Design and Testing of Self-Deploying Membrane Optic Support Structure Using Rollable Composite Tape Springs

Footdale, Joseph; Murphey, Thomas W.; Peterson, Michael E.

doi:10.2514/6.2013-1459

Cited by 13 publications

(9 citation statements)

References 5 publications

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“…4 The United States Air Force Research Laboratory (AFRL) Space Vehicles Directorate has developed a tape spring, a type of a deployable structure, which utilizes the stored strain energy of the structure to self-deploy, therefore eliminating the need for external energy sources. 5 The tape spring consists of a single on-axis CFRP layer sandwiched between two layers of offaxis (45 ) CFRP. While deployment utilizes the stiffness of the on-axis layer, energy dissipation during stowage is strongly dependent on the stress-relaxation of the off-axis layers.…”

Section: Introductionmentioning

confidence: 99%

“…While deployment utilizes the stiffness of the on-axis layer, energy dissipation during stowage is strongly dependent on the stress-relaxation of the off-axis layers. 4,5 Furthermore, from the strain energy density equation, when stiffness is reduced in half, the storage energy reduces by 50% as well. Unlike a storage tubular extendable member (STEM) boom, a tape spring, due to its laminate design, is stable in a rolled position and does not need external containment.…”

Section: Introductionmentioning

confidence: 99%

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Controlling off-axis stiffness and stress-relaxation of carbon fiber-reinforced polymer using alumina nanoparticles

Garner

Genedy

Kandil

et al. 2017

Journal of Composite Materials

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This investigation experimentally examines the effect of incorporating alumina nanoparticles on the off-axis stiffness and stress-relaxation of carbon fiber-reinforced polymer composites. Four epoxy–alumina nanoparticle nanocomposites incorporating 0.0, 1.0, 2.0, and 3.0 wt% alumina nanoparticles of the total weight of epoxy are examined. Off-axis tension stiffness and stress-relaxation tests were performed on carbon fiber-reinforced polymer coupons fabricated with alumina nanoparticles–epoxy nanocomposites. Dynamic mechanical analysis testing of neat epoxy and epoxy nanocomposites incorporating alumina nanoparticles was used to identify the stiffness and relaxation behavior of the alumina nanoparticles–epoxy nanocomposite matrix. Fourier transform infrared spectroscopy was used to observe chemical changes when alumina nanoparticles are mixed with epoxy. It is shown that using alumina nanoparticles at a concentration close to 2.0 wt%, can reduce the off-axis stiffness by ∼30% and increase the off-axis stress-relaxation of carbon fiber-reinforced polymer by ∼10%.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Controlling off-axis stiffness and stress-relaxation of carbon fiber-reinforced polymer using alumina nanoparticles

Garner

Genedy

Kandil

et al. 2017

Journal of Composite Materials

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“…Over the past decades, a significant amount of research has been conducted in deployable lightweight systems, in particular for space applications [1][2][3]. For example, membrane radar antennas [4,5], deployable membrane reflectors [6][7][8][9], membrane optic support structures [10], and solar sails [11,12] were studied and developed under this concept.…”

Section: Introductionmentioning

confidence: 99%

Control‐oriented modeling and deployment of tensegrity–membrane systems

Yang

Sultan

2016

Intl J Robust & Nonlinear

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Summary This study addresses control‐oriented modeling and control design of tensegrity–membrane systems. Lagrange's method is used to develop a control‐oriented model for a generic system. The equations of motion are expressed as a set of differential‐algebraic equations (DAEs). For control design, the DAEs are converted into second‐order ordinary differential equations (ODEs) based on coordinate partitioning and coordinate mapping. Because the number of inputs is less than the number of state variables, the system belongs to the class of underactuated nonlinear systems. A nonlinear adaptive controller based on the collocated partial feedback linearization (PFL) technique is designed for system deployment. The stability of the closed‐loop system for the actuated coordinates is studied using the Lyapunov stability theory. Because of system complexity, numerical tests are used to conduct stability analysis for the dynamics of the underactuated coordinates, which represents the system's zero dynamics. For the tensegrity–membrane systems studied in this work, analytical proof of zero dynamics stability remains an open theoretical problem. An H∞ controller is implemented for rapid stabilization of the system at the final deployed configuration. Simulations are conducted to test the performance of the two controllers. The simulation results are presented and discussed in detail. Copyright © 2016 John Wiley & Sons, Ltd.

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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].…”

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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 and Testing of Self-Deploying Membrane Optic Support Structure Using Rollable Composite Tape Springs

Cited by 13 publications

References 5 publications

Controlling off-axis stiffness and stress-relaxation of carbon fiber-reinforced polymer using alumina nanoparticles

Controlling off-axis stiffness and stress-relaxation of carbon fiber-reinforced polymer using alumina nanoparticles

Control‐oriented modeling and deployment of tensegrity–membrane systems

Large Strain Four-Point Bending of Thin Unidirectional Composites

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