SUMMARY A detailed account is given of the aerodynamic and inertia forces acting on a rotor blade when the helicopter is undergoing arbitrary disturbance in velocity and angular velocity. A fairly generalized form is used for the downwash velocity. A principle is enunciated enabling the several second order terms of significance in the angle variables to be recognized and retained.
Rotor Dynamics and Helicopter Stability
Development of a Unified Mathematical Theory of the Steady and Disturbed Motion of a Helicopter with Particular Emphasis on the Dynamical Aspects of the Problem
Aircraft Engineering and Aerospace Technology ; 35 , 6 ; 168-172
1963-06-01
5 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Rotor Dynamics and Helicopter Stability
Emerald Group Publishing | 1964
|Rotor Dynamics and Helicopter Stability
Emerald Group Publishing | 1964
|Rotor Dynamics and Helicopter Stability
Emerald Group Publishing | 1963
|Rotor Dynamics and Helicopter Stability
Emerald Group Publishing | 1963
|Rotor Dynamics and Helicopter Stability
Emerald Group Publishing | 1963
|