摘要
为探讨升推力装置对常规复合式直升机的飞行性能影响,建立了一种复合式直升机性能分析模型。以加装机翼和螺旋桨的UH-60A直升机为样例,探讨了机翼和螺旋桨参数、升推力分配对全机性能的影响机理。结果表明:低速时,机翼和螺旋桨效率低,加装机翼和螺旋桨会降低全机升阻比;螺旋桨转速越高或桨叶负扭越大,导致螺旋桨的型阻功率越大,升阻比降低越明显。高速时,机翼和螺旋桨效率增加,螺旋桨承担绝大部分推力、机翼承担大部分升力,并降低旋翼转速,为旋翼卸载,降低了旋翼诱导和型阻功率,显著提升了全机性能;升阻比随升推力分配分别先增加后降低。300 km/h时,100%、90%、85%和80%旋翼转速时,对升推力进行优化分配后,将基准直升机的升阻比分别提升了4.0%、21.33%、27.0%和30.6%。
To analyze the effects of lifting and propulsion devices for flight performance improvement of a compound helicopter, a model of performance prediction was developed. Based on the UH-60 A helicopter equipped with a wing and a propeller, the influence mechanism of parameters of the wing and propeller, lift and propulsive force shares on the performance was analyzed. At low speeds, due to the low efficiency of the wing and propeller, equipping the wing and propeller decreased the lift-to-drag ratio of the helicopter. The higher rotor speed or blade twist of the propeller led to larger profile power of the propeller, and further reduced the lift-to-drag significantly. At high speeds, the efficiency of the wing and propeller was higher;the performance was significantly improved when the wing and propeller offloaded most of the lift and propulsive force with the decrease of the main rotor speed;the lift-to-drag ratio increased first and then decreased as increasing the lift and propulsive force shares. At a speed of 300 km/h, optimizing the lift and propulsive force share, at 100%, 95%, 85% and 80% of main rotor speed, increased the lift-drag ratio by 4.0%, 21.33%, 27.0% and 30.6%, respectively.
作者
杨克龙
韩东
石启鹏
YANG Kelong;HAN Dong;SHI Qipeng(National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics,College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2020年第11期2429-2439,共11页
Journal of Aerospace Power
基金
国家自然科学基金面上项目(11972181)
旋翼空气动力学重点实验室开放基金(RAL20180201-1)
研究生创新基地(实验室)开放基金(KFJJ20190102)
江苏高校优势学科建设工程资助项目(PAPD)。
关键词
复合式直升机
机翼和螺旋桨参数
飞行性能
升阻比
升推力分配
compound helicopter
wing and propeller parameters
flight performance
lift-to-drag ratio
lift and propulsive force shares
