scholarly journals Fatigue Strength of an Aircraft Wing Panel with a Repair Patch Based on the Filled Hole at Various Values of Interference Fit

2021 ◽  
Vol 54 ◽  
pp. 150-156
Author(s):  
Vladimir Nizev ◽  
Oleg Polushkin ◽  
Sergey Kireev ◽  
Valentin Stepanov
Keyword(s):  
Fatigue Strength ◽  
Aircraft Wing ◽  
Interference Fit ◽  
Repair Patch ◽  
Wing Panel

Dynamic Response Analysis for the Solar-Powered Aircraft Composite Wing Panel with Viscoelastic Damping Layer

2011 ◽  
Vol 105-107 ◽  
pp. 491-494
Author(s):  
Tie Jun Liu ◽  
Yong Zhang ◽  
Gang Li ◽  
Feng Hui Wang
Keyword(s):  
Dynamic Response ◽  
Vibration Isolation ◽  
Viscoelastic Damping ◽  
Response Analysis ◽  
Aircraft Wing ◽  
Maximum Displacement ◽  
Displacement Response ◽  
Stiffened Structures ◽  
Solar Powered ◽  
Wing Panel

In design of solar powered aircraft wing panel, vibration properties of wing panel should be considered, especially for the peak value of dynamic response. In this research, a viscoelastic damping layer is built for vibration isolation, wing panel finite element models of stiffened and no-stiffened structures base on fiber-reinforced laminates with damping layer in the middle are built. Natural frequency and displacement response are analyzed with different thickness of damping layer and structures. Result shows natural frequencies decrease as thickness increased, and that of laminates are lower than stiffened structure. The maximum displacement response value decreased when thickness increased and that of laminates is higher than structured with stiffer. The presented work is helpful for type selection and designing of solar powered aircraft wing panel.

Dynamics-based Damage Inspection of an Aircraft Wing Panel

2004 ◽  
Vol 15 (11) ◽  
pp. 803-821 ◽  
Author(s):  
P. Frank Pai ◽  
Byeong-Seok Kim ◽  
Jaycee H. Chung
Keyword(s):  
Aircraft Wing ◽  
Wing Panel

Fatigue Strength of Small Pinned Connections Made from Alloy Steel Fv 520B

1967 ◽  
Vol 182 (1) ◽  
pp. 615-630 ◽  
Author(s):  
D. J. White
Keyword(s):  
Fatigue Strength ◽  
Alloy Steel ◽  
Design Method ◽  
Systematic Investigation ◽  
Fatigue Tests ◽  
Mean Stress ◽  
Interference Fit ◽  
Cadmium Plating ◽  
Engineering Sciences ◽  
Pinned Connections

Published work on pin-loaded lugs is reviewed, particular attention being given to photoelastically determined stress distributions and to results of fatigue tests for the purpose of identifying those factors that affect fatigue strength. Fatigue tests have been conducted on lugs of width 1 [Formula: see text] in made from alloy steel FV 520B and loaded by means of a [Formula: see text]-in diameter pin. A systematic investigation was made of pin fit for both clearance and interference and the effect of various treatments was investigated; these included cadmium plating the lug bore and pin, applying the ‘Sulfinuz’ process to the lug and overstraining the lug bore. Two conditions of mean stress were investigated, namely, pulsating or repeated tension and 15 tonf/in2 mean tension. Strength comparisons are based on the fatigue strength at 108 cycles, for the appropriate mean stress, of untreated lugs with exact-fit pins, these showing the lowest strength of all the lugs tested. It was found that clearance-fit pins and interference-fit pins were beneficial and with the larger values of clearance and interference tested the fatigue strength was almost doubled. Cadmium plating was ineffective while both Sulfinuz treated lugs and lugs with overstrained bores gave strength ratios of at least 1.6. An increase in mean stress from pulsating tension to 15 tonf/in2 mean tension, significantly reduced fatigue strength in most cases. On the basis of the present experimental results, the design method proposed for lugs with interference-fit pins in Royal Aeronautical Society Data Sheet A.05.02, amended by Engineering Sciences Data No. 67012, may sometimes prove to be unsafe and caution is warranted in interpreting the safe loads predicted.

The Estimation of Fatigue Damage in Aircraft Wing Structures

1954 ◽  
Vol 58 (522) ◽  
pp. 396-402 ◽  
Author(s):  
A. H. Chilver
Keyword(s):  
Fatigue Strength ◽  
Fatigue Damage ◽  
Design Criteria ◽  
Characteristic Form ◽  
Structural Components ◽  
Aircraft Wing ◽  
Damage Rate ◽  
Wing Structures ◽  
Damage Law ◽  
Cumulative Fatigue Damage

SummaryA simple cumulative fatigue damage law is used to estimate the endurance of a number of typical structural components when subjected to the alternating wing loads encountered by an aircraft in flight. A method is developed to study the fatigue damage in terms of infinitesimally small intervals of alternating load and the corresponding fatigue strength. Recent gust data are used in conjunction with the complete fatigue strength diagrams of 13 simple components. The fatigue damage is studied for the ranges of altitude (i) up to 12,000 ft., and (ii) above 30,000 ft. In each case it is found that the damage rate curve, which gives the intensity of fatigue damage at any gust velocity, takes a characteristic form, with a well-defined range of gust velocities giving the greatest fatigue damage. This leads to a simplification of the whole problem, and it is found, finally, that the life of the structure is governed—in so far as the cumulative law is correct—almost entirely by that gust velocity, which, when applied alone to the structure, gives an endurance of about two million cycles. The results of the survey are compared with the design criteria suggested by Walker and the lives estimated by Williams.

Aircraft wing panel buckling analysis: efficiency by approximations

1998 ◽  
Vol 68 (6) ◽  
pp. 665-676 ◽  
Author(s):  
C.B. York ◽  
F.W. Williams
Keyword(s):  
Buckling Analysis ◽  
Aircraft Wing ◽  
Wing Panel

Study on Fatigue Strength for Axle of High Speed EMU

2012 ◽  
Vol 479-481 ◽  
pp. 965-970
Author(s):  
Ping Yu Zhou ◽  
Ping Bo Wu
Keyword(s):  
Fatigue Life ◽  
Fatigue Strength ◽  
Life Prediction ◽  
High Speed ◽  
Load History ◽  
The Finite Element Method ◽  
Interference Fit ◽  
Vehicle Systems ◽  
European Standards ◽  
Set Up

In the paper, Assessment and comparison analyses of fatigue strength for different axles of CRH2, CRH3 and CRH5 EMUs are conducted by applying the European standards and Japanese standards. The wheelset models of CRH2, CRH3 and CRH5 are set up by means of the finite element method. Static and fatigue strength of the axles are analyzed as well as the influence of the interference fit between wheel and axle on the contact pressure. To get accurate simulation of the dynamic loads on axles, mathematical models of CRH2, CRH3 and CRH5 EMUs are established by using the SIMPACK software, considering the nonlinearities in the EMU vehicle systems. The simulation is carried out according to the runtime table of the EMU in Beijing-Tianjin line. Stochastic irregularities of the track are considered in the dynamic simulation and the load history acted on wheelset is obtained. Based on the NSOFT software, the fatigue life of axles is predicted by applying appropriate fatigue life prediction methods.

Dynamics-based damage inspection of an aircraft wing panel

2003 ◽  
Author(s):  
P. F. Pai ◽  
Byeong-Seok Kim ◽  
Jaycee H. Chung
Keyword(s):  
Aircraft Wing ◽  
Wing Panel
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