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Abstract
There is wide application of composite materials in commercial transport fuselage structure. With extensive usage of composite material systems there is requirement for incorporation of maintainability and repairability requirements of composite primary structure into the design. Such issues need to be addressed to meet regulatory requirements and ensure that life-cycle costs are competitive with current metallic structure. Development of Structural Repair Manual (SRM) needs to account for maintenance issues early in the design cycle and provide multiple repair options. Furthermore, proposed repair solution must have tradeoff between ease of installation, damage resistance/tolerance (repair frequency), and inspection burdens. To support SRM development analysis methods are developed to assess structural strength, repair life, residual strength in the presence of damage, and to evaluate repair design concepts. This paper summarizes the experiences in development of repair options for composite fuselage components due to complexities of material system and additional analysis requirements.
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References
- Flynn, B.W. et al., "Advanced Technology Composite Fuselage - Repair and Damage Assessment Supporting Maintenance", NASA CR-4733, 1997, NASA Langley Research Center, Hampton, VA 23665-5225.
- Justin Hale., "Boeing 787 from the Ground Up", QTR_04, 06, Boeing.com/commercial/ Aero magazine.
- Michael Niu., "Airframe Stress Analysis and Sizing", ISBN 962-7128-08-2.
- Alexander Rutman., Chris Boshers., John Parady and Larry Pearce., "Fastener Modeling for Joining Composite Parts", 2009 Americas Virtual Product Development Conference, April 21-22, 2009, Phoenix, AZ.
- Naik, R.A. and Crews, J.H.Jr., "Stress Analysis Method for Clearance-Fit Joints With Bearing-By-pass Loads", NASA TM-100551, 1989, NASA Langley Research Center, Hampton, VA 23665-5225.
- Bannantine, J.A., Comer, J.J. and Handrock, J.L., "Fundamentals of Metal Fatigue", Prentice Hall, New Jersey, 1989.
- NASA TM-X-73305, "Astronautic Structures Manual", Vol.1-3, NASA MSFC, August 1975.
- John M Barsom and Stanley T. Rolfe., "Fracture and Fatigue Control in Structures", Prentice-Hall, New Jersey.
- Federal Aviation Regulation - Section 25.571, "Damage Tolerance and Fatigue Evaluation of Structure", April 1998.
References
Flynn, B.W. et al., "Advanced Technology Composite Fuselage - Repair and Damage Assessment Supporting Maintenance", NASA CR-4733, 1997, NASA Langley Research Center, Hampton, VA 23665-5225.
Justin Hale., "Boeing 787 from the Ground Up", QTR_04, 06, Boeing.com/commercial/ Aero magazine.
Michael Niu., "Airframe Stress Analysis and Sizing", ISBN 962-7128-08-2.
Alexander Rutman., Chris Boshers., John Parady and Larry Pearce., "Fastener Modeling for Joining Composite Parts", 2009 Americas Virtual Product Development Conference, April 21-22, 2009, Phoenix, AZ.
Naik, R.A. and Crews, J.H.Jr., "Stress Analysis Method for Clearance-Fit Joints With Bearing-By-pass Loads", NASA TM-100551, 1989, NASA Langley Research Center, Hampton, VA 23665-5225.
Bannantine, J.A., Comer, J.J. and Handrock, J.L., "Fundamentals of Metal Fatigue", Prentice Hall, New Jersey, 1989.
NASA TM-X-73305, "Astronautic Structures Manual", Vol.1-3, NASA MSFC, August 1975.
John M Barsom and Stanley T. Rolfe., "Fracture and Fatigue Control in Structures", Prentice-Hall, New Jersey.
Federal Aviation Regulation - Section 25.571, "Damage Tolerance and Fatigue Evaluation of Structure", April 1998.