直升机惯性交感对操稳特性和突风响应的影响  

THE INFLUENCE OF THE INERTIA COUPLING ON THE STABILITY AND CONTROL OF THE HELICOPTER AND THE RESPONSE OF HELICOPTER GUST

作　　者：许心钰[1] 陈仁良[1] 

机构地区：[1]南京航空学院

出　　处：《飞行力学》1990年第1期44-51,共8页Flight Dynamics

摘　　要：本文研究直升机惯性交感对操稳以及对在突风中响应的影响.旋翼动力学模型采用水平铰外伸和根部弹性约束,诱导速度在桨盘处的分布采用广义涡流理论所导的公式,突风模型为飞行品质规范所要求的正弦平方型.最后以某典型机为算例,比较了计及惯性交感与否的操稳特性和突风响应的影响.The influence of the inertia coupling on the stability and control of the helicopter and the response of helicopter to dispersed gust are investigated in this paper. An articulated rotor with a blade hinge offset and with an elastic restraint about the flap hinge are used as the rotary wing dynamic model. The nonuniform distribution of induced velocity on the rotor disk derived from the generalized vortex theory is taken into account. The model of the dispersed gust is the sine-squared according to the demand of the specification. A sample calculation of a typical helicopter has been made. Considering the inertia coupling and not and comparing the two states, the detail calculation and analysis of the stability, control and the response of helicopter to dispersed gust are given.

关 键 词：直升机 惯性交感 突风响应 稳定性 

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]