Application of Optimal Kalman Filter to Improve the Accuracy of Aircraft Wing Vibration Parameters Measurement System

Abstract

This paper discusses the advantages of constructing a vibration parameters measurement system of an aircraft wing using mems IMUs. In addition to mems IMUs, the system makes use of displacement sensor and navigation system as secondary measurements, along with the optimal Kalman filter estimation. The basic principles of system operation are described. The main algorithms of the system and its errors mathematical model are presented. The results of simulation are presented, demonstrating the expected measurement accuracy of the system as a whole.

Promising Wing Vibration Measurement System Using MEMS IMUS and Kalman Filter Correction

“…The mathematical errors model of the orientation and navigation parameters channel used in the VPMS algorithm is obtained by applying the method of variation to the ideal operation algorithm [20]:…”

“…, For the open loop correction [20], the estimates of main system errors are formed using OKF estimates for the most general case of MEMS IMU2 as follows:…”

“…1). Besides, incorporation of optimal Kalman filter (OKF) based on open-loop scheme [20] gives acceptable results only for a limited period of time [21], after which a significant increase in estimation errors for a number of parameters arises. This is due to many reasons, including the limited accuracy of the MEMS IMU error models and the orientation and navigation channels which work based on them, as well as the DS, which becomes apparent especially sharply with their large intrinsic errors arising from long-term operation.…”