Aerodynamic Optimisation of Hovering Helicopter Rotors using Efficient and Flexible Shape Parameterisation

Morris, Asa; Allen, Christian B; Rendall, Thomas

doi:10.2514/6.2008-7338

Cited by 6 publications

(3 citation statements)

References 20 publications

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“…Examples of such an approach are given in Refs. [16][17][18]. The constraint on lift coefficient is set to maintain the trim condition of the entire helicopter and reduce the interaction with blade dynamics.…”

Section: Deterministic Forward Flight Optimizationmentioning

confidence: 99%

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Assessment of robust optimization for design of rotorcraft airfoils in forward flight

Fusi

Congedo

Guardone

et al. 2020

Aerospace Science and Technology

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The paper compares the deterministic and robust approaches to improve the aerodynamic design of helicopter airfoils. The two formulations are different due to the characteristics of each approach. In the deterministic case, the objective of optimization is the minimization of drag while maintaining a level of lift that guarantees satisfaction of trimming condition. In the case of robust design, a range of angles of attack and not a single trim condition is considered. Thus, the robust optimization takes the lift-to-drag ratio as a measure of the performance of the airfoil, imposing at the same time inequality constraint on the lift coefficient to guarantee a sufficient level of lift, and then checking after optimization that the trimming condition can be satisfied. The two approaches are compared showing pros and cons of the robust framework. In general, the robust approach shows the capability to reach the same mean performance of the deterministic one, but with a lower degradation of performances in off-design situations considered through the uncertainty. On the other side, the difficulties in imposing the lift trim condition for the robust formulation may lead to results of limited use.

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Section: Deterministic Forward Flight Optimizationmentioning

confidence: 99%

“…This is the approach followed in several works on optimization of airfoils for rotorcraft, see Refs. [16][17][18].…”

Section: Introductionmentioning

confidence: 99%

Assessment of robust optimization for design of rotorcraft airfoils in forward flight

Fusi

Congedo

Guardone

et al. 2020

Aerospace Science and Technology

View full text Add to dashboard Cite

show abstract

“…Then, a deterministic optimization of helicopter rotor airfoil in forward flight is performed, which consists typically in the minimization of the drag coefficient C D ensuring the satisfaction of constraints on the lift C L and moment C M coefficients [27,28,9]. Drag coefficient is used instead of torque, because a single radial station is considered, and a single airfoil is optimized.…”

Section: Deterministic Optimizationmentioning

confidence: 99%

Shape optimization under uncertainty of morphing airfoils

et al. 2017

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This paper is devoted to the formulation of a novel optimization under uncertainty framework for the definition of optimal shapes for morphing airfoils, applied here to advancing/retreating 2D airfoils. In particular, the morphing strategy is conceived with the intent of changing the shape at a given frequency to enhance aerodynamic performance. The optimization of morphing airfoils presented here only takes into account the aerodynamic performance. The paper is then focused on an aerodynamic optimization to set the optimal shape with respect to performance, where technological aspects are inserted through geometrical constraints. In fact, this paper presents an exploratory work on morphing geometries which aims at understanding the relationship between shape degree of freedom and actual aerodynamic gain. Thus, exploring and demonstrating the gain of the aerodynamic shape may drive the development of new mechanism for the realization of morphing structures, which could be applied to helicopter rotor blades

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Parametric structure optimization of a main rotor blade as an application for FSI analysis in main rotor optimization process

Kocjan,

Rogólski

2024

AEAT

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Purpose Modern warfare and modern battlefield are very demanding. The recent conflicts showed that the usage of the helicopters is very limited and only the best constructions are able to provide support for the operations. The purpose of this research is to show the possibilities of new design tool for main rotor aerostructural optimization. It is a next chapter of the research that is aimed at finding new solutions for rotorcraft constructions. Design/methodology/approach This work presents a method of preliminary structure optimization of the main rotor blade using parametric modeling. It is the next step in the main rotor optimization studies. It is the next step after preparing the parametric model for the external shape CFD analysis. As a basis for parametric blade structure calculations, the analytical model is provided in this paper. The equations of rigid blade loads and, as a consequence of the strength elements, stresses are shown. The parametric blade modeling is conducted using the Graphic Integrated Programming language. The parametric design method is shown to be used for various blade planform models and different section airfoils. The structure of a blade is generated automatically after the user enters the parameters. The code-inbuilt analysis systems provide a quick inertia examination of the generated geometry, which is the basis for further optimization. The program calculates the blade loads and verifies them with the given material conditions and proposed safety factors. In the analysis, composite materials for the strength elements were proposed. Findings The results of this research showed the application of parametrization into the main rotor blade design loop. It was presented that the main rotor blade structure can be enhanced using fluid-structure interaction (FSI) methods. The time saving with the implementation the process into design loop is shown. Practical implications This work can be practically used in the main rotor blade design process. It provides the possibilities to check various blade aerodynamic configuration in a structure strength aspect. Originality/value To the best of the authors’ knowledge, there were no published research that combines the main rotor FSI analysis. The method, which is presented in the work, provides a new approach to a rotorcraft design. The application of the parametrization and combining it with the FSI method gives a novel solution for helicopters construction enhancement.

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Aerodynamic Optimisation of Hovering Helicopter Rotors using Efficient and Flexible Shape Parameterisation

Cited by 6 publications

References 20 publications

Assessment of robust optimization for design of rotorcraft airfoils in forward flight

Assessment of robust optimization for design of rotorcraft airfoils in forward flight

Shape optimization under uncertainty of morphing airfoils

Parametric structure optimization of a main rotor blade as an application for FSI analysis in main rotor optimization process

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