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AAE450 Senior Spacecraft Design Matthew Fox Week 4: February 8th, 2007 Structures Group, Integration Group Transfer Vehicle Truss CAD Transfer Vehicle,

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Presentation on theme: "AAE450 Senior Spacecraft Design Matthew Fox Week 4: February 8th, 2007 Structures Group, Integration Group Transfer Vehicle Truss CAD Transfer Vehicle,"— Presentation transcript:

1 AAE450 Senior Spacecraft Design Matthew Fox Week 4: February 8th, 2007 Structures Group, Integration Group Transfer Vehicle Truss CAD Transfer Vehicle, Mars Crawler, Construction Crane, Ares V, ISPP Matthew Fox (1)

2 AAE450 Senior Spacecraft Design Truss Design Thin-walled Cylinder Design requirements included: Global Buckling Local Buckling 7g Launch Load for 20 m section Micrometeorite Impact. 120 mt Load (Crew TV) Safety Factor of 2 for wall thickness Added 20% mass to joints Local Buckling was to be the constraint Matthew Fox (2)

3 AAE450 Senior Spacecraft Design TV Truss Results Acceleration (g's)0.512 Length (m) 757.0617.7135.96 10018.7942.7586.8 12539.1775.27127.66 15071.86107.85170.04 Results in Mass (mt) Enclosed Volume: 495 m^3 Results are determinate of: Acceleration Length Matthew Fox (3) Material: Al 2090

4 AAE450 Senior Spacecraft Design Backup Slides Matthew Fox (4)

5 AAE450 Senior Spacecraft Design Buckling Equation and Forces Buckling Equation k=4, assume worst boundary condition 7g Launch Load (20m section) =truss mass*7g Global Buckling, buckling over length of Truss Local Buckling, buckling of segments between supports Matthew Fox (5)

6 AAE450 Senior Spacecraft Design Design Parameter Results Acceleration (g's)0.512 Length (m) 750.350.180.36 1000.350.270.28 1250.390.120.13 1500.360.110.13 t=thickness of wall R=radius of cylinder Outer Radius (m) Acceleration (g's)0.512 Length (m) 750.0020.010 1000.0040.0120.024 1250.0060.0460.088 1500.0100.0720.120 Wall Thickness (m) Matthew Fox (6)

7 AAE450 Senior Spacecraft Design Micrometeorite Impact Thickness Required where, C=41.5+/-14.0 m= mass of meteor v=velocity of meteor at impact S=particle spacing Current data and predictions state, thickness required for International Space Station (ISS) was 0.31 cm in 1995 and 1.8 cm in 2010. Note: ISS is in LEO and is subject to space debris, which increases yearly. Our mission does not have extended time in LEO, therefore 1.8 cm can be considered as a preliminary constraint. Matthew Fox (7)

8 AAE450 Senior Spacecraft Design References www.matweb.com Project Legend, Purdue University Spring 2005. Annarella, Cyril. Spacecraft Structures. Matthew Fox (8)

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