Research On Attitude Data Acquisition And Analysis Of General Aviation Aircraft

With the rapid development of the general aviation industry, the flight quality condition monitoring of general aviation become more and more important. The flight quality condition monitoring can’t be executed without flight data, especially aircraft attitude data. As an important part of the flight data, it is hard to acquire it in lots of general aviation aircraft, seriously hindered the monitoring of the flight quality condition.According to the current situation of general aviation and supporting by the subject of flight quality condition monitoring of general aviation, an attitude data acquisition and analysis project based on MEMS inertial sensors was proposed in this thesis. After completing the design of the hardware circuit and software program, the system examination platform was built to collect and analysis the attitude data. To test the efficiency of the platform, serial experiments were made with the gyro instrument testing platform and Cessna CJ1 simulator. The result showed that the system platform can gather and store the original data successfully. Integrating the data fusion algorithm and the error compensation algorithm to resolve the original data, and comparing with the real data, a conclusion can be given that the system platform has high accuracy and reliability.The situation of attitude data domestic and international, the purpose and the significance of the subject had been first introduced in this paper. In order to complete the functions of the system, the hardware was selected first. The STM32 MCU based on ARM kernel was selected as the microprocessor, the MPU6050 was selected which is the world’s first integrated 6-axis motion tracking device that combines a 3-axis accelerometer and a 3-axis gyroscope. The pluggable SD card was selected as the storage medium of the attitude data, and the raw data was saved as csv format by transplant the file system.The relevant knowledge of MEMS technology were introduced in this thesis, including the definition, characteristics and domestic and international situation. The working principle of MEMS accelerometer and gyroscope was mainly introduced. The working principle of complementary filter introduced and the possible error sources was analyzed in the thesis.At the last of the thesis, Testing was made by the gyro instrument testing platform and Cessna CJ1 simulator. Based on the original data, attitude algorithm was carried on by data fusion and error compensation, simulation was made by MATLAB tool, the result shows that the system has high accuracy and reliability compare with the real attitude data.