A method, apparatus, medium, and electronic device for calculating attitude angles.

By constructing a target coordinate system and calculating the transformation matrix, the accuracy of attitude angle changes during rocket attitude adjustment was solved, ensuring the effectiveness of space-based telemetry and control.

CN116009596BActive Publication Date: 2025-10-28AEROSPACE SCI & IND KET TECH CO LTD
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Patent Information

Application Number
CN202310024058.9
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2023-01-09
Publication Date
2025-10-28
Estimated Expiration
2043-01-09

AI Technical Summary

Technical Problem

Existing technologies make it difficult to accurately calculate the changes in flight attitude angles during the rocket's attitude adjustment process before and after separation of the satellite and rocket. Especially when the attitude angle changes are large, the relay satellite may be out of the field of view of the space-based antenna, thus failing to meet the needs of space-based telemetry and control.

Method used

Construct the target coordinate system, determine the transformation matrix between the target coordinate system and the geocentric coordinate system, obtain the transformation matrix between the rocket body coordinate system and the target coordinate system, calculate the transformation matrix between the rocket body coordinate system and the navigation coordinate system, and determine the rocket's attitude angles using these matrices.

Benefits of technology

It provides accurate reference data on rocket flight attitude angle changes, ensuring linear changes in the line-of-sight angle of the space-based antenna during rocket attitude adjustment, preventing the relay satellite from falling out of the field of view, and meeting the conditions for space-based telemetry and control.

✦ Generated by Eureka AI based on patent content.

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Abstract

This application relates to the field of aerospace technology, specifically to a method, apparatus, medium, and electronic device for calculating attitude angles. The method includes: constructing a target coordinate system and determining a first transformation matrix between the target coordinate system and a geocentric coordinate system; obtaining a second transformation matrix between the rocket body coordinate system and the target coordinate system before and after the target process; calculating target Euler angles between the rocket body coordinate system and the target coordinate system before and after the target process based on the second transformation matrix; determining a third transformation matrix between the rocket body coordinate system and the target coordinate system during the target process based on the target Euler angles; and calculating a fourth transformation matrix between the rocket body coordinate system and the navigation coordinate system during the target process to determine the rocket attitude angles in the navigation coordinate system. The technical solution provided by this application can accurately calculate the changes in flight attitude angles of a rocket during attitude adjustment.
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Citation Information

Patent Citations

  • Electromagnetic launching rocket turning section trajectory design method

    CN114485265A

  • Platform attitude measurement system

    US5751578A