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Throughout the years, development of aircraft design has already accomplished several major milestones. However, as can be observed from existing aircraft models, the fuselage structure remains still, mostly like it was in 1930s. In this paper, the trend of fuselage designs introduced within last few decades is studied through patents and published...
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... comprise fuselage of plurality of shells, the skin to be added later to integral structure so as to form a complete integral unit, which basically then forms a transverse portion of the fuselage [19], [20]. Another patent granted in 2007, claimed fuselage could contain pre- manufactured integral units, where portion of main deck cross members would merge into frame section creating a cord in its circle cross-section, as shown in Figure 3 [21]. In 2009, some German inventors working for Airbus redesigned traditional fuselage frame. The new frame is to accommodate windows within in an innovative design. Traditionally windows act as stress raisers beside frames. The new design can now be seen implemented in Airbus 380 [22]. After same idea introduced by NASA report in 2000, Sergio M. O. Tavares among others, discussed in an article for Key Engineering Materials journal in 20 11, “Impact of Integral Structures in the Design for Manufacturing and airframes appears to be the inverse of what the design for manufacturing should seek”. The article then pushed t owards integral joints manufactured via welding, proposing this as a solution for “lightweight reinforced structures” [23]. over fasteners but also its advantageous effect on better aerodynamics. Especially considering it was proven in 2006 that RSW is more cost effective than riveting [24]. The whole development timeline is summarized in Figure 4 ...
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Citations
... automobile"s have to achieve [2]. Another study have investigated patents regarding the metal aircraft fuselage [3]. The latter rendered some main points: ...
The development approach of the aircraft industry is briefly explained. Analyzing innovation attempts from 1950s to present showed the introduction of the coil fuselage concept and how it developed into the integral frames and panels concept currently pursued. The novel design is then proposed to bridge the gap between impractical novel ideas and industry needs which put cost first. The new structure is to require minimum time for assembly. It is also to eliminate the need for advanced manufacturing, usually suggested by innovative ideas in the field. The new structure is based on common aluminum alloy sheets to minimize variance from the conventional semi-monocoque structure manufacturing requirements. Whereas numerical comparison with the conventional structure showed up to 15% weight savings and about 45% decrease within inquired maximum stress could be achieved. The stress reduction was suggested to be a result of the new structure's arrangement homogeneity.
