Dalian University of Technology

Yang Zhang

Wei Liu

Zhenyuan Jia

Likun Si

Mengde Zhou

Bing Liang

Wei Peng

Ang Li

Zhenguo Jing

Qiang Liu

Yueying Liu

Di Feng

Zhiyuan Huang

Xintong Jiang

Kun Liu

Zhengquan Wen

Zhuang Yao

Linlin Tang

Xingtong Jiang

A white light interferometric fiber-optic gyroscope based on a rhombic optical path difference bias structure includes a laser, a rhombic optical path difference bias structure, a fiber coil and a photodetector. The white light interferometric fiber-optic gyroscope adopts an all-fiber structure to simplify the complexity of a gyroscope system and reduce the overall cost. A white light interferometric demodulation algorithm is used to realize linear output of rotation rate signals.

White light interferometric fiber-optic gyroscope based on rhombic optical path difference bias structure

A 3D measurement model and the spatial calibration method based on a 1D displacement sensor are proposed. A 3D measurement system based on a fixed 1D displacement sensor is established; then a spatial measurement model based on the 1D displacement sensor is established; and then based on the high precision pose data of the measurement plane and sensor measurement data, spatial calibration constraint equation are established; a weighted iterative algorithms is employed to calculate the extrinsic parameters of the 1D sensor that meet the precision requirements, then the calibration process is completed. A high precision 3D measurement model is established; a 3D measurement model based on a 1D displacement sensor is established, and the calibration method of the measurement model is proposed, which will improve the precision of the 3D measurement model and solve the problem of inaccurate spatial measurement caused by the errors of the sensor extrinsic parameters.

3D measurement model and spatial calibration method based on 1D displacement sensor

A multi-dimensional vibration control method based on piezoelectric ceramic actuator applied to wind tunnel test of aircraft model. The pitch and yaw acceleration sensors arranged on the center of mass of the aircraft model are used to measure the two components of the main vibration acceleration of the aircraft model, and the main vibration vector of the aircraft model is obtained and the real-time vibration plane of the strut is determined. Inertia is introduced to solve the dynamic bending moment on the active section of the multi-dimensional vibration damper, and then the stress distribution on the active section is obtained. The multi-dimensional active vibration control system is adopted to improve the stability and reliability of the active vibration control system of wind tunnel model, extend the service life of piezoelectric ceramic actuator, and ensure the quality of wind tunnel test data and the safety of wind tunnel test.

Multi-dimensional vibration control method for the model of strut tail-supported aircraft

Growing community of inventors

Liaoning, China

Yang Zhang