Relevant bibliographies by topics / Variable sweep wing

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Conference papers

Academic literature on the topic 'Variable sweep wing'

Author: Grafiati
Published: 4 June 2021
Last updated: 3 February 2022

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Journal articles on the topic "Variable sweep wing"

1

Xu, Lai Bin, Shu Xing Yang, and Bo Mo. "Controllability Analysis of Flexible Variable Sweep Control Wing." Advanced Materials Research 542-543 (June 2012): 873–77. http://dx.doi.org/10.4028/www.scientific.net/amr.542-543.873.

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Variable Sweep Control Wing (VSCW) was introduced to generate the rolling control moment with the sweep angle differences between the left and the right wings. Influence flexible matrixes were generated to obtain the deflection of the effective angle of attack (AOA) of the flexible swept wing. Comparison between aileron control surface and VSCW shows that VSCW can get benefit from wing flexibility, which degrades the control effectiveness of the traditional aileron. The main advantage and difference from the traditional aircraft is that VSCW has higher control effectiveness and can prevent control reversal especially at high flight speed range; and at low speed, with an AOA variation device VSCW can get similar rolling control performance compared with traditional aileron control surface.
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2

Tong, L., and H. Ji. "Multi-body dynamic modelling and flight control for an asymmetric variable sweep morphing UAV." Aeronautical Journal 118, no. 1204 (2014): 683–706. http://dx.doi.org/10.1017/s000192400000943x.

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AbstractIn this paper, the multi-body dynamic model of an asymmetric variable sweep wing morphing UAV is built based on Kane’s method. This model describes the UAV’s transient behaviour during morphing process and the dynamic characteristic of the variable sweep wings. An integrated design of trajectory tracking control via constrained backstepping method is presented then. The idea of aircraft roll control through asymmetric wing sweep angle changes rather than traditional aileron is explored and used in the fight control design. The control of variable sweep wings is designed as well based on the presented dynamic model. Command filters are used in the backstepping design procedure to accommodate magnitude, rate and bandwidth constraints on virtual states and actuator signals. Stability of the closed-loop system can be proved in the sense of Lyapunov. Simulation of tracking a desired trajectory which contains two manoeuvres demonstrates the feasibility of the proposed protocol and the morphing wing roll controller.
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Xu, Lai Bin, Shu Xing Yang, and Bo Mo. "Pitching Dynamic Response of Variable Sweep Wing Aircraft." Applied Mechanics and Materials 197 (September 2012): 159–63. http://dx.doi.org/10.4028/www.scientific.net/amm.197.159.

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The dynamic response of Variable Sweep Wing Aircraft (VSWA) with the wing sweeping is presented. The center of gravity (cg) of the aircraft, location of each wing partition , and moment of inertia alter significantly due to the wing morphing, resulting in considerably change of the dynamics of the aircraft. The extended equations of motion (EOMs) suitable for morphing wing aircraft are derived. Compared with the traditional EOMs, there are 4 additional forces and moments exhibiting in the extended EOMs due to the wing morphing. The results show that the additional forces and moments can affect the flight control considerably.
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4

An, Jiguang, Ming Yan, Wenbo Zhou, Xianghai Sun, Zhen Yan, and Chuanren Qiu. "Aircraft dynamic response to variable wing sweep geometry." Journal of Aircraft 25, no. 3 (1988): 216–21. http://dx.doi.org/10.2514/3.45580.

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5

Radhakrishnan P, Ramanan G, Chandan Gowda H R, Meghana C K, and Chaithra A N. "Aerodynamic Performance Analysis of a Variable Sweep Wing for Commercial Aircraft Applications." ACS Journal for Science and Engineering 1, no. 1 (2021): 31–37. http://dx.doi.org/10.34293/acsjse.v1i1.5.

