A method for analyzing the aeroelastic stability of a helicopter rotor in forward flight, Issue 1332
National Aeronautics and Space Administration, 1969 - Computers - 107 pages
Aerodynamic stability of helicopter rotor in forward flight.
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DEVELOPMENT OF THE BASIC METHOD
APPLICATION OF THE METHOD
2 other sections not shown
2mfie advance ratio aerodynamic forces aeroelastic aeroelastic stability American Helicopter Society analyzed appearing in Eq Blade motions blade section calculations characteristic polynomial computer program CONSTT CONTINUE coupled mode CVLL degree polynomial degrees of freedom DELTV derived differential equations digital computer DIMENSION direct time integration dz2 dz elastic axis elements equations of motion equations with periodic experimental fi(Z Figure flapping and lead-lag flapping motion forward flight Fourier coefficients Helicopter Rotor infinite determinant lead-lag hinges linear dynamic system LLV0 LLVO mass center method mn mn mode shapes model rotor modes of free ninth-order system obtained ORDER SYSTEM periodic coefficients periodically varying perturbation equations Polynomial Factor POLYNOMIVL Reference 12 RETURN END REVL rotating rotor blade rotor in forward second-order solution of Eq SUBROUTINE TEMP three degrees tions TISNOO unit span XI XR XI