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The helicopter blades aeroelastic stability optimization
Wang Hongzhou * #,Liu Yong,Zhang Chenglin
National Key Laboratory of Rotorcraft Aeromechanics, Nanjing University of Aeronautics & Astronautics, Nanjing 210016, China
*Correspondence author
#Submitted by
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Funding: none
Opened online:30 June 2009
Accepted by: none
Citation: Wang Hongzhou ,Liu Yong,Zhang Chenglin.The helicopter blades aeroelastic stability optimization [OL]. [30 June 2009] http://en.paper.edu.cn/en_releasepaper/content/33500
 
 
it deduces the helicopter rotor blade motion and give the aeroelastic stabile condition. The variables is the offset of hinge pretwist angle, coning angle and element mass of blade. The constrains are the stable parameter and frequencies. The objective function is to minimize the blade mass. Using the Sequential Quadratic Programming（NLPQL）algorithm and reliable optimization. It is the result that the blade mass is increased under the constraints being satisfied and all the design parameter’s reliability is 95%.
Keywords:aeroelastic stabile;reliable optimization;pretwist angle;Sequential Quadratic Programming（NLPQL）algorithm
 
 
 

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