Flight Performance Characteristics of a Biologically-Inspired Morphing Aircraft

Abdulrahim, Mujahid

doi:10.2514/6.2005-345

Cited by 19 publications

(23 citation statements)

References 1 publication

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“…However, since the morphing mechanism is bounded to correspond with additional weight, it is crucial that we quantify the advantages of such morphing aircraft over its fixed counterparts, so that we could compare the two against each other and make an educated decision. The added efficiency of the morphing concept over a standard A-like aircraft is defined by Equation (7), while the added efficiency of the morphing concept over the standard B-like aircraft is defined by Equation (8). Note that the added efficiency is defined as a percentage of improvement in the power requirement.…”

Section: Working Points and Morphing Efficiencymentioning

confidence: 99%

“…Bourdin et al [7] presented a flying wing capable of roll control using folding winglets enabling variable winglet angle between −90 • and 90 • . Abdulrahim [8] designed an aircraft biologically inspired by birds, capable of gull-like folding of the wings. Manzo [9] and Wiggins [10] both propossed a mechanical design for a Hyper-Elliptical Cambered Span (HECS) originaly presented by Ref [11], where the half span is segmented into two hyper-elliptical sections generating a cambered span with an anhedral.…”

Section: Introductionmentioning

confidence: 99%

“…The velocity at which the power requirement is minimal is calculated for the glider configuration and accordingly, the minimum power requirement velocity of the aerobatic configuration is also computed. • Flight Scenario impact-A flight scenario is introduced into the analysis using χ and the morphing efficiency is calculated using Equations (7) and (8). In order to attain results at various wing loadings, an iteration loop is set from the drag calculation phase recalculating the efficiency at different wing loading values.…”

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confidence: 99%

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Investigation of a Morphing Wing Capable of Airfoil and Span Adjustment Using a Retractable Folding Mechanism

2019

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The presented aircraft is capable of alternating between two singular working points by folding the exterior surfaces of the wing underneath the interior surfaces. This allows for a significant change in wingspan, lift surfaces, aspect ratio and airfoil (camber and thickness). The motivation for this type of morphing is twofold: The increase in wingspan due to unfolding, results in an increased endurance of the aircraft, while the opposite process, which eliminates the camber of the airfoil and reduces the moment of inertia, is translated into improved manoeuvre capabilities. An analysis was performed to assess the additional endurance gained by the morphing capabilities, factoring in a spectrum of aircraft geometries and flight missions. It was concluded that this morphing concept can, in theory, improve the endurance up to 50% compared to the standard counterparts. The penalty due to the additional weight of the morphing mechanism was factored in, which had an adverse effect on the endurance improvement. The concept also calls for unique airfoil selection process. Selecting a proper airfoil for either working point, results in irregular airfoil geometry upon morphing. The two possibilities were subjected to analysis and wind tunnel testing.

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Section: Working Points and Morphing Efficiencymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

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Investigation of a Morphing Wing Capable of Airfoil and Span Adjustment Using a Retractable Folding Mechanism

2019

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“…This vehicle can vary the gull wing angle to alter its aerodynamic performance and twist its wing tips for roll control [74]. A recent project supported by NASA resulted in a small vehicle with 61-cm (24-in.)…”

Section: Flexible and Adaptive Wingsmentioning

confidence: 99%

Elements of Aerodynamics, Propulsion, and Design

2007

Introduction to the Design of Fixed-Wing Micro Air Vehicles Including Three Case Studies

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Nomenclature AR= aspect ratio, b 2 /S b = wing span C = rated battery capacitylift-curve slope, 1/rad C M = pitching-moment coefficient aboutc/4, M/ 1 2 ρV ∞ 2 Sc c root = wing root chord c = wing chord c s = specific fuel consumption, weight of fuel consumed per unit power per unit timē c = mean aerodynamic chord, MAC D = drag force E e = specific energy E p = specific power e = Oswald span efficiency factor G = gear reduction ratio H = motor heating h CL = nondimensional location of the center of lift, x CL /c

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“…Morphing concepts can be thought of as falling into two general groups, large planform changes for an increased envelope of efficient flight, and small changes for increased efficiency or flight control. The former typically involves large changes to the wing's span [4,5], dihedral [6,7], or sweep [8,9]. These types of morphing concepts are generally thought of as slowly morphing focusing on maintaining an optimal wing shape as the aircraft changes flight conditions or fuel is burned.…”

Section: Introductionmentioning

confidence: 99%

Design and optimization of a morphing aileron control surface using FMC actuators

2014

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A process for the design and optimization of a morphing aileron using flexible matrix composite (FMC) actuators is developed. Design requirements were based on the use of a morphing aileron with an existing medium size commercial transport aircraft limiting the planform to the existing conventional aileron. The design uses two sets of contracting FMC actuators operating independently to actuate the deformable aileron in both trailing edge up and down cases while matching coefficient of lift values of a conventional aileron. The design was optimized by developing a series of response models which were then used to understand the sensitivity to material, geometric and loading design variables while minimizing required force from the FMC actuators. Using a combination of response models and sequential quadratic programming algorithm, a design is chosen that matched the conventional ailerons performance at multiple flight conditions.

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Flight Performance Characteristics of a Biologically-Inspired Morphing Aircraft

Cited by 19 publications

References 1 publication

Investigation of a Morphing Wing Capable of Airfoil and Span Adjustment Using a Retractable Folding Mechanism

Investigation of a Morphing Wing Capable of Airfoil and Span Adjustment Using a Retractable Folding Mechanism

Elements of Aerodynamics, Propulsion, and Design

Design and optimization of a morphing aileron control surface using FMC actuators

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