Online from: 1929
Subject Area: Mechanical & Materials Engineering
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|Title:||Configuration design and optimisation study of a compound gyroplane|
|Author(s):||Ngoc Anh Vu, (Aerospace Information Engineering Department, Konkuk University, Seoul, South Korea), Young-Jae Lee, (Aerospace Information Engineering Department, Konkuk University, Seoul, South Korea), Jae-Woo Lee, (Aerospace Information Engineering Department, Konkuk University, Seoul, South Korea), Sangho Kim, (Aerospace Information Engineering Department, Konkuk University, Seoul, South Korea), In Jae Chung, (Agency for Defense Development, Dae Jeon, South Korea)|
|Citation:||Ngoc Anh Vu, Young-Jae Lee, Jae-Woo Lee, Sangho Kim, In Jae Chung, (2011) "Configuration design and optimisation study of a compound gyroplane", Aircraft Engineering and Aerospace Technology, Vol. 83 Iss: 6, pp.420 - 428|
|Keywords:||Aircraft, Aircraft sizing, Compound gyroplane, Design optimisation, Helicopters|
|Article type:||Research paper|
|DOI:||10.1108/00022661111173298 (Permanent URL)|
|Publisher:||Emerald Group Publishing Limited|
|Acknowledgements:||This work was supported by a National Research Foundation Grant funded by the Korean Government with project reference K2060100001, and also the Defence Acquisition Program Administration and Agency for Defence Development in Republic of Korea under contract UD070041AD.|
Purpose – The purpose of this paper is to study the conceptual design and optimisation of a compound gyroplane. A study of a compound gyroplane configuration and its characteristics was performed to develop a sizing program.
Design/methodology/approach – The vertical takeoff and landing capabilities of a helicopter are particularly important. The need for efficient hover and the effectiveness of forward flight in the helicopter can cause conflicts within the design process. The designers usually wish to increase the helicopter's maximum forward speed. Recently, the compound aircraft is one of the concepts considered for the purpose of expanding the flight envelope of rotorcraft. The study of the compound gyroplane showed its advance capabilities for this purpose. Understanding its characteristics, a number of calculations are conducted to implement a sizing program for compound gyroplanes based on the conventional helicopter sizing process.
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. The program is appropriate to size a compound gyroplane at the conceptual design phase. An optimisation study was also performed to enhance sizing results. 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. The optimum results showed that the TOGW of all four kinds of compound gyroplanes was considerably reduced.
Originality/value – A conceptual sizing program for unconventional compound aircraft was developed. The study showed that an optimum design process is necessary to enhance the sizing results.
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