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Cabin Design of Civil Aircraft and Its Effect on Weight and Aerodynamic Characteristics

Author: ShiShiChen
Tutor: YuXiongQing
School: Nanjing University of Aeronautics and Astronautics
Course: Aircraft design
Keywords: Aircraft design Airliner Cabin design Parametric Design CATIA secondary development Fuselage Weight Pneumatic
CLC: V223.2
Type: Master's thesis
Year: 2009
Downloads: 112
Quote: 0
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Abstract


Civil aircraft cabin design is an important part of the design. In civil aircraft cabin design process, often need to compare different cabin design, the need to draw multiple cabin layout scheme; another program changes in the cabin, there are also a lot of duplication of work and labor; and in cabin design, you also need to ensure security of the premise, give full consideration to the cabin comfort and economy. In response to these needs, this paper completed the following studies: (1) for narrow-body aircraft cabin design methods were studied. Accordance with the relevant airworthiness management requirements, were investigated narrow-body aircraft cabin design design requirements and design process. And a typical 150-class aircraft cabin design, for example, a detailed analysis of the contents of the various parts of the cabin design. (2) studied a narrow-body aircraft cabin parametric design methods. The aircraft preliminary design stage, according to some cabin section main control parameters, rapid generation cabin interior layout design and cabin cross-sectional shape of the fuselage segment model, which eliminates the designers under the program in a variety of layouts repetitive manual operations for cabin design provides a tool. And a typical 150-class aircraft cabin design, for example, details of the cabin design parametric approach. (3) application of CATIA software product engineering optimization, to achieve a cabin section fuselage profile parameter optimization. Help designers in determining the cabin and hold the main control parameters, you can quickly generate optimal cross-sectional shape of the cabin section of the fuselage. (4) the establishment of a civilian aircraft maximum take-off weight estimation model based on an analysis of the various programs cabin design parameters on the maximum takeoff weight of the aircraft, cabin comfort and discussed the relationship between the weight of the aircraft. (5) establish a civilian aircraft aerodynamic analysis model, compared to several of the aircraft cabin design machine lift-drag ratio and zero lift drag effect, gives the aerodynamic characteristics and the relationship between cabin comfort. The design and application of case analysis shows that the proposed method of parametric design cabin and cabin fuselage section profile parameter optimization method can help designers quickly identify the cabin design programs, and through the appropriate weight and aerodynamic characteristics, preferably the comfort and better economy solution. For the aircraft cabin design provides a more convenient and fast methods and tools.

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CLC: > Aviation, aerospace > Aviation > Aircraft Construction and Design > Fuselage,the cockpit > Cabin , cargo
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