Multiphysics anti-icing simulation of a CFRP composite wing structure embedded with thin etched-foil electrothermal heating films in glaze ice conditions

2021 ◽  
pp. 114441
Author(s):  
Rene Roy ◽  
Lawrence Prince Raj ◽  
Je-Hyun Jo ◽  
Min-Young Cho ◽  
Jin-Hwe Kweon ◽  
...  
Keyword(s):  
Cfrp Composite ◽  
Ice Conditions ◽  
Wing Structure ◽  
Composite Wing

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.

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.

scholarly journals Towards the Design of a Multispar Composite Wing

Computation ◽  
2020 ◽  
Vol 8 (2) ◽  
pp. 24
Author(s):  
Dimitriοs Stamatelos ◽  
George Labeas
Keyword(s):  
Stress Analysis ◽  
Large Scale ◽  
Bolted Joints ◽  
Structure Stability ◽  
Composite Component ◽  
Structure Comparison ◽  
Analysis Methodology ◽  
Design Requirements ◽  
Wing Structure ◽  
Composite Wing

In the pursuit of a lighter composite wing design, fast and effective methodologies for sizing and validating the wing members (e.g., spar, ribs, skins, etc.) are required. In the present paper, the preliminary design methodology of an airliner main composite wing, which has an innovative multispar configuration instead of the conventional two-spar design, is investigated. The investigated aircraft wing is a large-scale composite component, requiring an efficient analysis methodology; for this purpose, the initial wing sizing is mostly based on simplified Finite Element (FE) stress analysis combined to analytically formulated design criteria. The proposed methodology comprises three basic modules, namely, computational stress analysis of the wing structure, comparison of the stress–strain results to specific design allowable and a suitable resizing procedure, until all design requirements are satisfied. The design constraints include strain allowable for the entire wing structure, stability constraints for the upper skin and spar webs, as well as bearing bypass analysis of the riveted/bolted joints of the spar flanges/skins connection. A comparison between a conventional (2-spar) and an innovative 4-spar wing configuration is presented. It arises from the comparison between the conventional and the 4-spar wing arrangement, that under certain conditions the multispar configuration has significant advantages over the conventional design.

Vibration Control of the Composite Wing Model Using Piezoelectric Actuators

2010 ◽  
Vol 123-125 ◽  
pp. 1027-1030
Author(s):  
Lae Hyong Kang ◽  
Hong Il Kim ◽  
Ju Ho Lee ◽  
Jae Won Park ◽  
Jae Hung Han
Keyword(s):  
Vibration Control ◽  
Piezoelectric Actuators ◽  
Flow Speed ◽  
Flow Induced Vibration ◽  
Wing Model ◽  
Optical Motion ◽  
Structure Vibration ◽  
Wing Structure ◽  
Optical Motion Capture ◽  
Composite Wing

This paper demonstrates the feasibility of using piezoelectric actuators in controlling flow-induced vibration of a lightweight composite wing structure. Vibration characteristics of the composite wing model were predicted analytically against the air flow speed and the results were compared with experimental results from wind tunnel tests. Vibration control tests were successfully accomplished using positive position feedback (PPF) controller and the real-time operating deflection shapes of the composite wing were measured using 3D optical motion capture system.

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