Simulation and modelling of flight missile dynamics and autopilot analysis

Document Type : Original Article

Authors

1 Egyptian Armed Forces, Egypt.

2 Military Technical College, Egypt.

10.1088/1757-899X/610/1/012033

Abstract

In the current paper, nonlinear modelling and dynamical analysis of a surface to surface missile with both aerodynamic and thrust vector control is investigated. Aerodynamic force and moment modelling of the presented missile includes the challenging high angle of attack aerodynamics behaviour and the so-called hybrid control, which utilizes both tail fins for
stabilization and rudder vanes as control surfaces. Then, concerning relative rotation between bodies, the missile aerodynamic model is built by Leabedev aerodynamic calculations software. After using the generated aerodynamic data obtained the required aerodynamic stability derivatives, the required transfer functions are resolute based on the equations of motion of the missile. The missile dynamic motion in pitch and roll channel are analysed. The guidance and control strategy are developed through an actuation system and autopilot design in the four channels based on the poles assignment technique. The roll autopilot is constructed to regulate the roll angle of the front body of the missile which is the controlled part, for the command signals generated by the guidance laws both pitch and yaw autopilots are designed to realize. The guidance command is in the form of rate of change of flight path angles of the missile with time.
International Conference on Aerospace Sciences and Aviation Technology
Volume 18, Issue 18
18th International Conference on Aerospace Sciences & Aviation Technology 9–11 April 2019
April 2019
Pages 1-11

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