Design and analysis of a meter-class CubeSat boom with a motor-less deployment by bi-stable tape springs

Jeon, Sungeun K.; Murphey, Thomas W.

doi:10.2514/6.2011-1731

Cited by 37 publications

(14 citation statements)

References 6 publications

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“…The effect of these residual Fig. 1 Space deployable structures using thin composite laminates: a) the triangular rollable and collapsible composite boom [19] partially rolled and the SIMPLE boom [18], b) packaged and c) partially deployed.…”

Section: Test Methodsmentioning

confidence: 99%

See 1 more Smart Citation

Large Strain Four-Point Bending of Thin Unidirectional Composites

Murphey¹,

Peterson

Grigoriev

2015

Journal of Spacecraft and Rockets

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A large deformation four-point bending fixture was used to test thin unidirectional composite laminas primarily used in strain energy deployable space structures. The tests allowed investigation of the large strain elastic constitutive behavior of two aerospace-grade intermediate modulus carbon fibers, a high modulus carbon fiber, and a structural glass fiber. Thermoset plastic coupons reinforced with these fibers and ranging in thickness from 0.1 to 0.5 mm were tested. A nonlinear empirical constitutive model was used to represent fiber axial tensile and compressive behavior and through a structural model, predict coupon flexural response and estimate constitutive model parameters. Intermediate modulus carbon fibers were found to be significantly nonlinear with modulus linearly increasing with strain. At failure, the fiber tangent modulus in tension was 2 to 3.1 times higher than in compression. The modulus of glass fibers was essentially constant. High modulus carbon fibers exhibited a more complex response with flexural stiffness initially slightly increasing followed by a moderate reduction in stiffness and finally, a sharp reduction in stiffness and failure. Nomenclature a = perpendicular distance between bearing axles of a cart, m b = coupon width, m β = initial angle from vertical of the plane defined by the cart bearing axles, rad D = coupon flexural rigidity, Nm ε = fiber or composite strain ε b = bending strain E c = composite tangent modulus in the fiber direction, Pa E f = fiber tangent modulus in the fiber direction, Pa E m = matrix Young's modulus, Pa E cC = composite tangent modulus in the fiber direction in compression, Pa E cT = composite tangent modulus in the fiber direction in tension, Pa E fC = fiber tangent modulus in the fiber direction in compression, Pa E fT = fiber tangent modulus in the fiber direction in tension, Pa ε f C = coupon surface strain at failure on compression side ε f T = coupon surface strain at failure on tension side E f fC = fiber tangent modulus at failure in the fiber direction in compression, Pa E f fT = fiber tangent modulus at failure in the fiber direction in tension, Pa E o = fiber initial tangent modulus at zero strain, Pa E 1 = composite Young's modulus in the fiber direction, Pa E 2 = composite Young's modulus in the transverse direction, Pa F = crosshead load, N γ 1 = fiber first-order nonlinear parameter γ 1C = fiber first-order nonlinear parameter in compression γ 1T = fiber first-order nonlinear parameter in tension h = vertical distance between bearing axles of a cart, m κ x = coupon curvature, 1∕m κ y = coupon transverse curvature, 1∕m κ f x = coupon curvature at failure, 1∕m M x = coupon moment per width, N M f x = coupon moment per width at failure, N M y = coupon transverse moment per width, N N c = composite normal force resultant, N∕m ν 12= composite Poisson's ratio R 2 = coefficient of determination s = coupon gage length, m σ c = composite stress, Pa σ cC = composite stress in compression, Pa σ cT = composite stress in tension, Pa t = coupon thick...

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Section: Test Methodsmentioning

confidence: 99%

“…A number of deployable space structure architectures have been or are currently under development, which employ thin composite laminates [9][10][11][12][13][14][15][16][17][18][19][20][21][22][23][24][25][26], two of which are shown in Fig. 1 [18,19].…”

mentioning

confidence: 99%

Large Strain Four-Point Bending of Thin Unidirectional Composites

Murphey¹,

Peterson

Grigoriev

2015

Journal of Spacecraft and Rockets

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“…Therefore, physical reconfigurability (rolling and unrolling) can be accomplished with a one-way linear or rotary actuator, unlike neutrally elastic mechanism (NEM) tape-springs that require two-way actuators. A deployable structure concept that utilizes bistable tape-spring elements is presented in [12] and [13] and shown in Fig. 1.…”

Section: Bistable Composite Tape-spring Materialsmentioning

confidence: 99%

CubeSat Deployable Antenna Using Bistable Composite Tape-Springs

Costantine

Tawk

Christodoulou

et al. 2012

Antennas Wirel. Propag. Lett.

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In this letter, a new conductive composite tape-spring is proposed for CubeSat deployable antennas that is constructed using a glass fiber reinforced epoxy with an embedded copper alloy conductor. The tape-spring is bistable enabling the antenna to be elastically stable in both the deployed and stowed states. A dipole antenna is designed, simulated, and tested to prove the viability of the electrical properties of this material.

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“…These thin composite laminates are desirable in the field of deployable space structures for the lack of reliance on mechanical mechanisms for structure packaging and on orbit unfolding. Variations of the laminate established by AFRL have been employed in the fabrication of structural tape springs used as flexural hinges 3,4 , in storable tubular extendible masts 5 , in the SIMPLE boom 6 and in antennas 7 . The specific tape springs studied here are integrated into a structure that will be the first space flight of a thin, flexible carbon fiber laminate structure known to the authors.…”

Section: Introductionmentioning

confidence: 99%

Large Deformation Bending of Thin Composite Tape Spring Laminates

Peterson

Murphey

2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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The bending stiffness of a thin carbon and glass fiber composite tape spring for deployable space structures was measured and compared to analytical predictions. Testing consisted of subjecting the laminate to bending in a large deformation four point bending test fixture. Bending stiffnesses in the D 11 and D 22 directions as well as failure curvatures were measured. Coupons failed in a fiber tensile mode at a bending strain of 2.2%. Modified micromechanics and classical lamination theory analysis were used to predict laminate stiffness properties. Test results were 10% less than predicted values. Nomenclature D 11= bending stiffness in the 11 direction D 22 = bending stiffness in the 22 direction U, D = coupon orientation, up or down F = force acting on the flexure fixture δ = cross head displacement M = moment (per width) κ = curvature E x = Young's modulus in the X direction E y = Young's modulus in the Y direction G xy = shear modulus in the XY direction ν xy = Poisson's Ratio in the XY direction ρ = density t = thickness

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Design and analysis of a meter-class CubeSat boom with a motor-less deployment by bi-stable tape springs

Cited by 37 publications

References 6 publications

Large Strain Four-Point Bending of Thin Unidirectional Composites

Large Strain Four-Point Bending of Thin Unidirectional Composites

CubeSat Deployable Antenna Using Bistable Composite Tape-Springs

Large Deformation Bending of Thin Composite Tape Spring Laminates

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