Numerical Method for Rapid Aerostructural Design and Optimization

Taylor, Jeffrey D.; Hunsaker, Douglas F.

doi:10.2514/6.2020-3175

Cited by 3 publications

(3 citation statements)

References 43 publications

(146 reference statements)

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“…A generic instrumentation pod weighing 500 lbf (57) is sometimes mounted at a hard point outboard of the wing root. Assuming that all of the fuel is distributed in fuel bladders that extend to 83.1% semispan (53) , the net-weight distribution can be approximated as where K is a scaling constant that depends on the length of the fuel bladder and the weight of the fuel carried in the wing. Using Equation (21) in Equation (8) gives a relationship that can be solved to find K for a fuel bladder that extends to 83.1% semispan with a given fuel weight , i.e. …”

Section: Resultsmentioning

confidence: 99%

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Low-fidelity method for rapid aerostructural optimisation and design-space exploration of planar wings

Taylor

Hunsaker

2021

Aeronaut. j.

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During early phases of wing design, analytic and low-fidelity methods are often used to identify promising design concepts. In many cases, solutions obtained using these methods provide intuition about the design space that is not easily obtained using higher-fidelity methods. This is especially true for aerostructural design. However, many analytic and low-fidelity aerostructural solutions are limited in application to wings with specific planforms and weight distributions. Here, a numerical method for minimising induced drag with structural constraints is presented that uses approximations that apply to unswept planar wings with arbitrary planforms and weight distributions. The method is applied to the National Aeronautics and Space Administration (NASA) Ikhana airframe to show how it can be used for rapid aerostructural optimisation and design-space exploration. The design space around the optimum solution is visualised, and the sensitivity of the optimum solution to changes in weight distribution, structural properties, wing loading and taper ratio is shown. The optimum lift distribution and wing-structure weight for the Ikhana airframe are shown to be in good agreement with analytic solutions. Whereas most modern high-fidelity solvers obtain solutions in a matter of hours, all of the solutions shown here can be obtained in a matter of seconds.

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Section: Resultsmentioning

confidence: 99%

“…We will also constrain spar height h and width w , as explained in Ref. (53), to ensure that the spar fits within the local aerofoil section. The optimisation problem can be summarised as follows: where the subscript 0 indicates that the parameter value is prescribed.…”

Section: Numerical Methodologymentioning

confidence: 99%

Low-fidelity method for rapid aerostructural optimisation and design-space exploration of planar wings

Taylor

Hunsaker

2021

Aeronaut. j.

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“…Beyond the classification according to winglet designs and non-planar concepts, publications in the field of induced drag reduction range from reviews (Kroo, 2001) to specific issues (Taylor & Hunsaker, 2020a, 2020bPhillips et al, 2019;Demasi, 2006). Specific issues include variational approaches (Demasi, 2006) and numerical methods for design and optimization (Taylor & Hunsaker, 2020b). Another group of publications focuses on minimizing induced drag under structural constraints (Jones, 1950;Pate & German, 2013;Phillips et al, 2019;Taylor & Hunsaker, 2020a).…”

Section: Introductionmentioning

confidence: 99%

An Alternative Approach to Induced Drag Reduction

Kehayas

2021

Aviation

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Induced drag constitutes approximately 40% of the total drag of subsonic civil transport aircraft at cruise conditions. Various types of winglets and several non-planar concepts, such as the C-wing, the joined wings, and the box plane, have been proposed for its reduction. Here, a new approach to induced drag reduction in the form of a combination of an elliptical and an astroid hypocycloid lift distribution is put forward. Lift is mainly generated from high circulation in the center part of the wing and fades away along the semi-span towards the wing tip. Using lifting line theory, the analysis shows that for fixed lift and wingspan the combined lift distribution results in an induced drag reduction of 50% with respect to the elliptical distribution. Due to its wing planform the combined lift distribution leads to a 51.5% higher aspect ratio. If structural constraints are placed, then the higher aspect ratio may affect wing weight. Although any substantial increase of wing weight is not envisaged, further study of the matter is required. Zero-lift drag and lift-dependent drag due to skin friction and viscosity-related pressure remain unaffected. The proposed lift distribution is particularly useful in a blended wing-body design.

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Characterization of the Common Research Model Wing for Low-Fidelity Aerostructural Analysis

Taylor

Hunsaker

2021

AIAA Scitech 2021 Forum

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Numerical Method for Rapid Aerostructural Design and Optimization

Cited by 3 publications

References 43 publications

Low-fidelity method for rapid aerostructural optimisation and design-space exploration of planar wings

Low-fidelity method for rapid aerostructural optimisation and design-space exploration of planar wings

An Alternative Approach to Induced Drag Reduction

Characterization of the Common Research Model Wing for Low-Fidelity Aerostructural Analysis

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