Automation of aircraft components with geometrical stress concentrators fatigue endurance calculations

Аuthors

Polonik E. N.^*, Surenskiy E. A.^**, Fedotov A. A.^***

PJSC Yakovlev , 68, Leningradskiy prospect, Moscow, 125315, Russia

*e-mail: Evgeniy.Polonik@irkut.com
**e-mail: Evgeniy.Surenskiy@irkut.com
***e-mail: Aleksandr.Fedotov02@irkut.com

Abstract

The paper contains the description of the computer program SNCalculator meant for fatigue endurance of aircraft components with geometric stress concentrators computation. SNCalculator is integrated into finite elements computation bundled software Femap. It allows significantly increase the degree of computations automation. As an initial data, the program uses material constants, stress history mask, parameters of calculation theories and mechanical stress level. Stress data is automatically loaded from Femap model after accomplishing its static analysis. Libraries allow re-use of materials and stress history mask. SNCalculator posesses post-processing features, such as results saving, export of the results to Excel spreadsheet, export of the results to Femap FEM, stress cyclogram viewer.

Fatigue endurance calculations algorithm is based on three most widely spread in aviation industry techniques: quality of design analysis (developed by Loim V.B.), similarity theory analysis (developed by Kogaev V.P.) and fatigue rating theory analysis (developed by Strigius V.E.). The first two methods employ conception of effective stress concentration coefficient. The first method implements «quality» as a parameter, which is identified by experimental data and study of analogous structures data. Effective stress concentration coefficient is calculated for the second method by Kogaev’s theory of similarity. The third method uses fatigue rating, which is defined as maximal normal stress of zero-to-tension cycle for which fatigue life is equal 10⁵ cycles with 50% probability and reliability level equal 0.5.

The paper describes the main steps of the abovementioned methods and presents schematic algorithm of fatigue life calculation realized by SNCalculator.

Keywords:

fatigue life, stress concentration, airframe, automation

References

1. Raschety i ispytaniya na prochnost’. Metody rascheta kharakteristik soprotivleniya ustalosti. GOST 25.504-82 (Strength calculation and testing. Methods of fatigue strength behavior calculation, State Standart 25.504-82), Moscow, Standarty, 1982, 55 p.

2. Kogaev V.P. Raschety na prochnost’ pri napryazheniyakh, peremennykh vo vremeni (Strength calculation for non-stationary stress), Moscow, Mashinostroenie, 1993, 364 p.

3. Loim V.B. Vestnik mashinostroeniya, 1998, no. 9, pp. 31-37.

4. Strigius V.E. Metody rascheta ustalostnoi dolgovechnosti elementov aviakonstruktsii (Methods of fatigue life calculations for aviation structures), Moscow, Mashinostroenie, 2012, 272 p.

5. Raschety i ispytaniya na prochnost. Metodi shematizatsii sluchaynikh protsessov nagrugenia elementov mashin I konstruktsiy I statisticheskogo predstavleniya rezultatov, GOST 25.101-83 (Strength calculation and testing. Representation of random loading of machine elements and structures and statistical evaluation of results, State Standart 25.101-83), Moscow, Standarty, 1983, 25 p.

6. Stebenev V.N. Trudy TSAGI, 1981, vol. 2117, pp. 42-54.

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