Rolling aircraft gyroscope error estimation method based on adam optimizer
By constructing an initial alignment equation and expanding the gyroscope error model, and using the Adam optimizer to estimate the roll angle and gyroscope error online, the initial alignment difficulty of the rolling aircraft under high overload and high speed environment was solved, and high-precision inertial navigation was achieved.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- BEIJING INST OF TECH
- Filing Date
- 2024-12-06
- Publication Date
- 2026-06-09
AI Technical Summary
Under high overload and high speed conditions, inertial devices cannot work, making it difficult to initially align the roll angle. When MEMS gyroscopes measure roll angular velocity, there is a large drift and residual installation error, resulting in serious accumulation of inertial navigation errors.
Based on the Adam optimizer, an initial alignment equation is constructed and the gyroscope error model is extended. By estimating the roll angle and gyroscope error online, the Adam optimizer is used to estimate the error and feed it back to the inertial navigation system.
It achieves synchronous online estimation of initial alignment and gyroscope error, effectively solving the problem of rapid accumulation of inertial navigation error and improving the alignment accuracy of roll angle and the accuracy of inertial navigation.
Smart Images
Figure CN122170918A_ABST