Please use this identifier to cite or link to this item: https://hdl.handle.net/11681/46261
Title: Helicopter rotor blade planform optimization using parametric design and multi-objective genetic algorithm
Authors: Wenren, Yonghu
Lim, Joon W.
Allen, Luke D.
Haehnel, Robert B.
Dettwiller, Ian D.
Keywords: Helicopters--Design
Rotors (Helicopters)--Design
Helicopters--Computer simulation
Rotors (Helicopters)--Computer simulation
Genetic algorithms
Publisher: Engineer Research and Development Center (U.S.)
Series/Report no.: Miscellaneous Paper (Engineer Research and Development Center (U.S.)) ; no. ERDC MP-22-7
Is Version Of: This paper was originally presented at the Vertical Flight Society’s 78th Annual Forum & Technology Display, Fort Worth, TX, on May 10-12, 2022.
Abstract: In this paper, an automated framework is presented to perform helicopter rotor blade planform optimization. This framework contains three elements, Dakota, ParBlade, and RCAS. These elements are integrated into an environment control tool, Galaxy Simulation Builder, which is used to carry out the optimization. The main objective of this work is to conduct rotor performance design optimizations for forward flight and hover. The blade design variables manipulated by ParBlade are twist, sweep, and anhedral. The multi-objective genetic algorithm method is used in this study to search for the optimum blade design; the optimization objective is to minimize the rotor power required. Following design parameter substitution, ParBlade generates the modified blade shape and updates the rotor blade properties in the RCAS script before running RCAS. After the RCAS simulations are complete, the desired performance metrics (objectives and constraints) are extracted and returned to the Dakota optimizer. Demonstrative optimization case studies were conducted using a UH-60A main rotor as the base case. Rotor power in hover and forward flight, at advance ratio 𝜇𝜇 = 0.3, are used as objective functions. The results of this study show improvement in rotor power of 6.13% and 8.52% in hover and an advance ratio of 0.3, respectively. This configuration also yields greater reductions in rotor power for high advance ratios, e.g., 12.42% reduction at 𝜇𝜇 = 0.4.
Description: Miscellaneous Paper
Gov't Doc #: ERDC MP-22-7
Rights: Approved for Public Release; Distribution is Unlimited
URI: https://hdl.handle.net/11681/46261
http://dx.doi.org/10.21079/11681/46261
Appears in Collections:Miscellaneous Paper

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