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Yes, I have googled it :) Many articles do not give the fatigue test process, so I asked for your help. I can say that, they specify the block of loads, as you said 1000 flights. Our UAV flies between 1g and 1.8g. I should try to do fatigue test in this range. Shouldn't I? Thanks to hydraulic...

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...

As in the file I shared before, I am doing 5 analyses (taxi - climb - cruise etc.) for its flight profile. First, my loads will be in unit load(1g), then the fatigue analysis program will calculate these values ​​according to the flight profile and the life will be obtained. After the stress...

Do you also calculate how much life is left after each flight after giving a certain life to the aircraft? Or how accurate is it to calculate this situation after each flight?

Actually, I like learning so, I try to improve myself. Thanks to you, I have an idea for aircraft's fatigue method. The analysis program can be learned, but the theory of fatigue is the most important.

Thank you so much. I am grateful to you

Damage = (Load)^4 I understood this. The analysis program (nCode DesignLife) calculates the damage. I don't think I need to go through this formula again. The main purpose is, after each flight of my plane, there will be damage to part X. There will be damage again on the next flight. My purpose...

Normally I would do it like this; Damage after 1st flight + Damage after 2nd flight + .... If I use the method you mentioned, I must do (Damage after 1st flight)^4 + (Damage after 2nd flight)^4 + ... I understood you correctly, did not I? If it is correct, can I calculate it without analysis...

Yes, I have heard the Miner's Rule before. :) damage is proportional to load^4 (or 5th power)*number of cycles. Is the there any source for it? I did not hear this formula. Actually, I'm not talking about the test, I'm interested in the flight status of the aircraft in general

Actually, I want to learn this. For example, a flight profile of mine is exposed to the current maximum of 1.5g and has a lifespan of 100,000 hours. If the plane sees 2g 10 times, I want to calculate how many hours its lifespan decreases without analysis. Does this make sense? The user may also...

I would also like to ask, with your permission, the aircraft flies at an average of 1.2g. How much does its lifespan shorten if it sees 2.5g once, twice or 10 times? Do you have an example of this? How can I write it in Excel without analyzing it? For example, the lifespan of an aircraft flying...

That was just a sample. Thank you for your reply.

I have flight spectrum data like it. I can use it to do fatigue analysis.

Additionally, I would like to ask, is it important to determine delta g? I assume the plane is flying at an average of 1.5g. So should I perform an analysis in the range of +-0.5g?

Thank you very much. Thanks to you, I have gained more useful information.

Yes you are right even if the cruise is 99% of the flight, the damage may not be critical like other spectrum (maneuever). I gave 30 taxi conditions as an example. I just want to know, should I take the average fuel mass of all flights? If it consumes an average of 2 lt in 30 taxi conditions, I...

I have searched a lot. :) Thank you so much for reply. When I search many fligth loads, the cruise segment is much more than other. It makes up 99% of the flight. As the fuel in the wing decreases, the load on the structures will inevitably increase. In that case, instead of creating a single...

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...

I'm not doing a bird strike test on wing which is tradional wing as you said. After a structure receives damage from fatigue, I just want to see whether other structures receive damage or not.

Yes, the structure can support some level of damage. Actually my aim is this, after analyzing at ultimate load I will detect the damaged structures. Then I will remove those damaged areas and apply 75% less load to determine the strength of other structures.