This paper describes a methodology for rapid design and development of the principal airframe systems for a UAV prototype. In the specific case study the prototype, the Demon UAV, is a technology demonstrator intended to achieve flapless flight. The Demon UAV is hence intended to demonstrate in flight both pitch and roll control without the use of hinged control surfaces, but instead by using fluidic devices based on the Coanda effect 24 months were allowed from the end of the conceptual design phase to the flight-ready state. The methodology was applied to the design, manufacturing and testing of a set of key subsystems; these include: 1) the auxiliary power unit (APU) which is the core of the Pneumatic Power Generation System; 2) the Pneumatic Power Distribution System, which includes ducting and a distribution plenum; 3) the Pneumatic Power Control System, which consists of eight servovalves developed in-house; 4) Landing Gear Systems.
展开▼
