Journal ArticleDOI
Sonic Fatigue Testing of an Advanced Composite Aileron
TLDR
In this paper, the authors describe a test program to verify the design of the composite inboard aileron for the L-1011 airplane, which is fabricated from graphite/epoxy minisandwich covers which are attached to graphite epoxy front spar and ribs, and to aluminum rear spar with fasteners.Abstract:
The sonic fatigue test program to verify the design of the composite inboard aileron for the L-1011 airplane is described. The composite aileron is fabricated from graphite/epoxy minisandwich covers which are attached to graphite/epoxy front spar and ribs, and to ma aluminum rear spar with fasteners. The program covers the development of random fatigue data by means of coupon testing and modal studies on a representative section of the composite aileron, culminating in the accelerated sonic fatigue proof test. The composite aileron sustained nonlinear panel vibration during the proof test without failure. Viscous damping coefficients as low as 0.4% were measured on the panels. The effects of moisture conditioning and elevated temperature on the random fatigue I;fe of both undamaged and impact damaged coupons were investigated. The combination of impact damage, moisture, and a 180°F temperature could reduce the random fatigue life by 50%.read more
Citations
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Review of sonic fatigue technology
TL;DR: The use of advanced composites in the 1980s generated an increased interest in development of more sophisticated theoretical models because of the possibilities for a much wider range of structural designs as discussed by the authors.
Journal ArticleDOI
An approximate solution for the spectral response of Duffing's oscillator with random input
TL;DR: In this article, an approximate method for estimating the power spectral density of the response of an oscillator when it is driven with Gaussian white noise is presented. But the method is not suitable for large non-linear systems, as the response peak in the response spectrum tends to broaden as the amplitude of the random excitation increases.
Proceedings ArticleDOI
A finite element formulation for the large deflection random response of thermally buckled beams
James Locke,Chuh Mei +1 more
TL;DR: In this article, the effects of temperature and acoustic loading are included in a theoretical finite element large deflection formulation for thin, isotropic beams, and the nature of the loads leads to the solution of two separate problems.
Journal ArticleDOI
Nonlinear multimode response of clamped rectangular plates to acoustic loading
Chuh Mei,Donald B. Paul +1 more
TL;DR: Utilisation des equations de plaques a grande deflexion de von Karman, de la methode de Galerkin and de la technique de linearisation equivalente as discussed by the authors.
Journal ArticleDOI
Effects of Large Deflection and Transverse Shear on Response of Rectangular Symmetric Composite Laminates Subjected to Acoustic Excitation
Chuh Mei,C.B. Prasad +1 more
TL;DR: In this paper, nonlinear equations of motion of symmetrically laminated anisotropic plates are derived accounting for von Karman strains, and the effects of transverse shear on large deflection vibration of laminates under random excitation are studied.
References
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Journal ArticleDOI
Stresses in Skin Panels Subjected to Random Acoustic Loading
TL;DR: In this paper, the authors present a design procedure for structures in the region of high noise levels and compare the predicted results with the experimental values, as well as apply the full theoretical treatment in design because of computational complexity.
Modal Investigation of Lightweight Aircraft Structures Using Digital Techniques
TL;DR: In this article, a digital impact response test technique was used to measure the dynamic properties of lightweight aircraft structures to include natural frequencies, mode shapes and modal damping, and two different types of structures were tested, honey-comb and skin-stiffened panels.
Design development of an advanced composite aileron
TL;DR: In this article, the design of an advanced composite inboard aileron for the L-1011 commercial transport aircraft is described. Butler et al. showed that the composite structure will be cost competitive with the metal structure it is replacing.