An analysis of the transition of a helicopter from hovering to steady autorotative vertical descent

Author / Creator

Nikolsky, A. A

Available as

Online

Summary

An analytical study is presented of transition from hovering flght (power on) to steady vertical descent (in autorotation) following power failure while hovering. Effects of hinging the blades, of ...

An analytical study is presented of transition from hovering flght (power on) to steady vertical descent (in autorotation) following power failure while hovering. Effects of hinging the blades, of blade moment of inertia, and of rapidity of pitch reduction after power failure are investigated.

.Blade stalling was indicated to be negligible. It was indicated that, during transition, it is desirable that blade pitch be reduced as rapidly as possible after power failure, and blade moment of inertia be large.

Sample calculations and graphs of computed transitions for a typical helicopter is presented.

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