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This study presents a detailed study on wing and its configurations and the morphing techniques for the wing. The morphing methods of the wing such as variable chord, variable span variable cambers have been studied in detail. In this study in detail about the effects of morphable sweep wing, the commercial aircraft wing has been designed and it‘s been modelled using the solid works software. To study the aerodynamic performance the wing, the wing has been analysed in ANSYS Fluent software and the results are interpreted in detail to analyze the effect of wing and its shapes. From the results it‘s been clear that at low speed (Mach=0.8) straight wing has high L/D ratio and at the sonic speed (Mach=1) sweep wing has higher L/D ratio and in Supersonic Speed (Mach=1.2) delta wing tends to have higher L/D ratio. Based on these results the wing can be morphed to the configurations to obtain a better performance in each flight regime. Based on these morphing, aircraft performance can be improved in all flight regimes.
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6

Greatwood, Colin, Antony Waldock, and Thomas Richardson. "Perched landing manoeuvres with a variable sweep wing UAV." Aerospace Science and Technology 71 (December 2017): 510–20. http://dx.doi.org/10.1016/j.ast.2017.09.034.

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7

Zong, Ning, Guang Jun Yang, and Sheng Li Lv. "Experimental Research on Aerodynamic Characteristics of Large Aspect Ratio Wing in Unfolding Process." Applied Mechanics and Materials 421 (September 2013): 56–61. http://dx.doi.org/10.4028/www.scientific.net/amm.421.56.

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For an unmanned aerial vehicle, in order to study the aerodynamic characteristics of the large aspect ratio wing during the deployment process with variable sweep angles, the scaled model was tested in the wind tunnel at different angles of attack with various sweep angles of wing. Experimental results indicate that the aerodynamic configuration satisfies the cruise design requirements, providing favorable longitudinal and lateral-directional stability. Fuselage of multi-plane combination brings beneficial effect for lift. Analysis have been made on the cases including wing flow separation which lead to the step of lift curve, and the existence of longitudinal unstable range during wing unfolding, which make the foundation for next optimum of configuration. The work described in this paper can be applied in the design of unmanned aerial vehicles, missiles and other research areas.
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8

Landfield, Joseph P., and Dario Rajkovic. "Canard/tail comparison for an advanced variable-sweep-wing fighter." Journal of Aircraft 23, no. 6 (1986): 449–54. http://dx.doi.org/10.2514/3.45328.

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9

Newman, Brett A., and Robert L. Swaim. "Classical flight dynamics of a variable forward-sweep-wing aircraft." Journal of Guidance, Control, and Dynamics 9, no. 3 (1986): 352–56. http://dx.doi.org/10.2514/3.20113.

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10

tarabi, abbas, sajjad ghasemloo, and mahmood mani. "Aerodynamic and Performance Evaluation of a Variable-Sweep Morphing Wing." Scientia Iranica 23, no. 6 (2016): 2694–703. http://dx.doi.org/10.24200/sci.2016.3978.

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Dissertations / Theses on the topic "Variable sweep wing"

1

Agenbag, Daniel Sarel. "Longitudinal handling characteristics of a tailless gull-wing aircraft." Diss., 2008. http://hdl.handle.net/2263/28011.

