Design Developments of a Non-Planar Deployable Structure

The paper presents ongoing research and development of novel concepts for deployable space structures using self-latching, flexural joints to replace mechanical hinges. The mechanics of deformation of Fiber-Reinforced-Polymers (FRP) joints for in-plane deployment mechanisms are studied. Methods for characterizing these joints via experiments and numerical simulations are proposed. A failure criterion suitable for ultra-thin, plain-weave composites is used to predict failure of the joints and achieve a successful design.

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“…Bending failure index F I 3 Coupled in-plane and bending failure index In-plane yield shear strain θ 1 , θ 2 folding angles τ y…”

Section: Nomenclaturementioning

confidence: 99%

“…Two examples are tape-spring rolamite (TSR) hinges 2 and compliant hinges. 3 TSR hinges are composed of two metal measuring tape sections and two sets of cams constrained to roll on each other. The deployment kinematics are controlled by the rolling cams and elastic latching into the deployed configuration is provided by tape springs.…”

Section: Introductionmentioning

confidence: 99%

Self-Deployable Joints for Ultra-Light Space Structures

Ferraro

Pellegrino

2018

2018 AIAA Spacecraft Structures Conference

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“…Hinges also allow for a paneling approach that is beneficial for arrays such as for sensors or solar panels [31,32]. Hinges can also be extended in 2 dimensions for self supporting reflector dishes [33]. A compromise example is the integrated, double-slot hinge.…”

Section: Introductionmentioning

confidence: 99%

Empirically Bounding of Space Booms with Tape Spring Hinges

Jennings

Black

Allen

2013

Shock and Vibration

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Self-deploying structures seek to provide a compact launch package for large, lightweight satellite booms. One self-deploying method is a foldable tape spring. This paper examines the large scale behavior of a boom attached by a tape spring hinge during mock deployments. A boom attached by tape spring to a rigid stand was released and the boom bounced up to 60° before coming to rest (as opposed to snap-through behavior). These large amplitude bounces can cause the boom to collide with sensors, other booms or arrays causing damage or preventing full deployment. Results show the first bounce of deployment is nearly bounded by a four parameter ellipse. The ellipses of similar folds are similar also, suggesting that a model can be developed. Free-fall tests simulating the free-free condition found in microgravity also show similar elliptical motion. Envelopes that bound the extents of the boom motion allow for collisions to be prevented by adjustment of the design.

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“…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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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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Design Developments of a Non-Planar Deployable Structure

Cited by 13 publications

References 2 publications

Self-Deployable Joints for Ultra-Light Space Structures

Self-Deployable Joints for Ultra-Light Space Structures

Empirically Bounding of Space Booms with Tape Spring Hinges

Large Strain Four-Point Bending of Thin Unidirectional Composites

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