![]() ![]() The rotor is then disconnected from the engine and Carter Aviation also claims the system is safer than aĬarterCopter should be capable of the higher airspeeds that can only be achievedīy fixed wing aircraft, but also able to land in any small area in anĪt takeoff the pilot angles the top rotor flat (zero angle of attack) and To leverage the advantages of fixed wings as well as gyrocopters, giving almostĪll the capabilities of helicopters (except hovering) but with a relatively Little drag, and the company claims that the aircraft would be potentially able The low rotation speed and flat feathering of the rotor means that it causes Helicopter this would cause massive lift asymmetry and insoluble control issuesīut the fixed wings keep the aircraft in the air and stable. ![]() The rotor spins with a tip speed belowĪirspeed, which means that the retreating blade flies completely stalled. Wings, with the rotor simply windmilling. Very brief hover, and can land more or less vertically.Īt high speed (above about 100 mph) the aircraft flies mostly using the fixed At low speed, the vehicleįlies as a gyrocopter, and can pre-spin the rotor for a vertical takeoff and Heavy rotor, supplemented with conventional wings. The CarterCopter concept is a gyrocopter with an unusually stiff, relatively It is an all-composite design The tricycle undercarriage is retractable. The rotor is a two-bladed design weighted with 55 pounds Aircraft Engineering and Aerospace Technology Emerald Publishing The Carter copter is a pusher configuration autogyro with wingsĪnd a twin boom tail. The study showed that an optimum design process is necessary to enhance the sizing results. Originality/value – A conceptual sizing program for unconventional compound aircraft was developed. The optimum results showed that the TOGW of all four kinds of compound gyroplanes was considerably reduced. ![]() The compromise between the rotor lift sharing factor and the ratio of the wing span (Bw) to rotor diameter (D) was solved by choosing the total gross weight (TOGW) as the objective function, while the design variables are compromising factors. An optimisation study was also performed to enhance sizing results. The program is appropriate to size a compound gyroplane at the conceptual design phase. Findings – The results of the sizing program were validated using existing aircraft data such as the Challis Heliplane, Carter Copter, FB‐1 Gyrodyne, and Jet Gyrodyne. Understanding its characteristics, a number of calculations are conducted to implement a sizing program for compound gyroplanes based on the conventional helicopter sizing process. The study of the compound gyroplane showed its advance capabilities for this purpose. Recently, the compound aircraft is one of the concepts considered for the purpose of expanding the flight envelope of rotorcraft. The designers usually wish to increase the helicopter's maximum forward speed. The need for efficient hover and the effectiveness of forward flight in the helicopter can cause conflicts within the design process. Design/methodology/approach – The vertical takeoff and landing capabilities of a helicopter are particularly important. A study of a compound gyroplane configuration and its characteristics was performed to develop a sizing program. Purpose – The purpose of this paper is to study the conceptual design and optimisation of a compound gyroplane. Ngoc Anh Vu Young‐Jae Lee Jae‐Woo Lee Sangho Kim In Jae Chung Configuration design and optimisation study of a compound gyroplane Configuration design and optimisation study of a compound gyroplane ![]()
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