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A Numerical Approach to the Kinematic Analysis of Deployable ...
www-civ.eng.cam.ac.uk/dsl/publications/Numerical_approach.pdf20 Mar 2006: Hence substituting Equation 23. into Equation 24, one obtains. (T1T ′̄AT3TB̄T1TC̄ T3TD̄) θA. ... 23. 7 Definition of hinge angle θA. 24. 8 Deployable square frame proposed by Hedgepeth. -
NEW CONCEPTS FOR SPACECRAFT ANTENNAS AND RADAR STRUCTURESBASED ON ...
www-civ.eng.cam.ac.uk/dsl/publications/New%20concepts.pdf17 Feb 2006: A T300/LTM45 plain weave CFRP, 3-ply laminate (0/45/0) with uniform thickness wasadopted.Rmin was set at 24 mm, which provides a margin of 2.3 on material -
doi:10.1098/rspa.2005.1598
www-civ.eng.cam.ac.uk/dsl/publications/Guest%20&%20Pellegrino.pdf2 Feb 2006: 24. 35 dq. dĈ. " #C/:. ð4:3ÞTo find equilibrium configurations of the structure, we look for points where. ... K̂ Zv2Û=vq2 v2Û=vq vĈ. v2Û=vq vĈ v2Û=vĈ2. 24. 35; ð4:5Þ. is positive definite. -
Computation of Buckling Pressure of Pumpkin Balloons
www-civ.eng.cam.ac.uk/dsl/publications/AIAA-2006-1803-983.pdf11 May 2006: n 16-48 64-96 112-145Elements along tendons 100 116 134Elements at equator 30 24 20Number of elements 3460 3216 3072Number of nodes 1831 1725 1671. ... Figures 24(a) and 24(b) show this type ofplot respectively for nCA118-10-290 and nCR118-10-290 balloons -
Wrinkled membranesPart II: analytical models
www-civ.eng.cam.ac.uk/dsl/publications/jomms-v1-n1-p03-p.pdf23 Feb 2006: 12(1 ν2)π 4 A2. 4λ4. (24). The stretching strain energy per unit area can be obtained, neglecting stretchingin the η-direction, from. ... U =(1 ν)E t γ. 2. (π 2t 2. 24(1 ν2)λ2+.
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