Flight test results from a supercritical mission adaptive wing with smooth variable camber

Powers, Sheryll Goecke; Webb, L. D.; Friend, E. L.; Lokos, William A.

doi:10.2514/6.1992-4101

Cited by 20 publications

(13 citation statements)

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“…The diagram shows a good correlation between the results provided by the model described by Equation (8) and the numerical simulations. For small actuator rotations, the functional relationship is practically linear.…”

Section: (7)supporting

confidence: 56%

“…Another important equation is Equation (8), which allows calculating the actuator shaft rotation (β) needed to achieve a given morphing angle (ϕ) of the rib block and hence of the entire mechanism. The Equation (8) can be easily obtained thanks to the following mathematical manipulations:…”

Section: Actuation Systemmentioning

confidence: 99%

“…NASA and USAF proposed the AFTI (Advanced Fighter Technology Integration)/F-111 program with the main purpose to integrate, on board a military aircraft, a wing camber morphing. The resulting mission-adaptive wing (MAW), described by (8) , consisted of a trailing edge and leading edge, variable camber control surfaces that could be deflected during flight to provide a near-ideal wing camber shape for any flight conditions. In (9) is presented an initial assessment of a new numerical model of a variable continuous trailing-edge flap (VCCTEF) system on a commercial transport-class fixed-wing aircraft in subsonic cruise.…”

Section: Introductionmentioning

confidence: 99%

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A linear guide-based actuation concept for a novel morphing aileron

Amendola¹,

Dimino²,

Concilio³

et al. 2019

Aeronaut. j.

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This paper deals with the actuation system design of a full-scale morphing aileron for regional aircraft. The aileron is allowed to smoothly change its geometrical configuration and perform the in-flight transition from a baseline shape to a set of optimal morphed ones pre-defined on the basis of aerodynamic requirements. The design of such innovative aileron is aimed not only at substituting the conventional aileron installed on a real aircraft but also to provide additional functionality. The aileron is free to rotate around its main hinge axis and it is also allowed to smoothly modify camber with two independent actuation systems. In such manner it can be used also during cruise with a symmetric deflection between the two half wings in order to reduce drag in off design condition. To accomplish variable aileron shape, a rigid-body mechanism was designed. The proposed aileron architecture is characterised by segmented adaptive ribs rigidly linked each other with spanwise reinforcements such as spars and stringers in a multi-box arrangement. Each rib is split into two movable plates connected by means of rotational hinges in a finger-like mechanism. The mechanism is driven by a load-bearing actuator by means of a kinematic chain opportunely tied based on the structural requirements in terms of shape to be matched and load to be withstood. The proposed device is an innovative arrangement of the quick-return mechanism composed of a beam leverage, commercial linear guides and a crank. The actuator shaft is directly inserted in the crank, which transmits the rotation to the linear guide that slide along a rail moving upward or downward the beam thus resulting in a camber variation. The entire aileron is moved by three leverages internally contained and distributed along the first two bays while the most external ribs are considered passive and their movement slaved. Two actuation layouts are analytically and numerically studied, the analytical theory is presented and validated by means of a multi-body simulation. Moreover, a linear static analysis was carried out under the hypothesis of glued contact between linear guides components simulating a jamming condition. This assumption has been formulated because it represents the most severe condition that envelop all the operative loads to which the actuation system is subjected. The analyses conducted are preliminarily aimed to verify that no failure occur under the imposed loads. In this first design loop, the vertical static force acting on the linear carriage exceeded allowable value and then a new configuration with double-sided linear guides was then investigated.

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Section: (7)supporting

confidence: 56%

Section: Actuation Systemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

A linear guide-based actuation concept for a novel morphing aileron

Amendola¹,

Dimino²,

Concilio³

et al. 2019

Aeronaut. j.

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“…Airfoil shape adaptation also constitutes the subject of many past and present large research projects. Among them, Mission Adaptive Wing (Powers et al, 1992), Active Flexible Wing (Perry et al, 1995), Adaptive Wing (Monner et al, 1998;Campanile and Sachau, 2000), and finally, the Morphing Program (Wlezien et al, 1998) should be mentioned here.…”

Section: The Adaptive Wing Problemmentioning

confidence: 99%

Initial Thoughts on Weight Penalty Effects in Shape-adaptable Systems

Campanile

2005

Journal of Intelligent Material Systems and Structures

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If a structural system has to be subjected to high loads and large geometry changes, according to the state of the art, articulated systems with discrete actuators are used, with the articulated systems consisting of stiff members connected by hinges. As an alternative, smart structures technologies can supply solutions based on the deliberate use of structural flexibility and on distributed actuation. In order to assess the advantages, which can be expected from such solutions, a thorough comparison must be made between the properties of compliant mechanisms and the conventional ones. A crucial aspect of this comparison, on which this contribution is focused, is the impact on the system's structural weight.The first part of the paper deals with the relevance of weight penalty effects in shapeadaptable systems, with a special focus on airfoil shape control. A quantitative analysis of weight penalty effects in pin-jointed articulated structures follows. The criterion on which this analysis is based allows a characterization of general validity, not restricted to a particular example, and can be applied to other mechanisms or hinge architectures, providing a sound way of assessing the lightweight potential of a given concept and allowing a consistent comparison between different design philosophies. An extension to weight penalty effects in compliant systems shows a higher degree of complexity and could not be addressed in the same detail in this study. Anyway, some peculiar aspects are discussed in the final part of the paper, which can serve as a basis for future developments in this sense. In particular, the dependence of weight penalty effects on the system's range of motion as well as on the loaddependence of the mechanism's kinematics is addressed.Even if the presented results can be of direct significance to the designer of conventional articulated mechanisms, the primary relevance of this work is to be seen in the long term. Its main target is to provide a basis for the analysis of the potential offered by the compliant mechanisms and smart materials for the realization of light shape-adaptable structures and to give an impulse to research efforts aiming at developing suitable optimization procedures as well as formulating proper design rules for such kind of systems.

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“…In the 1980s, NASA and Boeing Launched the mission adaptive wing technology research, the abolition of the traditional aircraft control surface, the use of flexible composite material skin and the digital flight control system [1]. In 2003, in order to satisfy the needs of long flight time, the United States FlexSys Inc company designed a piezoelectric ceramic structure that used as a driver to alter the camber of wing [2].…”

Section: Introductionmentioning

confidence: 99%

Structure design of an innovative adaptive variable camber wing

Zhao

Zeng

et al. 2018

MATEC Web Conf.

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In this paper, an innovative double rib sheet structure is proposed, which can replace the traditional rigid hinge joint with the surface contact. On the one hand, the variable camber wing structural design not only can improve the capacity to sustain more load but also will not increase the overall weight of the wing. On the other hand, it is a simple mechanical structure design to achieve the total wing camber change. Then the numerical simulation results show that the maximum stress at the connect of the wing rib is 88.2MPa, and the double ribs sheet engineering design meet the structural strength requirements. In addition, to make a fair comparison, the parameters of variable camber are fully referenced to the Talon Unmanned Aerial Vehicle (UAV). The results reveal that the total variable camber wing can further enhance aircraft flight efficiency by 29.4%. The design of the whole variable camber wing structure proposed in this paper has high engineering value and feasibility.

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Flight test results from a supercritical mission adaptive wing with smooth variable camber

Cited by 20 publications

References 0 publications

A linear guide-based actuation concept for a novel morphing aileron

A linear guide-based actuation concept for a novel morphing aileron

Initial Thoughts on Weight Penalty Effects in Shape-adaptable Systems

Structure design of an innovative adaptive variable camber wing

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