UAV attitude calculation algorithm based on acceleration correction model

In order to improve the accuracy of attitude unmanned aerial vehicle (UAV) navigation system in dynamic environment, an calculation algorithm based on acceleration correction model is proposed. First, established calculate estimated non-gravitational and external modify output value accelerometer, which reduces influence environment. Then, Kalman filter built, angle calculated by corrected magnetometer as measurement filtering model, designed. The experimental results show that can reduce interference calculation, avoids divergence UAV improves anti-interference ability