Planform, aero-structural, and flight control optimization for tailless morphing aircraft

The Variable Forward-Swept Wing (VFSW) Tailless configuration UAV can well satisfy multipurpose demands. However, this kind of unconventional morphing aircraft lacks tail, which brings great challenge to stability analysis. The connatural aero-elasticity divergence and the strong aerodynamic coupling as well as many uncertain factors in mechanical environment, give the VFSW Tailless configuration UAV complicated dynamic characteristics. During the process of transformation, the variation of dynamic shape will inevitably lead to the variation about aerodynamic center and barycentre positions of airplane, then make the angle of attack static stability margin variable, and directly influence stability of aircraft. On the basis of introduction of the VFSW Tailless configuration UAV, according to its geometric shape, positions of aerodynamic center and barycentre, in different states with different forward-swept angle, were calculated, so as to obtain variation curve of longitudinal static stability margin, which provided preferences for dynamics analysis, position of barycentre adjustment and design of flight control system (FCS).

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Polynomial Chaos-Based Flight Control Optimization with Guaranteed Probabilistic Performance

IFAC-PapersOnLine ◽

10.1016/j.ifacol.2020.12.565 ◽

2020 ◽

Vol 53 (2) ◽

pp. 7274-7279

Author(s):

Dalong Shi ◽

Xiang Fang ◽

Florian Holzapfel

Keyword(s):

Flight Control ◽

Polynomial Chaos ◽

Control Optimization

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Adaptive Wing Morphing Strategy and Flight Control Method of a Morphing Aircraft Based on Reinforcement Learning

Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University ◽

10.1051/jnwpu/20193740656 ◽

2019 ◽

Vol 37 (4) ◽

pp. 656-663

Author(s):

Binbin Yan ◽

Yong Li ◽

Pei Dai ◽

Muzeng Xing

Keyword(s):

Reinforcement Learning ◽

Flight Control ◽

Control Method ◽

Sliding Mode ◽

Normal Load ◽

Aerodynamic Characteristics ◽

Morphing Aircraft ◽

Adaptive Wing ◽

Aerodynamic Parameters ◽

Wing Morphing

The morphing aircraft can change different wing shapes or geometries to achieve the optimal flight performance according to various mission scenarios. In this paper, DATCOM is used to calculate aerodynamic parameters based on Firebee UAV morphing aircraft with different wing configurations and analyze aerodynamic characteristics. A novel adaptive wing morphing strategy for morphing aircraft based on reinforcement learning method is proposed. This method can highly meet the demand of keeping optimal performance in multiple flight conditions, and the adaptive wing morphing strategy, three-loop normal load altitude controller and sliding mode velocity controller can together make sure stability of morphing aircraft during morphing process with good tracking performance.

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Flight Control Optimization and Wind Tunnel Validation of a Morphing Flying Wing

AIAA Scitech 2019 Forum ◽

10.2514/6.2019-0854 ◽

2019 ◽

Author(s):

Dominic Keidel ◽

Urban Fasel ◽

Giulio Molinari ◽

Paolo Ermanni

Keyword(s):

Wind Tunnel ◽

Flight Control ◽

Control Optimization

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Planform, aero-structural and flight control optimization for tailless morphing aircraft

Journal of Intelligent Material Systems and Structures ◽

10.1177/1045389x18798952 ◽

2018 ◽

Vol 29 (20) ◽

pp. 3847-3872 ◽

Cited By ~ 4

Author(s):

Giulio Molinari ◽

Andres F Arrieta ◽

Paolo Ermanni

Keyword(s):

Flight Control ◽

Multidisciplinary Optimization ◽

Discrete Control ◽

Aerodynamic Efficiency ◽

Flight Condition ◽

Control Optimization ◽

Minimum Drag ◽

Shape Adaptation ◽

Morphing Structure ◽

Tailless Aircraft

Tailless swept wing airplanes rely on variations of the spanwise lift distribution to achieve controllability in all axes. As every flight condition requires different control moments, the conventional discrete control surfaces will be practically continuously deflected, leading to drag penalties. Shape adaptation base on chordwise morphing can achieve continuous deformations of the wing profile, leading to local lift variations with minimum drag penalties. As the shape is varied continuously along the wingspan, the lift distribution can be tailored to each flight condition. Tailless aircraft appear therefore as prime candidates for morphing, as the attainable benefits are potentially significant. This work presents a methodology to determine the optimal planform, profile shape, and morphing structure for a tailless aircraft. The employed morphing concept is based on a distributed compliance structure, actuated by piezoelectric elements. The multidisciplinary optimization considers the static and dynamic aeroelastic behavior of the structure and aims to maximize the aerodynamic efficiency of the plane while guaranteeing its controllability by means of morphing. The potential of the resulting wing design is fully exploited by means of a second optimization process, which identifies the actuation configuration resulting in the highest aerodynamic efficiency for a wide variety of control moments.

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Benefits and design challenges of adaptive structures for morphing aircraft

The Aeronautical Journal ◽

10.1017/s0001924000001135 ◽

2006 ◽

Vol 110 (1105) ◽

pp. 157-162 ◽

Cited By ~ 26

Author(s):

D. Moorhouse ◽

B. Sanders ◽

M. von Spakovsky ◽

J. Butt

Keyword(s):

Flight Control ◽

Integrated Approach ◽

Rate Of Change ◽

System Level ◽

Adaptive Structures ◽

Morphing Aircraft ◽

Potential System ◽

Wing Geometry ◽

Design Integration ◽

Future Work

Abstract The purpose of this paper is to discuss the future of adaptive structures leading towards the concept of a fully morphing aircraft configuration. First, examples are shown to illustrate the potential system-level mission benefits of morphing wing geometry. The challenges of design integration are discussed along with the question of how to address the optimisation of such a system. This leads to a suggestion that non-traditional methods need to be developed. It is suggested that an integrated approach to defining the work to be done and the energy to be used is the solution. This approach is introduced and then some challenges are examined in more detail. First, concepts of mechanisation are discussed as ways to achieve optimum geometries. Then there are discussions of non-linearities that could be important. Finally, the flight control design challenge is considered in terms of the rate of change of the morphing geometry. The paper concludes with recommendations for future work.

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