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Introduction
Published in Namrata Gangil, Arshad Noor Siddiquee, Sachin Maheshwari, Composite Fabrication on Age-Hardened Alloy using Friction Stir Processing, 2020
Namrata Gangil, Arshad Noor Siddiquee, Sachin Maheshwari
The basic structure of any aircraft consists of fuselage frame, wings, and tail assembly. The fuselage frame comprises a number of parts known as structural members as shown in Figure 1.2 (these members include components such as bulkhead, longerons, stringers, ribs, formers, and skin). Primary loads of the entire structure are supported by longerons. A longeron, in turn, is supported by other longitudinal members, called stringers. Stringers are numerous in number, smaller than longeron, and act as stiffeners. The frame, bulkhead, and formers are the vertical structural members of an airframe structure [4].
Vehicle structure and aerodynamics
Published in M.J. Nunney, Light and Heavy Vehicle Technology, 2007
These generally serve to extend the resistance to bending over the entire length of the underbody assembly. Since the longeron members which they normally comprise are integrated with the floor panel and the inswept front and rear wing valances, the supports also contribute to the torsional stiffness of the body.
Bulletproof optimisation design of helicopter cockpit subfloor
Published in International Journal of Crashworthiness, 2023
Bo Cui, Yongjie Zhang, Hao Dong, Zhiwen Li, Tao Jin, Haitao Wang
For the analysis of the subfloor, it can be seen from Table 9 that the design variables of longerons 2 and 3, longerons 1 and 4, and bulkhead 1 were relatively correlated to the ballistic performance of the subfloor. The longeron 3 was divided into two areas along with the central rib into the front and the rear areas, the added stiffener of longeron 4 was divided into three parts: upper and lower edge strips and stiffener plate, and the shores 1, 2, 3, 4 and the upper and lower two long stringers A and B attached to the side plate 2 were divided into independent parts. The breakdown of the subfloor parts was shown in Figure 26. Parametric modelling of the above areas and independent parts, as well as other non-subdivided parts, was carried out, and detailed optimisation was performed using the AMO with the optimised sizes as the initial values of the design variables.