TY - JOUR
T1 - EFFECT OF STRUCTURAL COUPLING PARAMETERS ON THE FLAP-LAG FORCED RESPONSE OF A ROTOR BLADE IN FORWARD FLIGHT USING FLOQUET THEORY.
AU - Schrage, Daniel P.
AU - Peters, David A.
PY - 1978
Y1 - 1978
N2 - An eigenvalue and modal decoupling method to predict helicopter rotor stability and forced response has been successfully developed. Using this method, it has been found that the major rotor coupling parameters can be chosen in a systematic way to achieve stability and low rotor loads. The following sequence indicates the manner in which the parameters could be chosen during preliminary design: The first parameter to choose should be the elatic coupling, R. The results for the rotors analyzed show that zero elastic coupling gives the smallest inplane loads. The second parameter to be chosen is pitch-flap coupling, theta // beta . This parameter should be given a large negative value in order to greatly reduce the 1/REV flapping loads. The third parameter to be chosen is the pitch-lag coupling, theta // zeta . Pitch-lag coupling has been shown to have little effect on loads but a large effect on stability.
AB - An eigenvalue and modal decoupling method to predict helicopter rotor stability and forced response has been successfully developed. Using this method, it has been found that the major rotor coupling parameters can be chosen in a systematic way to achieve stability and low rotor loads. The following sequence indicates the manner in which the parameters could be chosen during preliminary design: The first parameter to choose should be the elatic coupling, R. The results for the rotors analyzed show that zero elastic coupling gives the smallest inplane loads. The second parameter to be chosen is pitch-flap coupling, theta // beta . This parameter should be given a large negative value in order to greatly reduce the 1/REV flapping loads. The third parameter to be chosen is the pitch-lag coupling, theta // zeta . Pitch-lag coupling has been shown to have little effect on loads but a large effect on stability.
UR - https://www.scopus.com/pages/publications/0018205031
M3 - Conference article
AN - SCOPUS:0018205031
SN - 0160-8835
SP - 23. 1-23. 23
JO - American Society of Mechanical Engineers, Applied Mechanics Division, AMD
JF - American Society of Mechanical Engineers, Applied Mechanics Division, AMD
T2 - Eur Rotorcr and Powered Lift Aircr Forum, 4th, Pap
Y2 - 13 September 1978 through 15 September 1978
ER -