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A handling quality investigation was performed on the swept gull-wing configuration. The swept gull-wing configuration is tailless and has a wing with a transition in the sweep and dihedral angle. An example of this type of aircraft is the Exulans. This aircraft is currently under development at the University of Pretoria. The handling quality study was focussed on pitch axis dynamics. The Exulans is a research testbed that will be used to investigate the swept gull-wing configuration and its special controls by means of full-scale flight testing. Variable wing sweep, twisting elevons and winglets will be investigated as means of control. These control devices are configured in such a way as to have minimum impact on the performance of the aircraft. The handling qualities of the swept gull-wing configuration have to be acceptable while using these different control strategies. The study was launched to investigate whether a gull-wing configuration aircraft will have satisfactory handling qualities at CG positions associated with the most favourable aerodynamic performance. There is an aerodynamic performance gain in designing an aircraft so that the CG falls on the so-called `E-point'. The E-point is the centre of pressure for an elliptical circulation distribution. An elliptical circulation distribution is associated with the highest Oswald efficiency for an aircraft. Time domain simulation techniques and frequency domain analysis techniques were used to analyse the handling qualities of the gull-wing configuration. The C-star criterion was used to analyse handling qualities with time domain simulation data as input. Comparative time domain simulations were performed between the Exulans and other aircraft to compare handling qualities. Eigenvalue analysis was used together with the thumbprint criterion to investigate inherent gull-wing airframe dynamics. The Shomber-Gertsen and Military Specification 8785 criteria were also used for the same purpose. The Neal-Smith method was used to investigate the effect of control authority on handling qualities and the effect of a pilot. The Monnich and Dalldorff criterion was used to evaluate gust handling qualities. An analysis chart by Fremaux and Vairo was used to evaluate the tumbling susceptibility of the gull-wing configuration. The pitch handling quality investigation shows sufficient promise that the swept gull-wing configuration will have acceptable handling qualities with the CG placed at positions associated with optimised aerodynamic performance. Analysis showed that the swept gull-wing configuration is potentially prone to tumbling. With low static margins, the configuration should exhibit improved handling qualities in gusty conditions when compared to existing tailless aircraft. It is recommended that a lateral handling quality study be performed before full scale flight testing commences on the Exulans. In addition, the possibility of wingtip stall must be investigated for the case of the swept gull-wing configuration.<br>Dissertation (MEng)--University of Pretoria, 2008.<br>Mechanical and Aeronautical Engineering<br>unrestricted
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Books on the topic "Variable sweep wing"

1

Pantham, Satyaraj. Classical dynamics of variable sweep wing aircraft. Dept. of Aerospace Engineering, Indian Institute of Science, 1993.

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2

Hallissy, James B. Wind-tunnel investigation of aerodynamic characteristics and wing pressure distributions of an airplane with variable-sweep wings modified for laminar flow. Langley Research Center, 1989.

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3

Rozendaal, Rodger A. Variable Sweep Transition Flight Experiment (VSTFE): Parametric Pressure Distribution Boundary Layer Stability Study and wing glove design task. National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1988.

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4

Kehoe, M. W. Flutter clearance of the F-14 variable-sweep transition flight experiment airplane, phase I. National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1987.

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5

M, Goorjian Peter, and Ames Research Center, eds. Transonic aerodynamic and aeroelastic characteristics of a variable sweep wing. National Aeronautics and Space Administration, Ames Research Center, 1985.

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6

United States. National Aeronautics and Space Administration., ed. Study of a variable sweep wing in sub or transonic flow. National Aeronautics and Space Administration, 1987.

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7

R, Meyer Robert, and Dryden Flight Research Facility, eds. Effects of wing sweep on boundary-layer transition for a smooth F-14A wing at Mach numbers from 0.700 to 0.825. National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1990.

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8

R, Meyer Robert, and Dryden Flight Research Facility, eds. Effects of wing sweep on in-flight boundary-layer transition for a laminar flow wing at Mach numbers from 0.60 to 0.79. National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1990.

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9

Kamran, Rokhsaz, Housh Clinton S, and Langley Research Center, eds. An aerodynamic tradeoff study of the scissor wing configuration. University of Missouri-Rolla, 1990.

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10

W, Kehoe M., and Dryden Flight Research Facility, eds. Flutter clearance of the F-14A variable-sweep transition flight experiment airplane: Phase 2. National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1990.

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Conference papers on the topic "Variable sweep wing"

1

ROKHSAZ, KAMRAN, and BRUCE SELBERG. "Scissor wing - An alternative to variable sweep." In 27th Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-13.

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2

DOBBS, S. K., G. D. MILLER, and J. R. STEVENSON. "SELF-INDUCED OSCILLATION WIND TUNNEL TEST OF A VARIABLE SWEEP WING." In 26th Structures, Structural Dynamics, and Materials Conference. American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-739.

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3

Hall, Jeremiah, Kamran Mohseni, Dale Lawrence, and Philippe Geuzaine. "Investigation of Variable Wing-Sweep for Applications in Micro Air Vehicles." In Infotech@Aerospace. American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-7171.

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4

Peng, Wuyu, Zhiwei Feng, Tao Yang, and Bin Zhang. "Trajectory multiobjective optimization of hypersonic morphing aircraft based on variable sweep wing." In 2018 3rd International Conference on Control and Robotics Engineering (ICCRE). IEEE, 2018. http://dx.doi.org/10.1109/iccre.2018.8376435.

