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A non-cooperative spacecraft attitude and parameter estimation method considering no gyroscope

A non-cooperative, spacecraft technology, applied in the field of spacecraft navigation, can solve the problems of non-cooperative spacecraft relative navigation, etc., to achieve the effect of improving attitude estimation accuracy, simple equipment, and avoiding singular states

Active Publication Date: 2021-07-02
BEIHANG UNIV
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Problems solved by technology

However, this method can only determine the attitude of the main body, and is not suitable for the relative navigation of non-cooperative spacecraft

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  • A non-cooperative spacecraft attitude and parameter estimation method considering no gyroscope
  • A non-cooperative spacecraft attitude and parameter estimation method considering no gyroscope
  • A non-cooperative spacecraft attitude and parameter estimation method considering no gyroscope

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Embodiment Construction

[0083] The present invention will be further described below in conjunction with the accompanying drawings.

[0084] Such as figure 1 As shown, the method for estimating the attitude and parameters of non-cooperative spacecraft without gyroscopes in the present invention includes: first, considering the problem that the target coordinate system does not coincide with its body coordinate system, and establishing a relative target non-cooperative spacecraft coordinate system. The attitude kinematics and dynamics model of a fast-rolling non-cooperative spacecraft; then, the relative attitude quaternion vector part, the error of the three-axis rotation angular velocity and the moment of inertia ratio are selected as filtering variables, and the discrete state equation and Observation equation; finally, the multiplicative extended Kalman filter is designed, and the design of five-step prediction is improved to improve the filtering estimation accuracy and follow-up speed, and solve...

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Abstract

The invention discloses a non-cooperative spacecraft attitude and parameter estimation method considering no gyroscope. The attitude kinematics and dynamics model of the non-cooperative spacecraft that is rapidly tumbling in space under the relative coordinate system of the target non-cooperative spacecraft; the error of selecting the attitude quaternion vector part, three-axis rotational angular velocity and moment of inertia ratio of the target non-cooperative spacecraft As a filtering variable, the discrete state equation and observation equation of the linearization system are derived; the multiplicative extended Kalman filter is designed, and the five-step prediction is improved to improve the filtering estimation accuracy and follow-up speed, and solve the problem of excessive sampling frequency of the optical sensor. Low results in the problem of increased filtering error.

Description

technical field [0001] The invention belongs to the field of spacecraft navigation, and particularly relates to a non-cooperative spacecraft attitude and parameter estimation method considering no gyroscope, capable of identifying the moment of inertia ratio of space non-cooperative spacecraft and realizing high-precision, real-time relative attitude motion estimation. Background technique [0002] Spacecraft attitude determination is to determine the attitude of the main body with star sensors and gyroscopes. At present, most of the tasks faced are the maintenance of failed spacecraft and the capture of out-of-control spacecraft. control the spacecraft. This type of spacecraft often rolls rapidly out of control in space, so it is necessary to obtain the motion state and dynamic parameters of the non-cooperative spacecraft when the target shape characteristics are unknown, there is no response, and there is no identification. Specifically, in order to implement tasks such a...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/24G01C21/20
CPCG01C21/20G01C21/24
Inventor 胡庆雷陈航郑建英董宏洋
Owner BEIHANG UNIV
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