A three-stage gyro attitude determination precision guarantee method for deep space reentry sample capsule

By calibrating the assembly error between the gyroscope's sensitive axis and the mechanical reference, and calibrating the three-axis turntable coordinate system, combined with closed-loop experiments, the problem of gyroscope installation error on the target aircraft was solved, achieving high-precision gyroscope installation and attitude determination accuracy assurance.

CN122448249APending Publication Date: 2026-07-24BEIJING INST OF CONTROL ENG
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
BEIJING INST OF CONTROL ENG
Filing Date
2026-03-17
Publication Date
2026-07-24

AI Technical Summary

Technical Problem

In the existing technology, the installation error of the gyroscope on the target aircraft is difficult to eliminate through direct calibration methods, resulting in insufficient lateral attitude control accuracy of the spin stabilizer. Especially under the condition of no optical reference, the installation error of the single-axis gyroscope cannot be effectively controlled.

Method used

By using a closed-loop iterative method, the assembly error between the gyroscope's sensitive axis and the mechanical reference is calibrated. Combined with the calibration of the three-axis turntable coordinate system, the relevant transfer matrix is ​​calculated, the installation matrix of multiple single-axis gyroscopes is calibrated, and closed-loop experiments are conducted for verification. Finally, the installation error is reduced through assembly, adjustment, and calibration.

Benefits of technology

It achieves high-precision installation of gyroscopes on target aircraft without optical reference conditions, ensuring the attitude accuracy of the spin stabilizer, improving the accuracy of gyroscope installation and error control capability, and forming a complete closed-loop calibration and adjustment process.

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Abstract

The present application relates to a kind of three-stage gyroscopic attitude determination precision guarantee method of deep space reentry sample cabin, comprising: the assembly error between the sensitive axis of gyroscope and gyro single machine mechanical reference, i.e. primary installation error is calibrated;According to the definition of turntable coordinate system, calculate relevant transfer matrix;Carry out the calibration of gyro measurement axis relative to three-axis turntable coordinate system, obtain gyro rotation speed and turntable angle measurement value;Combined with the relevant transfer matrix obtained, while the installation matrix calibration of multiple single-axis gyroscopes relative to sample cabin is carried out, the secondary installation error calibration is completed;The installation matrix calibration result solved is substituted into three-axis turntable closed loop experiment, and the correctness of calibration result is verified;According to the calibration result after verification, calculate orthogonal direction compensation size and carry out adjustment, complete gyro installation calibration, and the closed loop verification of adjustment result is carried out until it is ensured that the installation error of gyro sensitive axis relative to sample cabin mechanical system is reduced to the allowed range of attitude determination precision.
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Citation Information

Patent Citations

  • CN104101363A

  • CN111664868A