Accelerometers and an Aircraft Attitude Evaluation

Abstract

The paper describes a method that enables a usage of low-cost inertial sensors, such as angular rate sensors and accelerometers, in a system of aircraft attitude evaluation. The method depicts a suitability of using accelerometers to restrict an influence of angular rates' integration on a precision of the attitude assessment. The method was verified with a simulation in MATLAB-Simulink environment and with various measurements. The method principles, simulation and measurement results are presented