Hi,
Corrosion has a significant effect on the fatigue of metals. I cannot simulate it directly in the fatigue analysis software, but I am able to modify the surface roughness of the material. How much does surface roughness typically increase after corrosion (as a percentage)?
Ideally, I...
Subsonic Flight: Fatigue is primarily dominated by high-cycle fatigue (HCF) due to repetitive low-stress loading. The absence of extreme thermal fluctuations reduces the impact of thermal fatigue, leading to a longer material lifespan.
Supersonic Flight: More severe low-cycle fatigue (LCF)...
There is a bushing between the pin and the part. I am loading the part up and down. Therefore, I expect stresses to occur in the hole area of the part, but I am not sure which contact type I should give between the bushing and the part in Ansys. I think that if I give Bonded, it will not reflect...
Hi,
I will need to determine a fatigue spectrum based on known or conservatively estimated load exceedances for the aircraft and its flight missions.
Taxi - Climbing - Cruise - Maneuver - Descent - Taxi
After the CFD results, I can know the limit and ultimate load of aircraft. I can calculate...
Hi,
I would like to validate the fatigue analysis program I am using with the attached example. The results for crack-free specimens are quite consistent and reliable.
However, for analyses involving a 2.5 mm crack, despite reading many articles, I am unsure about the approach I should...
Hi,
There is 4 blades engine which has 180 rad/s. I have to calculate the f0,f1,f2,f3 and f4 values.
For 15 Hz ---> 0.01 g^2/Hz
Blade has 180 rad/s = 28.65*4 Hz = f0
L0 = 0.6 g^2/Hz
S0 in this formula is equal to 3.70
What does -3dB mean?
Actually, I want to understand that f1 is not lower...
Hi,
We produced two wings, one made of Al7075-T6 and the other made of composite. We want to do fatigue test of these wings, however we do not to know procedure. We know the loads applied for climbing, cruising and descending. For example, between 0-1g load in climbing, between 1-2g load in...
Hi
I have written about fatigue here many times. I found a source that I thought might be helpful, and I have a question.
To find the stresses in each spectrum (taxi, cruise), should I consider the fuel mass used by the aircraft in that spectrum? For example, should I include the fuel mass...
Structural components for which the damage tolerance method is shown to be impractical must be shown by component fatigue tests, or analysis supported by tests, to be able to withstand the repeated loads of variable magnitude expected in service. Sufficient component, subcomponent, element, or...
A fail safe strength investigation in which it is shown by analysis, tests, or both, that catastrophic failure of the structure is not probable after fatigue failure, or obvious partial failure, of a principal structural element, and that the remaining structure is able to withstand a static...
Hi,
Firstly, I am grateful to those who answered my question here, I improved myself thanks to you.
We did a fatigue test of aircraft wing basically and the result was obtained as 200000 cycles. How can I say that the wing's life is ...hours? Is there any method?
Hi,
I want to perform fatigue analysis to see the notch effect. I drew a notch on a metal part I did the static analysis, but there is much stress due to the singularity. How can I prevent this?
I will do the fatigue analysis in nCode.
I have created a new thread about the fatigue test, however I recognised öne thing. Normally, I use nz load for metal part which iş connected to wing, because nz is more critic than the others (X and Y). Must I put X and Y conditons?
I use nCode DesignLife, is there any example for 3 load...
Hi,
Is it possible to do fatigue analysis of composite structure (winglet, wing, fuselage etc.)? There is no any article for that. nCode provides just fiber composite, but not appropriate for other composites.
Hi,
I want to conduct a fatigue test on an aircraft wing. I have performed a fatigue analysis with random loads applied to the wing. Additionally, the loads on the wing have a maximum of 1.2g in the positive direction and 0.4g in the negative direction. How should I determine the loads for the...
