直升机动力失效响应特性分析  

Helicopter Power Failure Response Characteristic Analysis

作　　者：张华[1] 周禹[1] 吕增岁 

机构地区：[1]中国飞行试验研究院,陕西西安710089

出　　处：《航空科学技术》2017年第4期12-16,共5页Aeronautical Science & Technology

摘　　要：建立了旋翼转速衰减方程和机体力矩平衡方程,并结合相关飞行试验数据,分析了直升机动力失效的响应特性及其主要影响因素。研究表明,旋翼转速衰减时间随机体动部件惯性矩之和的增大而增加,随旋翼需用功率增加而减小,直升机的结构、气动特性及飞行状态等对其动力失效响应特性具有明显影响,分析结果为制定直升机动力失效特情处置方案提供了参考依据。The attenuation equation of rotor speed and torque balance equation of the body were built. This thesis analyzed the response characteristic and main influence factors when the helicopter encountered the power failure, based on the theory analysis and the flight test data. The results shows that the rotor speed attenuation time increases with the sum of the moments of inertia of the body rotoring parts, decreases with the increase of rotor required power, the structure, aerodynamic characteristics and flight condition have important effects on the response of helicopter power failure. This thesis provided a reference for making plan when the helicopter encountered the power failure.

关 键 词：直升机 动力失效 飞行试验 响应特性 

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]