Air inlet duct suitable for small jet unmanned aerial vehicle with flying wing configuration

Abstract

The invention discloses an air inlet duct suitable for a small jet unmanned aerial vehicle with a flying wing configuration. The air inlet duct is in a Y shape and is divided into air inlet shaping sections, diffusion sections, mergence sections and a shrinking rectifying section. Two air inlets are formed in the upper surface of a flying wing, and the lower edges of the air inlets and the front edge of the flying wing are overlapped. The air inlet shaping sections each are in a bell shape, and the outlet area is 90% smaller than the inlet area of each air inlet shaping section. The diffusionsections on the two sides are merged through the mergence sections after complete diffusion and subjected to shrinking rectifying through the shrinking rectifying section. Internal structure arrangement is facilitated. The double-side air inlet layout is adopted on the small unmanned aerial vehicle, electronic equipment can be easily arranged on a nose, and meanwhile vehicle trim is facilitated.

Description

technical field [0001] The invention relates to an air intake of an aircraft, which belongs to the field of aircraft design. Background technique [0002] With the increasing demand for UAVs, especially the unique technical requirements for UAV launch / recovery, power plant, flight control, stealth, payload, etc., UAV systems have become independent from other aircraft. system. [0003] Since the size of small UAVs is generally small, the flight speed is also low, and the range and flight altitude are relatively small. The air intake of the aircraft has a significant impact on the performance of the jet aircraft, and it needs to be well matched with the flight speed, flight altitude and engine working status of the aircraft. Poorly matched inlets can cause low total pressure recovery and large airflow energy loss, which will have a huge impact on the performance of the aircraft; severe cases can cause high turbulence, engine surge, and even worse, cause the engine to stall ...

AI Technical Summary

Problems solved by technology

[0004] Since the flying wing layout UAV does not have a fuselage in the traditional sense, the height of the internal space is small, and the space near the central axis of the aircraft is difficult to use

If the air intake is arranged on the central axis, the relative thickness of the aircraft needs to be increased, which will increase the shape resistance of the aircraft and affect the flight performance of the aircraft

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