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Conceptual Design for a Suav Propulsion System Sizing
| Content Provider | Semantic Scholar |
|---|---|
| Author | Jun, Yongmin Jung, Yong-Wun Yang, Soo-Seok Koea |
| Copyright Year | 2004 |
| Abstract | The concept of a tipjet rotor drive system is to use tipjet as power source to drive a rotor with its reaction force. As the aircraft is required to take-off and land vertically and cruise with high speed, it employed one rotor for hovering and cruising modes with rotor and fixed wing mechanisms respectively. In hovering mode, the exhaust gas which came from a turbojet engine passed through an internal duct system controlled by mode selection valves and went to two rotor blades. In cruising mode, the gas was controlled not to go to the rotor but to go to the main nozzle at the back of the aircraft. Inside a rotating duct, compressible flow is affected by two additional forces; centrifugal force and coriolis force and they govern the performance of the tipjet rotor system in hovering mode. The loss coefficients for the internal duct system model were chosen by empirical relations and 3-D CFD results. The conceptual design for the tipjet drive propulsion system was mainly dependant on the design code which consists of two parts, engine model and internal duct system model. In this paper, key design parameters were revealed by analyzing the characteristics of the engine and the tipjet rotor system regarding the various configurations of the internal duct system. The direction for the next design step was shown by the results of the parametric study and the sensitivity analysis. |
| File Format | PDF HTM / HTML |
| Alternate Webpage(s) | http://www.icas.org/ICAS_ARCHIVE/ICAS2004/PAPERS/164.PDF |
| Language | English |
| Access Restriction | Open |
| Content Type | Text |
| Resource Type | Article |
