Robust design and optimization of UAV empennage

Klimczyk, Witold Artur; Goraj, Zdobysław

doi:10.1108/aeat-11-2016-0221

Cited by 12 publications

(8 citation statements)

References 15 publications

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“…Similar procedures, although using more advanced methods (higher fidelity), are presented in Klymcyzk and Goraj. 11,12 The numerical optimization included aerodynamic analysis, mass estimation and flight dynamics analysis. The aerodynamic analysis for the optimization was done with the use of the first-order panel method Panukl, 13,14 coupled with two-dimensional viscous analysis of an airfoil (Xfoil 15 ) for better drag estimation.…”

Section: Aerodynamic Analysis and Optimizationmentioning

confidence: 99%

Lightweight unmanned aerial vehicle for emergency medical service – Synthesis of the layout

Goetzendorf‐Grabowski

Tarnowski

Figat

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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The article presents the innovative unmanned aerial vehicle project for emergency medical services. Designed unmanned aerial vehicle combines vertical takeoff and landing characteristics with fast forward flight capability that are vital to perform such an emergency medical mission. The main purpose of the designed unmanned aerial vehicle is to deliver the necessary medical package to the place where access is difficult, and estimated arrival time of conventional ambulance is too long. The cost of the support of such unmanned aerial vehicle could be significantly lower than in case of medical helicopter, which is not necessary in some cases. Designed unmanned aerial vehicle can also be used for fast delivery of essential medical substances (e.g. blood). The selection of configuration was the first and crucial step of the design. After analysis of many different copter configurations, together with selected crash reports analysis, the coaxial quadcopter configuration crossed with conventional airplane was selected. All power units for VTOL capability are electric, and they are doubled for redundancy purposes, with maximum T/W ratio about 2.0. Such configuration allows to sustain a stable flight (vertical phases) in case of one motor failure. Two versions of the vehicle are designed: fully electric (power units for the forward flight and vertical takeoff and landing are electric) and mixed where forward flight unit is a small piston engine. The final layout was the result of conceptual investigation and preliminary research, MDO and trade-off analysis, where as many aspects as possible were considered. The main problem was to meet the vertical takeoff and landing capabilities, relatively long range and endurance, expected payload (3 kg) and the requirement not to exceed 25 kg of maximum take-off weight. Paper presents the design process from initial requirement to the final configuration accepted to be manufactured.

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Section: Aerodynamic Analysis and Optimizationmentioning

confidence: 99%

Lightweight unmanned aerial vehicle for emergency medical service – Synthesis of the layout

Goetzendorf‐Grabowski

Tarnowski

Figat

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…smoothness is maintained thanks to explicit definition of trailing edge curve by B-spline. The whole problem parametrization is based on previous parametrization and optimization conducted by authors (Klimczyk et al, 2017). The final model resulting from implementation of described methods is presented in Figure 4, along with conventional wing, with discrete flap.…”

Section: Parametrization Of Morphing Wingmentioning

confidence: 99%

Analysis and optimization of morphing wing aerodynamics

Klimczyk

Goraj

2019

AEAT

Self Cite

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Purpose The purpose of this paper is to present a method for analysis and optimization of morphing wing. Moreover, a numerical advantage of morphing airfoil wing, typically assessed in simplified two-dimensional analysis is found using higher fidelity methods. Design/methodology/approach Because of multi-point nature of morphing wing optimization, an approach for optimization by analysis is presented. Starting from naïve parametrization, multi-fidelity aerodynamic data are used to construct response surface model. From the model, many significant information are extracted related to parameters effect on objective; hence, design sensitivity and, ultimately, optimal solution can be found. Findings The method was tested on benchmark problem, with some easy-to-predict results. All of them were confirmed, along with additional information on morphing trailing edge wings. It was found that wing with morphing trailing edge has around 10 per cent lower drag for the same lift requirement when compared to conventional design. Practical implications It is demonstrated that providing a smooth surface on wing gives substantial improvement in multi-purpose aircrafts. Details on how this is achieved are described. The metodology and results presented in current paper can be used in further development of morphing wing. Originality/value Most of literature describing morphing airfoil design, optimization or calculations, performs only 2D analysis. Furthermore, the comparison is often based on low-fidelity aerodynamic models. This paper uses 3D, multi-fidelity aerodynamic models. The results confirm that this approach reveals information unavailable with simplified models.

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“…Starting from airliners optimization 1,2 through supersonic aircrafts 3 and ending up even with morphing structures. 4,5 Although variety of examples is very wide, only a few of design examples consider dynamic stability effects in the conceptual and preliminary design. In most cases, the designs are limited to longitudinal, or lateral stability modes 3,6,7 or to simplified configuration like flying wing.…”

Section: Introductionmentioning

confidence: 99%

Numerical multidisciplinary optimization of aircraft with flight dynamic stability constraints

Mieloszyk

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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Classical approach to conceptual and preliminary design in aerospace sciences reaches limits. To go further and achieve better, competitive results’ use of optimization methods becomes mandatory. The trend is clearly visible in professional software for simulations equipped with optimization tools, which was not standard just decade ago. Many examples of multidisciplinary optimization were shown, especially with coupled aerodynamics and structure analyses, but only few of them consider dynamic stability effects in the conceptual and preliminary design. The article shows successful example of multidisciplinary design and optimization of Vertical Takeoff and Landing aircraft, which includes coupling of aerodynamics, mass analyses and innovative approach of constraints from flight dynamic stability. Presented optimization framework revealed potential for more efficient conceptual and preliminary design with the result of known dynamic stability characteristics of the aircraft. Obtaining the dynamic stability characteristics is not common on the early stages of the design yet crucial for the aircraft flight performance.

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Robust design and optimization of UAV empennage

Cited by 12 publications

References 15 publications

Lightweight unmanned aerial vehicle for emergency medical service – Synthesis of the layout

Lightweight unmanned aerial vehicle for emergency medical service – Synthesis of the layout

Analysis and optimization of morphing wing aerodynamics

Numerical multidisciplinary optimization of aircraft with flight dynamic stability constraints

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