| 摘要 |
An enhanced pulse detonation engine (PDE) system for application in an aircraft capable of vertical takeoff and vertical landing (VTOVL) is described. The PDE system described herein may be installed onto a round vehicle platform whereby many PDE chamber and ejector tube assemblies are mounted with the ejector tubes facing towards a rotating bladed fan which, in certain embodiments, provides VTOVL flight and gyro stabilization. The angle and design of the fan blades are such that when the fan is rotated by exhaust force, the fan pulls fresh air through the aircraft's interior ducting, cooling the assemblies and adding more air mass for lift. Ignition rotation is adjustable (with or opposite fan rotation) to maximize the fan's thrust output. The design of the fan blade angle is optimized to provide low acoustical detection, low exhaust thrust temperature signature, and maximum air pull-through for lift.
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