Theoretical analysis, considering unsteady effects, shows that response to collective pitch while in descending flight is largely dependent upon rapidity of control application; experimental tests confirm results. Translation from Technique et Science Aeronautiques n 3 May-June 1959 p 177-83.
Response of helicopter rotor to increase in collective pitch for case of vertical flight
NASA -- Tech Translation
1961
20 pages
Report
English
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Engineering Index Backfile | 1960
|ASSISTED COLLECTIVE PITCH CONTROL SYSTEM FOR A HELICOPTER ROTOR
European Patent Office | 2023
|Engineering Index Backfile | 1960
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