Research On Aircraft Attitude Algorithm Based On The Array Of Accelerometer

In this paper the aircraft attitude resolution method based on accelerometer array is analyzed and its related principles are introduced.In the attitude resolution method for strap-down inertial navigation system based on accelerometer array, the related force equation, the coordinate transformation matrix and the inertial device model are analyzed firstly. Then, the single gyro five accelerometer configuration scheme is illustrated and an optimized angular velocity resolution method is adopted to complete navigation resolution. Finally, the resolution procedures of the direct differential method, the Pirkanmaa method, the four-sample rotating vector method and the cone compensation optimized method based on quaternion differential equation are re-deduced in the attitude updating link. Simulation experiments verify the feasibility of the single-gyro-five accelerometer scheme and the superiority of angular velocity resolution method. Besides, the four attitude updating methods are compared in the simulation, which indicates that the improved four-sample rotating vector method can effectively restrain the errors generated in the attitude updating process and is the one with the highest precision of all four methods.In the attitude resolution method for non-strap-down inertial navigation system based on accelerator array, the principle of the accelerator array configuration is analyzed at the first place. Then, the gyro-free resolution scheme is optimized and a new single-gyro resolution scheme is proposed in the four-accelerator attitude resolution method. Finally, two simplified attitude resolution methods are deduced. With the simulation experiments on the gyro-free-four-accelerator scheme and the single-gyro-four-accelerator scheme, the feasibility of the roll attitude angle resolution method for the non-strap-down inertial navigation system is verified.Based on the above attitude resolution methods, the paper analyzes the model error of inertial components, studies the errors generated during the attitude, velocity and position resolution, and deduces the error differential equation. The algorithm error of the non-strap-down inertial navigation system is also calculated. With theoretical deduction, the influence of the algorithm errors on the entire attitude resolution system is analyzed and effective error compensation is made accordingly.