Abstract

HondaJet utilizes an all-composite fuselage. The main feature of this fuselage structure is that the stiffened panel and the sandwich panel are co-cured integrally to reduce both weight and cost. Another key feature is that a buckling tolerance design is adopted for the skin. This means that shear buckling is allowed beyond 50% limit load. Several affordable process technologies were developed in the field of lay up and structural bonding. The material and structural tests were conducted applying the concept of “Building Block Approach” to prove safety of flight. First the design allowables of the materials were decided. Environmental, damage tolerance, and fatigue conditions were considered. Three major component tests were conducted.

References

1. (1) Nakayama, H., Bennett, G.: Introduction of the MH-02 Experimental Aircraft a Joint Research Program of MSU and Honda, Proc. AIAA/FAA/MSU 3rd Joint Symposium on General Aviation Systems (1994)
2. (2) Fujino, M.: Design and Development of the HondaJet, AIAA Paper 2003-2530 (2003)
3. (3) Matsui, N., Sato, K.: Research Work of the All-composite Fuselage Structure, SME Technical Paper, TP04PUB157 (2004)
4. (4) Sato, K., Kawabe, S.: An Experimental Investigation of Shear Buckling Behavior of Curved Stiffened Panels, Proc. 27th JSCM Composite Material Symposium, p. 165-166 (2002) (in Japanese)
5. (5) Federal Aviation Administration, AC 20-107A, Composite Aircraft Structure (1984)

Author (organization or company)

• Nobuo MATSUI（Wako Research Center）
• Keiichi SATO（Wako Research Center）

Publication Information

Article of Honda R&D Technical Review Vol.16 No.2 (47 - 54)

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Citation Information