NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Sources of helicopter rotor hub inplane shearsSources of helicopter rotor hub inplane shears are identified using simplified equations and the full aeroelastic analysis code, CAMRAD/JA (Johnson, 1988). Analytical results are obtained for an articulated rotor operating at moderate thrust and high airspeed. It is found that the blade chordwise inplane shear, which includes the aerodynamic component, the Coriolis contribution, and the inertial component, and the hub inplane shears are strongly dependent on the out-of-plane response. The sources of helicopter rotor hub inplane shears lie not only in the inplane response but depend on the flap and elastic flatwise responses/modes.
Document ID
19930049930
Document Type
Conference Paper
Authors
Kottapalli, Sesi (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: AIAA(ASME)ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 34th and AIAA/ASME Adaptive Structures Forum, La Jolla, CA, Apr. 19-22, 1993, Technical Papers. Pt. 1 (A93-33876 1
Subject Category
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number
AIAA PAPER 93-1358
Distribution Limits
Public
Copyright
Other

Related Records

IDRelationTitle19930049879Analytic PrimaryAIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 34th and AIAA/ASME Adaptive Structures Forum, La Jolla, CA, Apr. 19-22, 1993, Technical Papers. Pts. 1-6