The purpose of this research is to design and analyze a new control surface for the single seat helicopter. The new control system is designed to replace the normal principle of controlling helicopters which using swash plate at the main rotor. The single seat helicopter which has a fixed coaxial rotor that not able to turn into any angle is adjusted the ways on controlling the movement of the helicopter. Basic principle of aerodynamics is used to disturbed the lift produced by the rotor blade. New control system consist of a pair of beam which 7ft each. Two plates are put at the end of each beam to react as lift disturbance. Aluminum rectangular hollow shape beam is selected in this project as it is the most suitable because of higher moment of inertia and lighter weight. 1ft square of aluminum plate is used as control surface to disturb lift produce in each side. Shear force diagram and bending moment diagram has been developed to see the location of maximum shear force and bending moment. Structural analysis has been made by using Finite Element Method that built in ANSYS software. According to the analysis made, the maximum Von Mises Stress occur at the beam is 66 MPa and the maximum deformation which is 0.00345 m occurred. This value is then been compared to the mechanical properties of the material used and the safety factor is then been calculated.
Design and Structural Analysis on Single Seat Helicopter Control Surface_ Rohilmi Jasmi_A2_2014_NI