倾转三旋翼飞行器地面效应风洞试验

doi:10.7527/S1000-6893.2014.0353

Abstract

Abstract:

Tilt-rotor aircraft has an obvious ground effect in hover or low-speed forward flight near ground, which has a strong effect on the aircraft aerodynamic loads. According to the ground effect problems of tri tilt-rotor (TTR) aircraft, a 0.5-scale TTR aircraft model is used in tests, a movable plat is designed to simulate the height of TTR vehicle above the ground in low-speed opening wind tunnel, a rod balance is used to measure the loads on the body and particle image velocimetry (PIV) is applied to the shot of dynamic flow field underneath the body. The test results show that with the influence of ground effect, the maximum upload on the body is about 4% of the thrust of total rotors when the TTR aircraft hovers height is less than 1.25 times of the rotor diameter, and the vortex fountain flow phenomenon is observed; in low-speed forward flight, with the influence of rotor wake flow and forward flow, the upload on the body significantly reduces with respect to the hover state, and the fountain flow center shifts afterward. The test results provide a reference for the TTR unmanned aerial vehicle power system selection, design of control systems and improvement of carrying capacity by using the advantage of ground effect.

Key words: tri tilt-rotor, hovering, low-speed forward flight, ground effect, wind tunnel test, particle image velocimetry

CLC Number:

V211.7

CHEN Kun, SHI Zhiwei, SUN Jialiang. Ground effect test of tri tilt-rotor aircraft in wind tunnel[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(9): 2884-2891.

References

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Ground effect test of tri tilt-rotor aircraft in wind tunnel

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