The missile model with accelerometric feedback

Missile guidance system, autopilot part is used for missile guidance and missile flight stabilization. Missile autopilot uses inertial sensors, gyroscopes and accelerometers for missile movement parameters measurements. Missile accelerometric feedback is changing according to accelerometer parameters, scale factor, offset and their temperature dependency. In this article accelerometer temperature stability, accelerometer white noise and their influence are explained. The article contribution is in creation of the missile model with accelerometric feedback, measurement of missile accelerometer temperature dependency, estimation of accelerometer white noise. According missile model temperature dependency (especially accelerometer temperature dependency) there are evaluated changes of the basic cybernetics circuit parameters, normal acceleration peak values, final normal acceleration values, missile regulation times and percentage overshoots. New accelerometer Simulink model is created according to accelerometer temperature dependency measurement and white noise estimation.