Accession Number:

AD0781814

Title:

Advanced Metallic Structure: Cargo Fuselage Design for Improved Cost, Weight, and Integrity

Descriptive Note:

Final rept. 1 Jun 1972-1 Apr 1973

Corporate Author:

BOEING COMMERCIAL AIRPLANE CO SEATTLE WA

Personal Author(s):

• McCarty, John E.

Report Date:

1973-06-01

Pagination or Media Count:

451.0

Abstract:

The preliminary design study was conducted to identify, evaluate, and select advanced concepts for cargo aircraft fuselage structure. The goals were to reduce the structural weight, maintain the baseline fatigue life 60,000 flight-hours and 20,000 flights, and reduce the acquisition cost. All three selected fuselage shell concepts provide a reduction in both total unit cost 2 to 7 and participating weight 17 to 19. Three adhesive-bonded fuselage shell concepts are recommended for further study, development, and test evaluation. Adhesive-bonded construction was chosen as the primary assembly method to reduce structural weight because it allows a significant improvement in fatigue quality of the structure. The improved fatigue quality allowed effective utilization of the new aluminum alloys, which provide a combination of improved fracture toughness and strength. Fracture mechanics and fatigue life characteristics of new aluminum alloys were investigated in an exploratory testing program. Sensitivity studies were conducted to evaluate the impact of the application of the USAF Damage Tolerance Criteria.

Descriptors:

• *TRANSPORT AIRCRAFT
• *ALUMINUM ALLOYS
• *FUSELAGES
• RELIABILITY
• HONEYCOMB CORES
• BONDING
• LIFE CYCLES
• TOLERANCES(MECHANICS)
• FRACTURE(MECHANICS)
• STRUCTURAL PROPERTIES
• COST EFFECTIVENESS
• WEIGHT

Subject Categories:

• Transport Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE