Identification method for three-axis moment-of-inertia ratio of non-cooperative spacecraft under approximate spinning

Abstract

The invention discloses an identification method for the three-axis moment-of-inertia ratio of a non-cooperative spacecraft under approximate spinning, comprising the following steps: under the condition that the angular velocity change rate of rotation around a maximum inertia main shaft is almost zero, using quaternion parameters to establish kinematics and dynamics models a non-cooperative spacecraft under approximate spinning; establishing a spacecraft attitude observer model with noise; and aiming at the mathematical relationship of the moment-of-inertia ratio, decoupling the three-dimensional moment-of-inertia ratio, selecting a two-dimensional moment-of-inertia ratio of the moment-of-inertia main shaft corresponding to a large angular velocity change rate, forming an eight-dimensional filter state variable with the attitude and the angular velocity, and designing a state transfer matrix, a gain matrix and a spacecraft multiplicative extended Kalman filter based on an error quaternion. Under the condition that the angular velocity of a target cannot be known, the attitude information of the target is obtained through a non-cooperative sensitive component only. The attitude filtering, angular velocity estimation and moment-of-inertia ratio identification of a non-cooperative target approximately spinning around the maximum inertia main shaft are achieved.

Description

technical field [0001] The invention belongs to the field of non-cooperative spacecraft navigation system design, in particular to an identification method for the three-axis moment of inertia ratio of non-cooperative spacecraft in an approximate spin state. Background technique [0002] At present, as the mission requirements of spacecraft tend to be diversified and complex, including various space operations, for example, on-orbit operations can realize space operation tasks such as on-orbit refueling, on-orbit maintenance and assembly, and on-orbit module replacement. Distance operation; the spacecraft will encounter space junk in space, and there will be a risk of collision. The capture of space debris can ensure the safety of the spacecraft; spacecraft rendezvous and docking require the space orbit parameters and relative poses of the main and auxiliary spacecraft Accurate knowledge of information, etc. With the rapid development of space technology and the increasing ...

AI Technical Summary

Problems solved by technology

[0005] In order to solve the problem of obtaining the attitude information of the target only through non-cooperative sensitive components when the angular velocity of the target cannot be known, the filtering of the attitude of the non-cooperative target, the estimation of the angular velocity, and the identification of the moment of inertia ratio are realized. The present invention provides a state filter based on the multiplicative extended Kalman filter method. In order to overcome the fact that the angular velocity change rate of the rotation around the maximum inertia axis is almost zero, the moment of inertia ratio corresponding to the maximum inertia axis is not in the filter. Sensitive, based on the equation relationship, establish the two-dimensional moment of inertia ratio, and indirectly realize the parameter identification of the three-dimensional moment of inertia ratio

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