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Fatigue resistance of aircraft propeller blades

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Strength of Materials Aims and scope

Conclusions

  1. 1.

    Distribution of the logarithms of aircraft propeller blade lives can be satisfactorily described by the normal law. The deviations which arise in calculations using this law are in the direction of increasing the safety factor.

  2. 2.

    Aircraft propeller blades and helicopter rotor spars show great variance in cyclic strength values, exceeding the variance in the results of laboratory specimen tests.

  3. 3.

    Fatigue curves for blades and spars can be described by Eqs. (2) or (4) with an exponent of two; this permits accelerated assessment of resistance to fatigue if the results of tests at one stress level are available.

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Literature Cited

  1. N. D. Efremov, M. M. Abramov, B. P. Rykovskii, and É. M. Radetskaya, in: Surface Hardening of High-Duty Materials [in Russian], Moscow (1971).

  2. I. V. Fisherov, E. I. Zmitrenya, A. I. Chizhevskii, and V. S. Golubkova, in: Surface Hardening of High-Duty Materials [in Russian], Moscow (1971).

  3. D. M. Himmelblau, Process Analysis by Statistical Methods, Wiley, New York (1970).

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  4. M. N. Stepnov and E. V. Giatsintov, Fatigue in Light Structural Alloys [in Russian], Mashinostroenie, Moscow (1970).

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  5. M. L. Mil', A. V. Nekrasov, A. S. Braverman, et al., Helicopters: Calculations and Design [in Russian], Part 2, Mashinostroenie, Moscow (1967).

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  7. W. Weibull, Fatigue Tests and Analysis of Their Results [Russian translation], Mashinostroenie, Moscow (1964).

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Authors
  1. M. N. Stepnov
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  2. A. S. Seregin
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  3. O. V. Leonova
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  4. Yu. L. Sukhorosov
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  5. E. I. Kulikov
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  6. É. V. Dunaev
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Additional information

Moscow. Translated from Problemy Prochnosti, No. 5, pp. 36–39, May, 1977.

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Stepnov, M.N., Seregin, A.S., Leonova, O.V. et al. Fatigue resistance of aircraft propeller blades. Strength Mater 9, 550–554 (1977). https://doi.org/10.1007/BF01532922

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  • DOI: https://doi.org/10.1007/BF01532922

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