Efficient Global Optimization of Helicopter Rotor Blades for Vibration Reduction in Forward Flight

Glaz, Bryan; Friedmann, Peretz P.; Liu, Li

doi:10.2514/6.2006-6997

Cited by 7 publications

(6 citation statements)

References 32 publications

(34 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Similar results demonstrating the superiority of the EGO algorithm for optimization in the BVI regime can be found in Ref. 25.…”

Section: Single Objective Function Optimization Resultssupporting

confidence: 77%

“…The EGO algorithm was first applied to the vibration reduction problem in Ref. 25, where it was shown that EGO was superior to "one-shot" optimization for reduction of BVI-induced vibrations. The objectives of this paper are to (1) demonstrate the effectiveness of EGO combined with kriging surrogates for vibration reduction at low advance ratios, where BVI-induced vibrations dominate, as well as high advance ratios where dynamic stall induced vibrations are critical;…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Helicopter Vibration Reduction throughout the Entire Flight Envelope Using Surrogate-Based Optimization

Glaz¹,

Friedmann²,

Liu³

2009

j am helicopter soc

Self Cite

View full text Add to dashboard Cite

The effectiveness of surrogate-based optimization of helicopter rotor blades for vibration reduction at both low-and highspeed forward flight is studied. The efficient global optimization (EGO) algorithm is used to conduct a global search of the design space. Vibration levels in the low-speed regime are caused primarily by blade-vortex interaction (BVI), and vibrations at high advance ratios are caused by dynamic stall. Although the source of high vibrations is different for both flight conditions, the results show that the EGO algorithm is effective in finding reduced vibration designs at both flightconditions. Furthermore, the results indicate that it is possible to design a blade with reduced vibration levels at both flight conditions. However, a single design that is best for both flight conditions does not exist. Therefore, multiobjective function optimization techniques were employed to identify Pareto optimal designs.

show abstract

“…Similar results demonstrating the superiority of the EGO algorithm for optimization in the BVI regime can be found in Ref. 25.…”

Section: Single Objective Function Optimization Resultssupporting

confidence: 77%

Section: Introductionmentioning

confidence: 99%

Helicopter Vibration Reduction throughout the Entire Flight Envelope Using Surrogate-Based Optimization

Glaz¹,

Friedmann²,

Liu³

2009

j am helicopter soc

Self Cite

View full text Add to dashboard Cite

show abstract

“…This weight scheme was selected for two reasons: (1) so that the EGO algorithm would focus on a more global search initially and then move to a more local search within regions of high probability of improvement, and (2) because these weights were shown to be effective for BVI vibration reduction. 37 The weighted sum approach to multi-objective function optimization was conducted with the following values of W : 0.0, 0.25, 0.50, 0.75 and 1.0. All optimization results are compared to a baseline blade with cross-sectional properties resembling an MBB BO-105 blade.…”

Section: Ivb Passive Reduction Resultsmentioning

confidence: 99%

Vibration Reduction and Performance Enhancement of Helicopter Rotors Using an Active/Passive Approach

Glaz¹,

Friedmann²,

Liu³

2008

49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference &Amp;lt;br> 16th AIAA/ASME/AHS Ada

Self Cite

View full text Add to dashboard Cite

Active/passive optimization of helicopter rotor blades for vibration reduction and performance enhancement at high advance ratios is studied. Dynamic stall is the dominant source of high vibration levels for this flight regime. In the active/passive approach, active control of vibration and required rotor power is implemented with partial span trailingedge flaps operating according to a closed-loop control algorithm. The blade/flap combination is optimized simultaneously using the Efficient Global Optimization (EGO) algorithm. However, due to strong trade-offs between the objective functions, there is no single best active/passive configuration for reduced vibration levels and power consumption. Therefore, a surrogate based multi-objective function optimization approach is employed to find the active/passive configurations corresponding to the best trade-offs between vibration and performance characteristics.

show abstract

“…EGO has recently been applied to practical engineering problems by several studies [5][6][7]. EGO was originally built in order to solve unconstrained optimization problems.…”

Section: Introductionmentioning

confidence: 99%

Efficient global optimization incorporating feasibility criterion for the design of a supersonic inlet

Lee

Ahn

Bae

et al. 2011

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

The optimal design of a supersonic inlet is generally performed with expensive computer analysis such as the computational fluid dynamics. Thus, the feasibility criterion was incorporated into efficient global optimization (EGO) in order to efficiently perform optimal design of a supersonic inlet in this study. The strategy of EGO incorporating feasibility criterion is to improve computational efficiency by skipping unessential updation of the Kriging surrogate model of constraint function. The surrogate model is not updated when a new sample is expected to be feasible by feasibility criterion. The efficiency of EGO incorporating feasibility criterion was demonstrated by the test functions. Then, this method was applied to the optimal design of a supersonic inlet. The objective function is the coefficient of cowl drag. The constraint functions are the pressure recovery and mass flowrate. As a result, the EGO incorporating feasibility criterion for the design of a supersonic inlet was effectively performed with lower computational cost.

show abstract

Efficient Global Optimization of Helicopter Rotor Blades for Vibration Reduction in Forward Flight

Cited by 7 publications

References 32 publications

Helicopter Vibration Reduction throughout the Entire Flight Envelope Using Surrogate-Based Optimization

Helicopter Vibration Reduction throughout the Entire Flight Envelope Using Surrogate-Based Optimization

Vibration Reduction and Performance Enhancement of Helicopter Rotors Using an Active/Passive Approach

Efficient global optimization incorporating feasibility criterion for the design of a supersonic inlet

Contact Info

Product

Resources

About