M-DOT proposes to design, fabricate and test a tiny gas turbine which will be configured as a turbojet. The design will be based on the aerodynamic flow path of M-DOT's DARPA-funded TPR80-1 turboprop engine which is currently under test. The engine as projected, will be approximately 1/5 scale, have a static thrust of 6.2 newtons (1.4 lbs), a maximum diameter less than 4.0 cm and approximate mass of 85 g. As a gas generator supplying a tip-jet driven fan, maximum power output would be 0.75 kw (1.0 hp). On a micro UAV with characteristic length of 15 cm, this engine will afford vertical takeoff, 100 kph dash capability, hover capability and 1-hour mission duration using heavy fuel. Phase I Technical Objectives are: 1) Perform a mission and vehicle analysis to identify desired engine performance characteristics, interfaces and installation envelope, 2) Determine the engine scale that best meets the performance requirements identified by the mission study, 3) Conduct a system trade study that compares an integrated electrical generator and power conditioning electronics to a battery, 4) Design, fabricate and text a prototype turbojet, and 5) Create a Phase II program plan for design refinement, fabrication and flight test of the engine and tip-jet-driven lift fan.
