Dynamic Model and Analysis of Asymmetric Telescopic Wing for Morphing Aircraft

Chen, Lili; Guo, Zheng; Wang, Wenkai

doi:10.1051/matecconf/20166501004

Cited by 3 publications

(2 citation statements)

References 7 publications

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“…In contrast, an aircraft with a small wingspan can offer higher flight speeds and better manoeuvrability (25) . The asymmetric telescopic wingspan technique can be employed for roll control instead of using conventional control surfaces (26,27) . However, the constant challenge facing designers regarding variable span morphing wing design is to overcome the weight penalty as well as its design complexity (28) .…”

Section: Design and Modelling Of The Mvstw Modelmentioning

confidence: 99%

Wing component allocation for a morphing variable span of tapered wing using finite element method and topology optimisation – application to the UAS-S4

et al. 2021

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This work presents the Topology Optimisation of the Morphing Variable Span of Tapered Wing (MVSTW) using a finite element method. This topology optimisation aims to assess the feasibility of internal wing components such as ribs, spars and other structural components. This innovative approach is proposed for the telescopic mechanism of the MVSTW, which includes the sliding of the telescopically extended wing into the fixed wing segment. The optimisation is performed using the tools within ANSYS Mechanical, which allows the solving of topology optimisation problems. This study aims to minimise overall structural compliance and maximise stiffness to enhance structural performance, and thus to meet the structural integrity requirements of the MVSTW. The study evaluates the maximum displacements, stress and strain parameters of the optimised variable span morphing wing in comparison with those of the original wing. The optimised wing analyses are conducted on four wingspan extensions, that is, 0%, 25%, 50% and 75%, of the original wingspan, and for different flight speeds to include all flight phases (17, 34, 51 and 68m/s, respectively). Topology optimisation is carried out on the solid wing built with aluminium alloy 2024-T3 to distribute the wing components within the fixed and moving segments. The results show that the fixed and moving wing segments must be designed with two spar configurations, and seven ribs with their support elements in the high-strain area. The fixed and moving wing segments’ structural weight values were reduced to 16.3 and 10.3kg from 112 to 45kg, respectively. The optimised MVSTW was tested using different mechanical parameters such as strains, displacements and von Misses stresses. The results obtained from the optimised variable span morphing wing show the optimal mechanical behaviour and the structural wing integrity needed to achieve the multi-flight missions.

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Section: Design and Modelling Of The Mvstw Modelmentioning

confidence: 99%

Wing component allocation for a morphing variable span of tapered wing using finite element method and topology optimisation – application to the UAS-S4

et al. 2021

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“…Tong and Ji [5] have established the dynamic model and explored using the idea of roll control through asymmetric sweep angle change rather than traditional aileron in the flight control design. Chen et al [6] have developed the dynamic and kinematic equations of asymmetric telescopic wing aircraft. Analysis results have shown that telescopic wings behave better roll performance in the case of a large angle of attack and lift.…”

Section: Velocity Potentialmentioning

confidence: 99%

Efficiency Change of Control Surface of a Biomimetic Wing Morphing UAV

Song

Pei

et al. 2020

IEEE Access

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Variation modes of avian wings offer large-scale morphing aircraft an effective approach for solving problems such as the mass center shift in longitudinal trim and control system design during the morphing process. In this paper, a numerical method is established for fully understanding the influence of combined morphing on roll efficiency of a biomimetic wing unmanned aerial vehicle (UAV) from the perspective of aerodynamic change, system convergence time and aerodynamic energy consumption. Analysis and simulation results show that the biomimetic wing provides effective measures to improve the mission execution efficiency of UAV. System oscillation can obviously be reduced with asymmetric sweep angle change as the supervisory control surface for pure roll maneuver, and actuators require higher output power than that with the single deflection of the flexible trailing edge (Flex-TE). In addition, for aircraft design, a larger mass ratio of the inner wing is beneficial to enhance system stability. Energy consumption of wing and Flex-TE show laws of first increasing and then decreasing along the spanwise direction during the morphing process. For actuators of the Flex-TE, the output power of units 1 to 15 should higher than other spanwise units. For the sweep angle generalized control surface, the maximum value of energy consumption per unit time is located near the 20-th spanwise unit. INDEX TERMS Multi-joint wing, control efficiency, control allocation, aerodynamic energy consumption.

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