New Design Approach of Compound Helicopter

Current trends in the design of helicopter have shown that in order to be economically viable and competitive it is necessary to investigate new design concept which may give an improvement in performance and operational flexibility goal and expanding the flight envelope of rotorcraft, but must be shown to be costeffective. The helicopter has carved a niche for itself as an efficient vertical take-off and landing aircraft, but have limitation on its cruising speed due to restrictions of retreating blade stall and advancing blade compressibility on the rotor in edgewise flight. This is a challenging task, which might be solved by the use of new design approach. It is believed that the application of a compound helicopter design concept would assist in achieving such a task. This paper describes an investigation aimed to examine the suitability of a compound helicopter design concept, allowing for the use of a combined conventional fix-wing aircraft with single propeller in the nose and conventional helicopter to satisfy the above objectives. The paper describes the phenomenon of presents VTOL (vertical take-off and landing) aircraft. It then discusses the benefits and penalties of the presents concept. Description is then given of the concept proposed compound helicopter which incorporated combines main rotor-wing-auxiliary propeller. It concludes with a discussion of the results and recommendations for future work. Key-Words: compound helicopter, VTOL (vertical take-off and landing), high speed helicopter, aircraft design