A design method for the aerodynamic shape of a new helicopter rotor blade
A technology of rotor blades and aerodynamic shape, applied in computer-aided design, design optimization/simulation, calculation, etc., can solve problems such as heavy workload, inability to find parameter combinations, and failure to consider the mutual influence of multiple parameters, achieving aerodynamic performance. The effect of improved performance
Active Publication Date: 2022-04-29
CHINA HELICOPTER RES & DEV INST
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Problems solved by technology
In the process of optimizing the aerodynamic layout of rotor blades, the method of artificial "sea calculation" is often used for screening, and a large number of calculations are performed for a single parameter or a limited combination of two or three parameters, and the better parameters are selected for solidification, and then other Parameters are optimized. This method not only requires a lot of work and takes a long time, but also does not take into account the interaction between multiple parameters, and cannot find the optimal parameter combination, so that the final optimized rotor blade aerodynamic layout is not optimal. aerodynamic form factor
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[0036] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.
[0037] In view of the increasingly urgent demand for low-noise and high-performance rotors of existing helicopter models and next-generation helicopter models, the optimization goals are formulated, and the optimization parameters and ranges are determined based on past engineering design experience and a large number of sensitivity analysis results of aerodynamic layout parameters. The optimization method of surrogate model and genetic algorith...
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The invention belongs to the technical field of helicopter aerodynamic design, and discloses a method for designing the aerodynamic shape of a novel rotor blade of a helicopter. In view of the increasingly urgent demand for low-noise and high-performance rotors of existing helicopter models and next-generation helicopter models, the optimization goals are formulated, and the optimization parameters and ranges are determined based on past engineering design experience and a large number of sensitivity analysis results of aerodynamic layout parameters. The optimization method of surrogate model and genetic algorithm is used to carry out iterative design and calculation of multi-wheel rotor aerodynamic layout optimization, and obtain a new rotor aerodynamic shape design scheme that meets the performance requirements.
Description
technical field [0001] The invention belongs to the technical field of helicopter aerodynamic design, in particular to a method for designing the aerodynamic shape of a novel rotor blade of a helicopter. Background technique [0002] The blade has multiple aerodynamic parameters, such as airfoil configuration, torsion distribution, chord length distribution, blade tip form, etc., and the rotor has multiple design objectives, such as hovering efficiency in hovering flight state, and forward flight in horizontal forward flight state. Therefore, the aerodynamic layout design of rotor blades is a multi-parameter, multi-objective optimization iterative process. In the process of optimizing the aerodynamic layout of rotor blades, artificial "sea calculation" is often used for screening, and a large number of calculations are performed for a single parameter or a limited combination of two or three parameters, and the better parameters are selected for solidification, and then othe...
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IPC IPC(8): G06F30/15G06F30/28G06F111/04G06F113/08G06F119/10
CPCG06F30/15G06F30/28G06F2111/04G06F2113/08G06F2119/10Y02T90/00
Inventor 曹亚雄樊枫林永峰孙朋朋
Owner CHINA HELICOPTER RES & DEV INST