摘要
倾转旋翼机的机翼端部装有一个可倾转的旋翼.所建立的倾转旋翼机前飞动力学稳定性分析简化模型由一个机翼和一个螺旋桨旋翼组成.机翼承受垂向弯曲、弦向弯曲和扭转变形,螺旋桨旋翼的桨叶认为是刚性的并承受一阶挥舞和摆振.机翼和螺旋桨旋翼的空气动力学载荷由准定常片条理论得到.利用此模型在高入流状态下建立运动微分方程,对倾转旋翼机在前飞状态下的动力学稳定性进行计算,计算结果与Bell公司试验结果基本一致,表明该模型可用于倾转旋翼机的前飞动力学稳定性分析.
Tiltrotor aircraft has a tilting proprotor at the tip of wing. The analytical model of dynamic stability for tiltrotor aircraft in forward flight in this paper consists of a cantilever wing and a rotor. The wing withstands vertical bending, chordwise bending and torsional deformations, and the rotor blade is considered to be capable of rigidly withstanding one order flap and lag motions. The aerodynamic loads are gained by quasi-steady flow and thin wing theory. Using the model, the differential equations of motion have been formulated under the condition of high inflow, making it possible to analyze the dynamic stability of tiltrotor aircraft in forward flight. The numerical results are basically consistent with the experimental results obtained by the Bell Helicopter Company, showing that the analytical model is suitable for analyzing the dynamic stability of tiltrotor aircraft in forward flight.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第11期1863-1867,共5页
Journal of Aerospace Power
基金
直升机旋翼动力学国家级重点实验室基金项目
关键词
航空
航天推进系统
倾转旋翼机
前飞状态
稳定性
aerospace propulsion system
tiltrotor aircraft
forward flight
dynamic sta bility
