Project 2
Design Objective:
Perform a Feasibility Study of the design of a longitudinal, riveted skin
splice joint joining the top and bottom halves of the fuselage
of the Boeing 747.
The splice must withstand the
pressurization hoop tension loads at 42000 ft.
Weight and aerodynamic
disturbances are important considerations.
Attempts should be made to limit the number of fasteners to be
installed during assembly.
Two concepts are to be considered:
1. lap splice
2. butt splice
Design Requirements:
Protect against:
skin bearing failure
rivet shear failure
net area shear failure
net area tension failure
stress concentration failure edge margin >= 2.0
spacing of rivets "edge" margin >= 2.0
rivet bearing failure
Fixed Constraints:
The passenger cabin pressure altitude of the Boeing 747 is 8000 ft MSL.
Rivets: 2017-T3 aluminum, 100 degree flush-head, solid, machine-countersunk
maximum allowable rivet diameter = 1/4 in. (to prevent feather edge limitations )
minimum allowable rivet diameter = 5/32 in. (to reduce fatigue Severity Factor)
Skin: 2024-T3 0.071 inch thick aluminum alloy sheet
Fuselage radius = 128 in.
Design ultimate load factor = 3.0
Project 2A Report Requirements:
Project 2A DUE: Thursday, September 14 during lab.
Grading Sheet 2A
Project 2B Report Requirements:
- Submit in the form of a memorandum to LNW the complete report
on tne project. That is, the part required in 2A (updated and/or corrected as needed) plus the remainder
of the project in the following format:
- (See "Notes" to determine content of sections below)
3. Baseline Study
3.1 Parameter List
3.2 Solution Algorithms
for criteria and inequality constraints
3.3 Feasible Solutions
show values substituted into equations,
results, and comparison of inequalities
with allowables
3.4 Discard of Non-Feasible Concepts
4. Evaluation & Decision
4.1 Evaluation
4.2 Recommendations
Project 2B DUE: Thursday, September 28 during lab.
Grading Sheet 2B
PLEASE: be brief, simple lists normally suffice.