Abstract:

Transfer alignment of some airborne equipment is executed during takeoff of the aircraft. With traditional matching schemes, the transfer alignment accuracy is affected due to the limited speed of aircraft. To solve this problem, a specific force integration matching scheme is proposed to adapt to the aircraft’s low speed. Observation of Kalman filtering is the integration of specific force difference between master inertial navigation system (MINS) and slave inertial navigation system (SINS), and gyro error is not imported. Since SINS only performs calculation of the specific force integral, computation complexity is reduced. Taking into account error angle in installation and the flexural distortion angle, a system error model is established. Simulation results indicate that the proposed method can improve transfer alignment accuracy at low aircraft speed. It is potentially useful in medium- and low-precision strap-down inertial navigation systems.

Key words: inertial navigation, transfer alignment, low speed, Kalman filtering