A theoretical analysis, considering unsteady effects, shows that the response to collective pitch while in descending flight is largely dependent upon the rapidity of control application. Experimental tests confirm the theoretical results.
Response of a Helicopter Rotor to an Increase in Collective Pitch for the Case of Vertical Flight
1961
22 pages
Report
Keine Angabe
Englisch
Response of helicopter rotor to increase in collective pitch for case of vertical flight
Engineering Index Backfile | 1961
|Engineering Index Backfile | 1960
|ASSISTED COLLECTIVE PITCH CONTROL SYSTEM FOR A HELICOPTER ROTOR
Europäisches Patentamt | 2023
|Engineering Index Backfile | 1960
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