Vibration analysis of composite wing with geometric and material coupling

Magdy, Ahmed; Kamel, Mohamed A.; Elshafei, M. Adnan; Kassem, M. E.

doi:10.1088/1757-899x/1172/1/012003

Cited by 3 publications

(2 citation statements)

References 11 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Vibrations affect generally all the locations of the aircraft. The research in the field of vibrations is really huge in the aircraft wings applications, [7][8][9][10][11]. Flutter mechanisms ensuing from oscillatory aerodynamic condition with large deformations are actually of specific attention for assessing the dynamic wings behaviour.…”

Section: Introductionmentioning

confidence: 99%

Vibration Response Analysis of a Main Landing Gear System for High In-Flight Dynamic Loadings

Arena,

Tartaglia,

Bruno

et al. 2024

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

The prediction of aircraft vibrations is necessary for identifying possible design optimization points of each on-board system. In this context, the authors investigated the dynamic response of a Main Landing Gear (MLG) conceived for a fast helicopter when exposed to flight vibrations arisen from the engine propellers. The research activity falls within the Racer program of Clean Sky 2 framework, which aims to develop a novel high-speed rotorcraft. Relying on Airbus Helicopters operative requirements, this paper deals with the numerical procedure description of the MLG dynamic response assessment (resonance frequencies, accelerations amplitude, generalized masses) with respect to the expected in-flight vibrations levels. In particular, an equivalent combined load (sine and random spectrum) based on the normal modes and the corresponding modal mass distribution is employed for investigating the relevant effects on structural endurance. The central themes focus on the possible numerical modelling strategies and vibration loads analysis, which led safely to the qualification. This method could allow for performing sensitivity dynamic analyses in case of further design stiffness or weight changes.

show abstract

Section: Introductionmentioning

confidence: 99%

Vibration Response Analysis of a Main Landing Gear System for High In-Flight Dynamic Loadings

Arena,

Tartaglia,

Bruno

et al. 2024

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

show abstract

“…Yang et al 20 propose an analytical method based on the mode superposition and Galerkin hybrid method (MSGHM) has been proposed for vehicle-SFT-current coupling vibration, the influences of several structural parameters on the vehicle-SFT-current coupling vibration are discussed. Magdy et al 21 discusses intensively the dynamic characteristics of a cantilever composite wing with both torsion and bending coupling to represent both material and geometric coupling, a MATLAB code is developed and results are validated in comparison with published work. Such a comparison shows a good agreement between both results.…”

Section: Introductionmentioning

confidence: 99%

Vibrational coupling mechanism and experimental study of rotor system with double-disk magnetic coupler

Wang

Guo

et al. 2023

Advances in Mechanical Engineering

View full text Add to dashboard Cite

At present, the vibrational coupling mechanism of the rotor system with a double-disk magnetic coupler has not been sufficiently studied. Based on the mechanical impedance theory, the patterns of structural mass and stiffness distribution were quantitatively described, to establish the model for the vibrational coupling mechanism. Methods were proposed to determine the vibrational coupling point and to simulate the transient response to the interacting excitations, so as to analyze the potential vibrational coupling point and the dynamic response characteristics. Then, the Campbell diagram of the shared support-dual rotor system was combined with the mechanical impedance characteristics of the shared support. As a result, it was found that although the base vibration of the shared support was significantly amplified, the single-axis trajectory showed that both the output and input rotors were synchronized with the forward vortex motion, with almost no coupling between them. A double-disk magnetic coupler test bench with a rated power of 55 kW was designed to verify the experiments. The results showed that the vibration displacement occurred in a periodic variation pattern. Moreover, the maximum errors between the theoretical, simulated, and experimental values of the vibration displacement at different input speeds were less than 5%. The experiments verified the validity of the model for the vibrational coupling mechanism and the simulation of the transient response to the interacting excitation. The results of the study could be used as a basis for calculating the vibration of the rotor system with a double-disk magnetic coupler.

show abstract

Modal analysis of isotropic and composite wings with the Dynamic Transfer Matrix Method

Abdel-Rahman

Elshafei

Kamel

et al. 2022

2022 4th Novel Intelligent and Leading Emerging Sciences Conference (NILES)

View full text Add to dashboard Cite

Vibration analysis of composite wing with geometric and material coupling

Cited by 3 publications

References 11 publications

Vibration Response Analysis of a Main Landing Gear System for High In-Flight Dynamic Loadings

Vibration Response Analysis of a Main Landing Gear System for High In-Flight Dynamic Loadings

Vibrational coupling mechanism and experimental study of rotor system with double-disk magnetic coupler

Modal analysis of isotropic and composite wings with the Dynamic Transfer Matrix Method

Contact Info

Product

Resources

About