直升机吊挂飞行平衡、稳定性与操纵性研究  

Studies on trims,stability,and controllability of helicopter with slung-load

作　　者：崔利[1] 曹义华[1] 李国知[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《航空动力学报》2010年第10期2307-2311,共5页Journal of Aerospace Power

摘　　要：建立带吊挂载荷的直升机飞行动力学模型,其中吊挂载荷为单点悬挂在直升机机身底部的六自由度模型,并计入了吊挂模型的气动阻力.对所建立模型进行配平,并将结果与参考数据对比.通过仿真计算分析了直升机吊挂前飞状态下的稳定性,此外,分析了在吊挂相关参数改变时直升机稳定性的相应变化,最后,分析了当施加纵向周期变距阶跃输入、横向周期变距阶跃输入以及尾桨距阶跃输入时带吊挂直升机的动力学响应历程.A rotorcraft with slung-load model was built.Slung-load model with six freedoms was used to simulate the flight process with slung-load.It is assumed that the external slung-load is suspended in a single-point.Trim calculation of the helicopter with slung-load model was conducted and compared with the reference values.Stability of helicopter with slung-load was analyzed in forward flight,and the change of stability was compared when some parameters were adjusted.At last,the dynamic response to the step inputs of the longitudinal,lateral and pedal controls was analyzed in forward flight simulation.

关 键 词：直升机 吊挂 稳定性 操纵性 动力响应 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]