Vendetta Final Proposal Part 2 - Cal Poly

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15 Manufacturing Ease of manufacturing was a design criterion for the Vendetta. Part commonality will reduce the total number of separate parts that must be manufactured, thereby lowering manufacturing costs. The Vendetta is symmetrical in that both left and right wings, landing gear, horizontal and vertical stabilizers, etc. will be manufactured almost exactly the same. Furthermore, all control surfaces are symmetrical and would provide an additional improvement in manufacturing costs. The design has also taken into consideration the routing of electrical lines, hydraulic lines, etc. These systems Figure 15.1 - Routing Tunnel would be interconnected through two separate routing tunnels in the fuselage of the aircraft. This would reduce installation complexity and system redundancy and therefore reduce the amount of labor involved in the installation process. The routing tunnel is shown in Figure 15.1. Manufacturing breaks include the wings, empennage, forward, center, and aft portions of the fuselage, as well as the landing gear itself. These breaks are shown in Figure 15.2 and Foldout 1. The entire propulsion system is capable of being dropped out the bottom of the aircraft which provides for easy installation and maintenance. Figure 15.2 - Manufacturing Breaks Computer-aided manufacturing will enable more complex parts to be machined by computernumerically-controlled machining tools. Large items such as bulkheads can be machined from a single piece of metal. Inspection and maintenance panels will be placed wherever possible throughout the aircraft without compromising the low observability requirements. Furthermore, access panels will be built as structural doors able to carry through the skin loads that will be required to meet the stringent structural load limits. These access panels will ease maintenance and reduce maintenance hours required per flight hour. 78
The assembly line would allow for major components, such as the wing, fuselage, and empennage to be prefabricated at other site locations and brought in to a central assembly line as shown below in Figure 15.3. Figure 15.3 - Assembly Line 79
Page 1 and 2: well as a tip back angle which did
Page 3 and 4: Table 9.II - Final Component Weight
Page 5 and 6: the center-of-gravity location clos
Page 7 and 8: 10 Stability and Control To initial
Page 9 and 10: management system could then be use
Page 11 and 12: 40 30 20 10 0 -10 -20 -30 -40 -50 2
Page 13 and 14: flight. This would require a large
Page 15 and 16: Table 10.IV - Longitudinal and Late
Page 17 and 18: Additional components were integrat
Page 19 and 20: 11 Performance 11.1 Specific Excess
Page 21 and 22: 70,000 60,000 50,000 Altitude (ft)
Page 23 and 24: 11.3 Mission Requirements The RFP d
Page 25 and 26: 11.4 Takeoff & Landing The RFP requ
Page 27 and 28: 12 Payload Weapon internal layout w
Page 29 and 30: ange occurs due to the additional w
Page 31 and 32: 13 Cockpit Cockpit design began wit
Page 33 and 34: Due to RFP requirements the majorit
Page 35 and 36: fuelled systems offer high power to
Page 37: 14.4 Government Furnished Equipment
Page 41 and 42: is a learning curve associated with
Page 43 and 44: Table 17.I - RFP Compliance Checkli
Page 45 and 46: 20,000 0.9 581 2,164 3,231 4,407 5,
Page 47 and 48: Appendix B - Design Tools Company S
Page 49: 25. Roskam, J. Airplane Flight Dyna

Vendetta Final Proposal Part 2 - Cal Poly

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