General Approach to Lifting-Line Theory, Applied to Wings with Sweep

Reid, Jackson T.; Hunsaker, Douglas F.

doi:10.2514/1.c035994

Cited by 11 publications

(5 citation statements)

References 17 publications

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“…MachUpX is a Python implementation of the Goates-Hunsaker (G-H) general numerical lifting-line method, which is a modern extension of Prandtl's classical lifting-line theory [26][27][28]. Within the G-H method, the wing is replaced by a set of horseshoe vortices and Prandtl's lifting-line hypothesis is enforced at a single control point on each vortex to determine the aerodynamics of the wing.…”

Section: Numerical Lifting-line Solution (Machupx)mentioning

confidence: 99%

“…Next, we aligned and simplified each extracted wing shape (n = 1031) and connected these wings to a gull-shaped body (figure 1b). With each final wing-body configuration, we predicted the aerodynamic properties using MachUpX, a low-order numerical general lifting-line model (figure 1c) [26][27][28]. We validated the outputs from MachUpX with experimental wind tunnel measurements on 3D-printed half-span equivalent wing-body models (figure 1d).…”

Section: Introductionmentioning

confidence: 99%

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Gull-inspired joint-driven wing morphing allows adaptive longitudinal flight control

Harvey

Baliga

Goates

et al. 2021

J. R. Soc. Interface.

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Birds dynamically adapt to disparate flight behaviours and unpredictable environments by actively manipulating their skeletal joints to change their wing shape. This in-flight adaptability has inspired many unmanned aerial vehicle (UAV) wings, which predominately morph within a single geometric plane. By contrast, avian joint-driven wing morphing produces a diverse set of non-planar wing shapes. Here, we investigated if joint-driven wing morphing is desirable for UAVs by quantifying the longitudinal aerodynamic characteristics of gull-inspired wing-body configurations. We used a numerical lifting-line algorithm (MachUpX) to determine the aerodynamic loads across the range of motion of the elbow and wrist, which was validated with wind tunnel tests using three-dimensional printed wing-body models. We found that joint-driven wing morphing effectively controls lift, pitching moment and static margin, but other mechanisms are required to trim. Within the range of wing extension capability, specific paths of joint motion (trajectories) permit distinct longitudinal flight control strategies. We identified two unique trajectories that decoupled stability from lift and pitching moment generation. Further, extension along the trajectory inherent to the musculoskeletal linkage system produced the largest changes to the investigated aerodynamic properties. Collectively, our results show that gull-inspired joint-driven wing morphing allows adaptive longitudinal flight control and could promote multifunctional UAV designs.

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Section: Numerical Lifting-line Solution (Machupx)mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Gull-inspired joint-driven wing morphing allows adaptive longitudinal flight control

Harvey

Baliga

Goates

et al. 2021

J. R. Soc. Interface.

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“…Because of this, the algorithm works best for wings with aspect ratio of four or greater, where spanwise flow effects are minimal. The numerical algorithm shows good agreement with higher fidelity aerodynamic tools and experimental results [43], and has been implemented in several journal publications [10,41,[44][45][46][47][48][49]. The particular implementation of the numerical lifting-line algorithm used in this work is an open-source tool called MachUp [43,49], which allows control points to be clustered at the wing tips as well as near the aileron edges.…”

Section: Methodsmentioning

confidence: 92%

Controlling roll-yaw coupling with aileron and twist design

Brincklow,

Montgomery,

Hunsaker

2024

Aeronaut. j.

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Most simple ailerons produce adverse yaw. However, with proper aileron placement and wing twist, an aileron can produce proverse or neutral yaw, eliminating the need for aileron-rudder mixing, differential aileron deflection or Frise ailerons. The relationship between wing planform, aileron placement and lift distribution is studied here for a special class of optimal lift distributions that minimise induced drag for a variety of design constraints. It is shown that a wing employing the elliptic lift distribution will always produce adverse yaw, independent of aileron design or operating condition. However, for wings employing other optimal lift distributions, the ailerons can be placed to produce proverse or neutral yaw. A numerical lifting-line algorithm is used to explore the impact of aileron design on a wide range of wing planforms and lift distributions. Results can be used in the early stages of design to correctly place ailerons with respect to desired roll-yaw coupling.

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“…Different low-order approaches can be adopted to model nonlinear unsteady aerodynamics, such as the Unsteady Lifting Line method [19][20][21], Unsteady Vortex Lattice Method (UVLM) [22,23] or panels method. The aeroelastic framework adopted in this work opted for the use of UVLM as a compromise between accuracy and computational time.…”

Section: Fig 1 Aspect Ratio Trend For Commercial Aircraft [6]mentioning

confidence: 99%

Low-order Aeroelastic Modelling of a High Aspect Ratio Wing Aircraft Under Constrained Motion

Pontillo

Navaratna

Ascham

et al. 2022

AIAA SCITECH 2022 Forum

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The work presented in this paper describes the modelling of a low-order aeroelastic solver, built with the aim of analysing the dynamics of very flexible wing aircraft, with a focus on the coupling between the flight dynamics and the structural dynamics. The model implements a geometrically exact, low-order nonlinear beam solver based on beam shape functions coupled with Vortex Lattice Method (VLM), specifically adapted to account for large deformations. The static solution calculated by implementing the VLM was compared with the one calculated using strip theory as aerodynamic solver, showing good agreement in magnitude, but different load distribution. The aeroelastic solver was then used to analyse the dynamics of a flexible aircraft constrained to a circular trajectory with free pitch (resembling the motion on a Pendulum Rig) and on a spherical motion with free pitch and yaw (resembling the motion on the University of Bristol 5-DOF Manoeuvre Rig), for two different values of pitch stiffness and three different flexible wings (5% deflection, 10% deflection and 15% deflection with respect to the wing semispan). The results show that when the stiffness is high, it suppresses any interaction between the flight dynamics and the structural dynamics. Therefore there is no impact of the wing flexibility on the aircraft motion. On the other hand, when lowering the value of the pitch stiffness, the interaction between the wing dynamics and the pitch dynamics become evident. However, the impact of the wing flexibility was found to be always negligible on the yaw dynamics.

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General Approach to Lifting-Line Theory, Applied to Wings with Sweep

Cited by 11 publications

References 17 publications

Gull-inspired joint-driven wing morphing allows adaptive longitudinal flight control

Gull-inspired joint-driven wing morphing allows adaptive longitudinal flight control

Controlling roll-yaw coupling with aileron and twist design

Low-order Aeroelastic Modelling of a High Aspect Ratio Wing Aircraft Under Constrained Motion

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