直升机前飞吊挂飞行动力学响应分析  

Control response character of the rotorcraft with slung load in forward flight

作　　者：郭广利[1] 高正[1] 孙传伟[1] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016

出　　处：《北京航空航天大学学报》2005年第10期1087-1091,共5页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：建立了带吊挂载荷的直升机飞行动力学模型,其中旋翼诱导速度场计算采用了广义动态入流理论模型并添加了畸变项,用以考虑从加速过程的尾迹畸变和附加非定常效应;旋翼气动载荷模型采用了翼型大角度范围插值技术,并结合经典薄翼型理论建立综合的非定常气动载荷模型.还建立了六自由度吊挂载荷模型,其中吊索采用了柔性钢索模型,计入了吊挂模型的气动阻力.通过仿真计算分析了吊挂前飞状态下总距阶跃操纵输入以及前推杆阶跃操纵输入时直升机及吊挂动力学响应历程.A rotorcraft with slung-load model was built for the general real-time flight simulation program. A general dynamic, distortional wake model based on the nonlinear and unsteady Peters-He inflow model was investigated and applied to the real-time wake model, it was an important part in the forward acceleration flight because the wake distortion effect and the blade unsteady aerodynamics relation to the whole aerodynamic force. The steady part of blade circulated airload was calculated by the full angle wind test data for all airfoils of the blade, but the unsteady part of the blade load was just a classical ONERA thin airfoil theory with dynamic stall. A six freedom slung load with a soft cable model was used to simulate the slung and also the helicopter motion. The control response character was analyzed in forward flight simulation under the step inputs of the collective pitch and push/pull stick control.

关 键 词：直升机 吊挂 尾迹畸变 操纵 响应 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程]