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5

Li, Daiwei, Zheng Zeng, Junjun Cao, Danfeng Chen, Baoheng Yao, and Lian Lian. "Variable-sweep Wing for Multi-modal Underwater Vehicle with Passive-controlled Accumulator." In 2018 IEEE/OES Autonomous Underwater Vehicle Workshop (AUV). IEEE, 2018. http://dx.doi.org/10.1109/auv.2018.8729775.

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6

WAGGONER, E., R. CAMPBELL, and P. PHILLIPS. "Computational wing design in support of an NLF variable sweep transition flight experiment." In 3rd Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-4074.

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7

Manchester, Zachary R., Jeffrey I. Lipton, Robert J. Wood, and Scott Kuindersma. "A Variable Forward-Sweep Wing Design for Enhanced Perching in Micro Aerial Vehicles." In 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-0011.

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8

Calogero, Joseph, Mary Frecker, Zohaib Hasnain, and James E. Hubbard. "Optimization of a Forward-Swept Compliant Mechanism." In ASME 2017 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/smasis2017-3843.

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A coupled 3 degree-of-freedom contact-aided compliant mechanism called the Forward Swept Compliant Mechanism (FSCM) is designed optimized for coupling orthogonal translational motion. The purpose of this mechanism is to allow desirable wing morphing passively in an ornithopter wing structure to improve free flight pitch agility via sweeping the wing tip forward during downstroke. This new contact-aided compliant mechanism design, based on the coupled three degree of freedom Bend-Twist-and-Sweep Compliant Mechanism, was developed to couple motion in bending to forward sweep during downstroke to destabilize the downstroke, and thereby increasing pitch agility. This is made possible due to an axial rotation of the mechanism, positioning the angled compliant joint such that the axis of deformation is skewed from the lifting direction. A multi-objective optimization problem was formulated and solved using a multi-objective genetic algorithm. The objectives of this optimization were to maximize forward sweep while minimizing bending, twist, peak stress, and mass. During the optimization, 3084 designs were simulated throughout 37 generations. The complete data set from the optimization was used to understand the relationship between each design variable and each objective, as well as in a random forest of regression trees to determine each variable’s importance to each objective. Two designs were chosen and compared for performance tradeoffs, where additional shape change is achieved at the expense of higher peak stress. The first design achieved the desired 2 degrees of forward sweep, and the second design achieved 5 degrees of forward sweep at the expense of larger bending and a higher peak stress.
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WAGGONER, E., P. PHILLIPS, J. VIKEN, and W. DAVIS. "Potential flow calculations and preliminary wing design in support of an NLF variable sweep transition flight experiment." In 23rd Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-426.

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10

Stacey, Benjamin J., and Peter Thomas. "Initial Analysis of a Novel Biomimetic Span-Wise Morphing Wing Concept." In ASME 2019 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/smasis2019-5567.

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Abstract Morphing wings and the adaptive systems they form have been developed significantly over recent decades. Increased efficiency and control performance can be achieved with their implementation, while advances in material technology, system integration and control, have allowed concepts to present a realistic alternative to fixed-wing and aft-tail aircraft. Set out in this paper is the preliminary design and development for a novel span-wise morphing concept which employs and heavily implements biomimetic design. Specifically, the skeletal structure of the bird wing by mimicking the humerus, ulna/radius, and carpometacarpus of birds of prey as they exhibit the most versatile wing shape enabling multiple manoeuvre and flight types. The concept comprises three sections corresponding to the skeletal structure, each consisting of a leading edge D-spar and an internal structural member onto which trailing edge plates are mounted. Pneumatic artificial muscle (PAM) actuators are presented as a drive for a biologically derived ‘drawing-parallels’ mechanism, through which a 75% semi-span length change and variable sweep angle, can be obtained. Analysis of initial CFD results is discussed in comparison with similar concepts in the field and a proposal for small scale wind tunnel verification put forward. While a rapid prototype is printed to confirm the viability of the concept.
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