直升机自转飞行的最大过载系数试飞验证

为了验证直升机自转飞行的最大过载系数,首先从直升机最大过载系数理论估算模型入手,分析最大过载系数的关键影响因素;其次,通过对模拟自转下滑和俯冲拉起试飞方法的研究,确定自转情况俯冲拉起的初始试验高度、自转进入速度以及纵向重心位置;最后,提出了一种自转情况俯冲拉起试飞方法并经飞行试验验证,结果表明:该方法能够验证直升机自转飞行的最大过载能力;获取的过载系数随拉杆量、旋翼转速的变化关系曲线与理论分析吻合.这对试飞工程师和试飞员理论、驾驶技术培训具有较高的科学研究和推广应用价值.

Flight Test Verification of Maximum Overload Coefficient for Helicopter Autorotation Flight

In order to verify the maximum overload coefficient of helicopter autorotation flight, the key influencing factors of the maximum overload coefficient were analyzed from the theoretical estimation model of the helicopter maximum overload coefficient. Secondly, the initial test height, the entry speed of autorotation and the longitudinal gravity center position, beacause of spin-pull, were determined through the study of the simulated test methods of autorotation sliding, dive and pull up. Finally, the autorotation dive and pull up test method was proposed and verified by flight tests. The results show that this method can verify the maximum overload capacity of helicopter autorotation flight, that variation curves, the amount of overload coefficient obtained by the test with the pull stick and rotor speed, are in accordance with the theoretical analysis. The results have very strong reference value to the scientific research and application of theory of flight test engineer and test pilot, driving skill training.