A Composite Wing Structure with a Morphing Leading Edge

2010 ◽  
Author(s):  
Ryoko Morishima ◽  
Shijun Guo ◽  
Shakeel Ahmed
Keyword(s):  
Leading Edge ◽  
Wing Structure ◽  
Composite Wing

Analysis of High Velocity Impact on Composite Structures

2014 ◽  
Vol 617 ◽  
pp. 104-109 ◽  
Author(s):  
Milan Žmindák ◽  
Zoran Pelagić ◽  
Maroš Bvoc
Keyword(s):  
Carbon Fibers ◽  
Composite Structures ◽  
Impact Resistance ◽  
Leading Edge ◽  
Layered Composite ◽  
Bird Strike ◽  
Out Of Plane ◽  
The Matrix ◽  
Composite Wing ◽  
Considerable Damage

In the recent years a big focus is subjected to the response of structures subjected to out-of-plane loading such as blasts, impact, etc. not only to homogenous materials, but also to heterogeneous materials, such as composites. Such form of loading can cause considerable damage to the structure. In the case of layered composite materials the damage can have several forms, starting from damage in layers up to delamination and full damage of the construction. This paper describes the investigation of shockwave propagation in composite structures caused by impact loading. The composite consists of carbon fibers in a polymer matrix, in which the fibers are much stiffer then the matrix. Finite element simulations were carried out for a “bird” strike impact on a composite wing leading edge. Results show a good impact resistance and good damping abilities of shockwaves.

Selection of the Optimal Structural Design of a Spar Composite Wing

2021 ◽  
pp. 90-99
Author(s):  
O.V. Tatarnikov ◽  
W.A. Phyo ◽  
Lin Aung Naing
Keyword(s):  
Optimal Design ◽  
Element Analysis ◽  
Minimal Weight ◽  
Wing Structures ◽  
Optimization Parameters ◽  
Nonlinear Static ◽  
Wing Structure ◽  
Pareto Method ◽  
Selection Of ◽  
Composite Wing

This paper describes a method for optimizing the design of a spar-type composite aircraft wing structure based on multi-criterion approach. Two types of composite wing structures such as two-spar and three-spar ones were considered. The optimal design of a wing frame was determined by the Pareto method basing on three criteria: minimal weight, minimal wing deflection, maximal safety factor and minimal weight. Positions of wing frame parts, i.e. spars and ribs, were considered as optimization parameters. As a result, an optimal design of a composite spar-type wing was proposed. All the calculations necessary to select the optimal structural and design of the spar composite wing were performed using nonlinear static finite element analysis in the FEMAP with NX Nastran software package.

Thermo-structural design of a Ceramic Matrix Composite wing leading edge for a re-entry vehicle

2019 ◽  
Vol 207 ◽  
pp. 264-272 ◽  
Author(s):  
Michele Ferraiuolo ◽  
Roberto Scigliano ◽  
Aniello Riccio ◽  
Emanuele Bottone ◽  
Marco Rennella
Keyword(s):  
Matrix Composite ◽  
Structural Design ◽  
Ceramic Matrix Composite ◽  
Leading Edge ◽  
Ceramic Matrix ◽  
Composite Wing

Induced Strain Actuation for Solid-State Ornithopters: Pitch and Heave Coupling

2017 ◽  
Author(s):  
Francis Hauris ◽  
Onur Bilgen
Keyword(s):  
Finite Element ◽  
Finite Element Model ◽  
Fiber Composite ◽  
Leading Edge ◽  
Theoretical Models ◽  
Element Model ◽  
Harmonic Excitation ◽  
Edge Stiffener ◽  
Modes Of Vibration ◽  
Composite Wing

This paper investigates the heaving and pitching of a wing-like parameterized cantilevered plate with a leading edge stiffener and clamp variation when actuated with a surface-bonded piezoelectric actuator. The response is analyzed using a finite element model that is validated by comparison with known analytical solutions. The validated finite-element model is subjected to a harmonic excitation parametric analysis. The parameters varied in the model are the root clamped percentage, leading edge stiffener thickness, and the aspect ratio of the plate. The model is examined at the first two Eigen frequencies. Metrics of heaving and pitching are developed using surface fitting methods and their amplitudes and phases are reported throughout the parameter space. Emphasis is placed on the interaction and coupling of the first two modes of vibration with respect to the parameters. A piezo-composite wing prototype is fabricated and actuated harmonically with a Macro-Fiber Composite actuator while leading edge stiffener thickness and root clamped percentage is varied. The resulting experimental data is used to further validate the theoretical models.

Vibration Characteristics of Non-Metal Flight Control Structures in Extremely High Temperature Environments

2015 ◽  
Vol 724 ◽  
pp. 265-270
Author(s):  
Da Fang Wu ◽  
Ying Pu ◽  
Lan Shang ◽  
Yue Wu Wang ◽  
Jia Ling Yang
Keyword(s):  
High Temperature ◽  
Flight Control ◽  
Dynamic Performance ◽  
Thermal Vibration ◽  
Vibration Signals ◽  
Control Structures ◽  
Acceleration Sensors ◽  
Wing Structure ◽  
Dynamic Performance Analysis ◽  
Composite Wing

A self-developed extension configuration of high-temperature ceramic pole was used to transfer the vibration signals to non-high temperature zone, and the vibration signals of composite wing structure under high-temperature environment were identified by the ordinary acceleration sensors. The experimental measurement on the key vibration characteristic parameters of composite wing structure under high temperature thermal vibration environment up to 1100°C (e.g., the natural frequency, mode shape) was realized. The experimental results can provide an important basis for the dynamic performance analysis and safety design of composite wing structure under high-temperature thermal vibration conditions.

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