Design of a Smart Droop Nose as Leading Edge High Lift System for Transportation Aircrafts

Monner, Hans Peter; Kintscher, Markus; Lorkowski, T.

doi:10.2514/6.2009-2128

Cited by 66 publications

(47 citation statements)

References 2 publications

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“…Figure 1b shows some representative examples, including a linear spring, a linear spring with a vertical offset, and a stiffening spring. Loads of this form would be expected for morphing aircraft concepts such as compliant leading or trailing edge camber changes, 20,21,22,23,24 elastic span extension, 25,26 warp induced variable twist, 27 and chord extension, 28 The impact of the mismatch in force profiles between actuator and load is a reduction in achievable deflection and a loss of efficiency, requiring more input energy and a larger, heavier actuator to perform a given task. Actuators convert energy input into force and displacement available.…”

Section: Actuator and Load Force Profilesmentioning

confidence: 99%

Advanced Kinematic Tailoring for Morphing Aircraft Actuation

Woods

Wereley

Friswell

2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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Morphing aircraft concepts require powerful, compact and lightweight actuation technologies in order to realize the significant changes in shape and aerodynamic properties desired. One source of inefficiency and lost performance common to all types of actuators is the mismatch between the force available versus stroke profile of the actuator and that required by the load. This work investigates a novel spiral spooling pulley mechanism that allows for kinematic tailoring of the actuator load line to better match the load required. To show the impact of kinematic tailoring on actuator efficiency, a representative case study is made of a Pneumatic Artificial Muscle driven morphing camber airfoil employing the Fish Bone Active Camber concept. Pneumatic Artificial Muscles have a decreasing force available with displacement, which is the opposite behavior of the system being driven since the aerodynamic and structural loads on the active camber mechanism increase with deflection. This results in inefficient usage of the energy in the actuator, and reduced system performance. By using an advanced spiral pulley kinematic mechanism, the actuator force profile is successfully tailored to match that required, with an additional torque margin added to account for any unmodeled effects. Genetic algorithm optimization is used to select the geometric parameters of the spiral pulley that maximize energy efficiency of the actuator while ensuring it is able to produce the required torque levels. The performance of the optimized spiral pulley is compared to a baseline case employing an optimized circular pulley which does not alter the shape of the actuator force profile to show the performance improvement provided by the kinematic tailoring.

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Section: Actuator and Load Force Profilesmentioning

confidence: 99%

Advanced Kinematic Tailoring for Morphing Aircraft Actuation

Woods

Wereley

Friswell

2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…Wing level Maute and Reich 21 Material-based topology optimization 12.3 2.1 Simulation Vasista et al 29 Load-path topology optimization method 10.1 À6.8 /þ8.0 Wing level Smart Droop Nose 26 Traditional rigid-body mechanisms 20 -Wing level DARPA 51 Eccentuator and piezomotor-based actuation -+20…”

Section: Aerodynamic Analysis Of Leading-edge Deflectionmentioning

confidence: 99%

Design of compliant mechanism-based variable camber morphing wing with nonlinear large deformation

Zhang

et al. 2019

International Journal of Advanced Robotic Systems

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The morphing wing with large deformation can benefit its flight performance a lot in different conditions. In this study, a variable camber morphing wing with compliant leading and trailing edges is designed by large-displacement compliant mechanisms. The compliant mechanisms are carried out by a hyperelastic structure topology optimization, based on a nonlinear meshless method. A laminated leading-edge skin is designed to fit the curvature changing phenomenon of the leading edge during deformation. A morphing wing demonstrator was manufactured to testify its deformation capability. Comparing to other variable camber morphing wings, the proposal can realize larger deflection of leading and trailing edges. The designed morphing wing shows great improvement in aerodynamic performance and enough strength to resist aerodynamic and structural loadings.

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“…However, the ability to modify the airfoil shape is still one of the promising technology, due to its potential capability to optimize selected aircraft performance index during the mission, like for example fuel burning. Of special interest are the concepts focused on variable camber leading edge [10,11], trailing edge [12,13] and full profile [14,15]. Nevertheless, the design of this kind of devices does not represent an easy task and would require the availability of ad-hoc developed procedures able to tackle the conflicting requirements such as the high deformability requested to change the airfoil shape coupled to the load carrying capability and low weight.…”

Section: Design Manufacturing and Wind Tunnel Test Of A Morphing Winmentioning

confidence: 99%

Design, Manufacturing and Wind Tunnel Validation of a Morphing Compliant Wing

Gaspari

Riccobene

Ricci

2018

Journal of Aircraft

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The paper describes the activities performed at Politecnico di Milano in the framework of FP7-NOVEMOR Project aiming at the design, manufacturing and wind tunnel test of a wing model equipped with morphing leading and trailing edges based on compliant structures. Starting from the Reference Aircraft, i.e. a typical regional aircraft developed during NOVEMOR project, a small scale wind tunnel model has been derived to validate the proposed morphing concept and to correlate the numerical models in an experimental environment. A special attention has been devoted to the selection of the manufacturing technology due to the difficulty in realizing compliant structures with enough accuracy at a small scale level. After a short reminder of the tools developed for the design of variable camber morphing wings, the paper describes in details the design and manufacturing phases together with the functionality and wind tunnel tests.The results were used to validate the procedure adopted for the synthesis of the compliant structures and to evaluate the aerodynamic performances of the morphing wing. Nomenclature a = vector of CST extra-coefficients α = angle of attack [deg] α e = "effective" angle of attack [deg] c = airfoil chord [m] C d = drag coefficient for unit span C l = lift coefficient for unit span C m = pitch moment coefficient for unit span ∆κ = curvature difference function between the initial and the deformed shape [1/m] ∆L = length difference function between the initial and the deformed shape [m] δ LE = leading edge equivalent deflection [deg] δ T E = trailing edge equivalent deflection [deg] ψ = non-dimensional airfoil chordwise coordinate T p = CST-Vandermonde matrix of order p σ axial = axial stress due to the skin length variation [Pa]σ bend = bending stress due to the skin curvature variation [Pa]

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Design of a Smart Droop Nose as Leading Edge High Lift System for Transportation Aircrafts

Cited by 66 publications

References 2 publications

Advanced Kinematic Tailoring for Morphing Aircraft Actuation

Advanced Kinematic Tailoring for Morphing Aircraft Actuation

Design of compliant mechanism-based variable camber morphing wing with nonlinear large deformation

Design, Manufacturing and Wind Tunnel Validation of a Morphing Compliant Wing

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