Buckling Analysis of Airframe Jointed Panel Under Combined Loading

The complicated relationship of the high order static indeterminate structure will lead to a lot of calculation work. The strength analysis of the structure is very difficult. In aircraft design phase, a structural simplified method should be used to model the load characteristics of the structure. In the paper, the buckling analysis of airframe jointed panel is investigated under combined loading and the effect of jointed position to buckling load is also presented. For the buckling analysis of special joined structure, one new method which is better than traditional methods is described.

REFERENCES (10)

Gerard G. and Becker H. (1957): Handbook of structural stability. Part 1 buckling of flat plates. – NACA Technical Note 3781.

Google Scholar

Timoshenko and Gere (1963): Theory of Elastic Stability. – USA: McGraw-Hill International Book Company.

Google Scholar

Megson T.H.G. (2013): Introduction to Aircraft Structural Analysis. – Butterworth-Heinemann.

Google Scholar

Huston R. and Josephs H. (2009): Practical stress analysis in engineering design. – CRC Press.

Google Scholar

Liu B., Zhang B. and Sun Q. (2011): Study on overall buckling strength of stiffened panels. – Journal of Mechanical Science and Technology for Aerospace Engineering, vol.30, No.12, pp.1977-1980.

Google Scholar

Beerhorst M. and Seibel M. (2011): Buckling behavior of an orthotropic plate strip under combined compression and shear. – Journal of Aircraft, vol.48, No.4, pp.1360-1367.

Google Scholar

Engineering Sciences Data Unit (1949): Initial buckling of flat plates under compression, bending and shear. – ESDU 02.04.05.

Google Scholar

Bruhn E.F. (1973): Analysis and Design of Flight Vehicle Structures. – USA: Jacobs Publishing, Inc..

Google Scholar

Niu C.Y. (1999): Airframe Stress Analysis and Sizing. – Hong Kong Conmilit Press Ltd..

Google Scholar

10.

Ma A.J. and Zhou C.Y. (2005): Wang X. Patran and Nastran finite element analysis professional tutorial. – Beijing: Tsinghua University Press.

For Authors

Weak Formulation Study For Thermoelastic Buckling Analysis Of Thick Laminated Cylindrical Shells

Simulating Progressive Damage of Notched Composite Laminates with Various Lamination Schemes

Indexes

Keywords index

Topics index

Authors index

We process personal data collected when visiting the website. The function of obtaining information about users and their behavior is carried out by voluntarily entered information in forms and saving cookies in end devices. Data, including cookies, are used to provide services, improve the user experience and to analyze the traffic in accordance with the Privacy policy. Data are also collected and processed by Google Analytics tool (more).

You can change cookies settings in your browser. Restricted use of cookies in the browser configuration may affect some functionalities of the website.

I agree I do not agree

eISSN:	2353-9003
ISSN:	1734-4492