Method for measuring and calculating inertial parameter of non-contact-type tumbling spacecraft

Abstract

The invention discloses a method for measuring and calculating an inertial parameter of a non-contact-type tumbling spacecraft, and relates to the technology of attitude as well as inertia moment measurement of the tumbling spacecraft under a space on-orbit-servicing technology belonging to the field of spaceflight. A principle is characterized in that an analytical solution of an attitude quaternion kinetic equation of the tumbling spacecraft is employed, and the attitude quaternion is expressed as an equation having a linear form and containing the undetermined parameters; then the undetermined parameters of the constant values substitute the inertia parameter, angular velocity and attitude angle for being as a state quantity of a system, and a Kalman filter is used for estimation. The observed quantity obtained by employing the Kalman filter is the measured value of the attitude quaternion of the tumbling spacecraft obtained by a current observation technology. Following with the increasing observation data, the estimated value of the constant parameter is more and more accurate, by using the estimated value of the undetermined parameters, the ratio of the main inertia moments of the tumbling spacecraft can be directly reckoned.

Description

【Technical field】 [0001] The invention relates to space on-orbit service technology in the field of aerospace, to the field of attitude and moment of inertia measurement of rolling satellites, and in particular to a non-contact measuring method for inertial parameters of rolling satellites. 【Background technique】 [0002] With the expansion of the scale of human development of space, more and more invalid satellites with failed missions or expired life are appearing in space. Because these satellites usually occupy important orbital positions and are of high value, it is particularly urgent and necessary to develop technologies for capturing and recovering such satellites. However, most of the failed satellites are in an uncontrolled rolling state, and the measurement and prediction of the attitude change and moment of inertia characteristics of the failed satellite before capture is one of the problems to be solved urgently in the capture task. [0003] The non-contact mea...

AI Technical Summary

Problems solved by technology

Under the existing technology, stereo vision equipment or laser range finder can be used to discretely measure the attitude of unknown satellites without contact, but it is extremely difficult to accurately measure its moment of inertia without contact

The traditional non-contact inertia parameter estimation method is to use the Kalman filter to recursively fit its moment of inertia as one of the state variables, but the accuracy is very low, and it is necessary to give a sufficiently accurate initial value of the angular velocity measurement to ensure the convergence of the algorithm

In practical applications, the contact method is often used to measure the moment of inertia of the tumbling satellite after capture. Although this simplifies the task process, it will increase additional energy consumption

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