention discloses a method for comprehensively identifying dynamic parameters of a spacecraft by comprehensively utilizing the information of mass mutation and engine on / off. Comprehensively utilize the information of the mass mutation and the thrust change information of the engine switching on and off during the flight of the spacecraft; use the known mass mutation information and corresponding observation data to realize the independent identification of dynamic parameters; The model describes the flight of the spacecraft during the whole process; based on this, the dynamic parameters of the spacecraft are identified. This method can use observation data for a longer period of time to estimate parameters, effectively solve or alleviate the problems of parameter coupling, distribution solution errors, and insufficient effective information of observation data, and make parameter estimation more stable and accurate.

Description

A method for comprehensive identification of spacecraft dynamics parameters Technical field [0001] The present invention relates to a comprehensive utilization of the quality mutation and engine caused by the throwing off of accessories during the flight of a spacecraft Synthetic identification method of dynamic parameters of switch machine information. Background technique In the parameter estimation problem based on spacecraft motion information, if spacecraft thrust parameter, initial quality parameter, quality Due to the multiplicative coupling of the parameters, only the ratio between the parameters can be estimated, and the former cannot be independently identified. The above parameters, the behavior of rapidly throwing away the attached parts with known mass in a short period of time during the flight of the spacecraft will generate mass mutation excitation, This will result in a sudden change in the acceleration experienced by the object, and using this informa...

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Problems solved by technology

Relative to the thrust acceleration is relatively large, using slightly different time intervals, the estimated parameters are quite different

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