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17 May 2005: chosen to have a stiff-ener width of 0.06R = 24 mm, load angle γ = 7, hingeangle η = 14 and a stiffener thickness of 2 materialplies. ... This results in a plan stiffener width of22.6 mm, compared to that of 24 mm in Config VI.It also worth noting that

6 Feb 2001: b = 2 (15 6) 24 = 204 (4). Substituting Equations 3 and 4 into Equation 1 we obtain. ... 1.32. 1.29. (b). 1.48 1.24 1.24. 1.52 1.52. 3.020.43 1.40 1.40.

21 Jan 2002: 0.07 -0.06 -0.05 -0.04 -0.03 -0.02 -0.01 0 0.01-24. -20.

16 Nov 1999: c) Common limit point. 24. 5 Example of system with corner limit point; in the initial configuration p = L,ϕ = 0. ... 24. 6 Equilibrium path of simple example. 24. 7 Different shapes of equilibrium path at a corner point, for c1 6= 0 and c2 6= 0; (a)c3 6

14 May 2002: Offset 6 45.9Configuration 12 12.5(A = 1 m) 24 3.3. Table 1: Typical surface errors of reflectors with D =10 m and F = 7.8 m.

15 Aug 2003: Yee, J.C.H. and Pellegrino, S. (2003b) Folding of composite structures. Conference onDeformation and Fracture of Composites (FRC-7), Sheffield University, 22-24 April2003.

13 Sep 2000: dh = r sin ΦX ΓXY (24). dv = r (1 cos ΦX ) ΓXZ (25).

17 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

9 Apr 2004: 24 and 20 into Eq. 21, and multi-plying by the arc length of the tape, Rθ. ... 24. • The steady-state moments for equal and oppositesense bending of a folded tape spring are given byEqs.

20 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.

22 May 2003: e11 =h1A2 h2A1. (h1h3 h22)|V |(23). e12 =h3A1 h2A2. (h1h3 h22)|H|(24). ... At this. 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 401.

18 Feb 2002: 20 16 4.130 24 5.340 33 5.9. best-fit line through points 5-8 is 1 : 5. ... The long slits in the Configuration B dish, whichhas β = 24 deg, leave two long unsupportedlengths of skirt.

14 May 2002: γ tot2. .   .   γ tot π kα (24).

18 May 2007: changes. Furtherinvestigation of this result is required. 2.98. 1.49. 0.00. 0.75. 2.24.

7 Jul 2004: 62 200 16.28 277. 90 273 24.8 177. - - 60.4 215. - - ... cannot be used to analyse this effect. 24. 3.2 Simulation with Pro/Mechanica.

16 Nov 1999: 24). Type 2 constraints prevent specified points Ci, at the corners of certain panels of wing 2,. ... 23. 7 Equilibrium path. 24. 8 Simulation of antenna deployment (connecting rods not shown).

28 Mar 2000: a2 b c = 0 (24). can be solved and, of the two solutions, the one closest ton1 is chosen. ... 24. 25. 26. 27. 28. 29. 30. 31. 32. 33. 3435.

6 May 2004: FOLDING OF WOVEN COMPOSITE STRUCTURES. J.C.H. Yee and S. Pellegrino1. Department of Engineering, University of CambridgeTrumpington Street, Cambridge CB2 1PZ, UK. ABSTRACT This paper investigates one-ply and two-ply laminates made from woven T300

10 Jan 2004: US Patent,. 4,942,700. July 24, 1990. [5] Hoberman C. Radial expansion/retraction truss structures. ... mization. International Journal for Numerical Methods in Engineering 1987, 24:359–. 373.

5 Apr 2007: lx ly (24). The outcome of this calculation is. . Nx.

30 Jan 2005: W = PE δwsin2θcosθ. (23). But, since. φ =π. 2 2θ (24).

21 Mar 2001: E. 266664. X1Y1::Z3. 377775 =. 24 aX bX cXaY bY cYaZ bZ cZ. ... 3.3. Prestressing Strategy 24. Tx1 = T1 tx1s1. Ty1 = ty1D1D2=2 (3.13).

2 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.