Optimal Wing and Horizontal Tail Plane Design for Maximizing the Aircraft Performance in Cruise Flight

Ferrero-Guillén, Rubén; Díez-González, Javier; Alija-Pérez, José-Manuel; Martínez-Gutiérrez, Alberto; Verde, Paula; Pérez, Hilde

doi:10.1080/01969722.2022.2030010

Cited by 6 publications

(3 citation statements)

References 25 publications

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“…3D simulation technology can also provide more graphic features, motion states, stress and strain distribution curves and boundary conditions to support dynamic modeling, dynamic testing and research. The simulation program is shown in Figure 1: On the computer, we can intuitively observe various objects and conduct virtual experiments [8]. Visual simulation technology is to use the tools of computer graphics and image processing to intuitively describe the three-dimensional physical objects.…”

Section: D Simulationmentioning

confidence: 99%

Dynamic performance analysis of aircraft chassis based on 3D simulation technology

Song

Sun²

2023

Third International Conference on Mechanical Design and Simulation (MDS 2023)

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As an important part of the aircraft, the analysis of its dynamic performance is also extremely critical. As the core component of the aircraft, the performance of the aircraft chassis plays a vital role in the overall aircraft structure and flight safety. In order to provide scientific basis for the performance evaluation and design improvement of the aircraft chassis, this paper analyzes its dynamic performance and uses 3D simulation technology to carry out experiments on it. This paper mainly uses the experimental method and the investigation method to analyze the relevant data of the aircraft case. The experimental results show that due to the damping of the system, from 2 ms to 4 ms, when the equivalent voltage oscillates, the acceleration pulse remains at 0 value, and the amplitude decreases gradually with time, showing an attenuation trend.

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Section: D Simulationmentioning

confidence: 99%

Dynamic performance analysis of aircraft chassis based on 3D simulation technology

Song

Sun²

2023

Third International Conference on Mechanical Design and Simulation (MDS 2023)

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“…and others [7][8][9][10][11] introduced longitudinal trim consideration into gradient-based optimization by deriving adjoint equations for solving zero-pitching moment constraints. Rubén [12] applied Prandtl's lifting line theory to compute the lift distribution of wings and horizontal tails, optimizing the combination using genetic algorithms to achieve optimal lift distribution while considering longitudinal trim.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Shape Optimization of Subsonic/Supersonic Flows Integrating Variable-Fidelity Longitudinal Trim Analysis

Wu,

Huang,

et al. 2024

Aerospace

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Most existing studies on aerodynamic shape optimization have not considered longitudinal trim under control surface deflection, typically achieving self-trim through a constraint of zero pitching moment or adjusting the optimized configuration for longitudinal trim. However, adjustments to the optimized configuration might introduce additional drag, reducing overall optimization benefits. In this paper, a novel approach of incorporating control surface deflection for longitudinal trim in aerodynamic optimization is proposed. Firstly, an aerodynamic computation program based on the high-order panel method was developed, introducing velocity perturbations on specific mesh surfaces to simulate actual control surface deflections. Subsequently, a comprehensive optimization framework was established, encompassing parametric modeling, aerodynamic computation, and variable-fidelity control surface deflection analysis. Finally, aerodynamic optimization analysis was conducted under both subsonic and supersonic conditions. Thirty-one design variables were selected with the trimmed lift-to-drag ratio in cruising condition as the objective function and the control surface deflection angle as the constraint. The results indicated an 8.52% increase in the trimmed lift-to-drag ratio compared to the baseline model under subsonic conditions and an 8.1% increase under supersonic conditions.

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“…The main function of the civil aircraft's horizontal tail is to ensure the longitudinal stability and pitch control of the aircraft [1] . In actual flight, the horizontal tail is subjected to aerodynamic loads caused by various factors, such as the deflection of the control surfaces, downwash of the wing-body combination, and jet exhaust from the aircraft engine [2] .…”

Section: Introductionmentioning

confidence: 99%

Anti-vibration Design of the Civil Aircraft’s Horizontal Tail Trailing Edge Compartment

Lyu,

Yu,

Chen

2023

J. Phys.: Conf. Ser.

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The horizontal tail trailing edge compartment is a vital component of civil aircraft, situated between the horizontal tail beam and elevator. Its primary function is to connect the elevator and meet the aerodynamic sealing requirements of the unflapped elevator, and to transfer the aerodynamic and inertial load of the elevator to the outboard wing box of the horizontal tail in concentrated form. Under aerodynamic or other excitation, the horizontal tail trailing edge compartment may experience vibration, increasing the risk of structural damage. This study aims to enhance the anti-vibration capability of the horizontal tail trailing edge compartment via parametric finite element analysis. This analysis examines various design elements of the horizontal tail end cabin and compares the first-order modal frequency to deduce the influence of factors on the stiffness. The results provide a reference for the anti-vibration design of the horizontal tail trailing edge compartment in civil aircraft.

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Optimal Wing and Horizontal Tail Plane Design for Maximizing the Aircraft Performance in Cruise Flight

Cited by 6 publications

References 25 publications

Dynamic performance analysis of aircraft chassis based on 3D simulation technology

Dynamic performance analysis of aircraft chassis based on 3D simulation technology

Aerodynamic Shape Optimization of Subsonic/Supersonic Flows Integrating Variable-Fidelity Longitudinal Trim Analysis

Anti-vibration Design of the Civil Aircraft’s Horizontal Tail Trailing Edge Compartment

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