摘要
通过对 Z1 1直升机自转特性及自转着陆的试飞 ,研究了在自转着陆的进场着陆阶段 ,如何使旋翼能够提供最大的拉力 ,减小下降率 ,使直升机以低于起落架设计允许的最大下降率进行自转着陆 ,从而保证直升机和驾驶员的安全。最后分析探讨了 Z1 1直升机空中停车后处置的驾驶技术及操纵要领。可供有关研究人员和直升机飞行员参考。
The flight test of Z11 helicopter autorotation landing has been analyzed in this paper. It has been focused to how to produce the maximum thrust of rotor propeller, to reduce descent ratio and to make helicopter autorotation land at a speed less than the maximum descent ratio, which is designed and permitted for landing-gear during the final approach and landing phase, so that to insure helicopter and pilots to be safe. Finally, driving technology and control skill after in-flight engine failure of Z11 helicopter has been discussed. This paper can be regarded as the reference for some researchers or helicopter pilots.
出处
《飞行力学》
CSCD
2001年第3期74-76,83,共4页
Flight Dynamics
关键词
自转着陆
试飞
空中停车
直升机
autorotation land
flight test
in-flight engine failure
