旋翼变体技术对直升机性能的提升

为研究旋翼变体技术对直升机性能的提升作用,先建立旋翼模型,然后耦合机体模型,从而建立直升机需用功率计算模型.主要对比了几种不同旋翼变体技术,包括旋翼变直径、旋翼变转速、桨叶变弦长和桨叶变负扭转角在不同飞行状态时对直升机需用功率的影响.前飞速度为130km/h时,10%旋翼转速减小、10%旋翼直径减小、10%桨叶弦长减小和桨叶负扭转角由-12°变为-6°时,需用功率分别降低了15.7%,14.6%,5.8%和3.1%;前飞速度为250km/h时,10%旋翼转速减小和10%旋翼直径减小可分别降低14.5%和23.9%需用功率.结果表明,旋翼变转速明显优于桨叶变弦长和桨叶变负扭转角所取得的性能提升,高速前飞时旋翼变直径降低的需用功率大于旋翼变转速技术.

Helicopter performance improvement by rotor morphing technologies

To investigate the effect of rotor morphing technologies on helicopter performance improvement, a rotor model was derived. A fuselage model was coupled with this rotor model to establish the computational model of helicopter power. Several rotor morphing technologies, including varying rotor diameter, varying rotor speed, varying blade chord length and varying blade twist angle, were compared to investigate the influence on the helicopter power at different flight states. At the forward speed of 130km/h, 10% reduction of the rotor speed, 10% reduction of the rotor diameter, 10% reduction of the blade chord length and the blade twist angle variation from -12 degree to -6 degree, the power can reduce by 15.7%, 14.6%, 5.8% and 3.1%, respectively. At the forward speed of 250km/h, 10% reduction of the rotor speed and 10% reduction of the rotor diameter, can reduce the power by 14.5% and 23.9%, respectively. The results indicate varying rotor speed can achieve better performance improvement than varying blade chord length or varying blade twist angle. In high forward speed, varying rotor diameter can achieve better rotor power saving than varying rotor speed.