Folding Large Antenna Tape Spring

Soykasap, Omer; Pellegrino, Sergio; Howard, Phil; Notter, Michael

doi:10.2514/1.28421

Cited by 41 publications

(22 citation statements)

References 14 publications

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“…Novel solar array and reflector antenna concepts based on the same general approach have been proposed, including the hollow solid reflector structure [5] shown in Fig. 1, the fold integrated thin-film stiffener solar array, which undergoes three different folding stages to achieve a highly compacted configuration [6], and the folding large antenna tape-spring radar concept [7].…”

mentioning

confidence: 99%

Quasi-Static Folding and Deployment of Ultrathin Composite Tape-Spring Hinges

Mallikarachchi

Pellegrino

2011

Journal of Spacecraft and Rockets

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Deployable structures made from ultrathin composite materials can be folded elastically and are able to selfdeploy by releasing the stored strain energy. This paper presents a detailed study of the folding and deployment of a tape-spring hinge made from a two-ply plain-weave laminate of carbon-fiber reinforced plastic. A particular version of this hinge was constructed, and its moment-rotation profile during quasi-static deployment was measured. The present study is the first to incorporate in the simulation an experimentally validated elastic micromechanical model and to provide quantitative comparisons between the simulations and the measured behavior of an actual hinge. Folding and deployment simulations of the tape-spring hinge were carried out with the commercial finite element package Abaqus/Explicit, starting from the as-built unstrained structure. The folding simulation includes the effects of pinching the hinge in the middle to reduce the peak moment required to fold it. The deployment simulation fully captures both the steady-state moment part of the deployment and the final snap back to the deployed configuration. An alternative simulation without pinching the hinge provides an estimate of the maximum moment that could be carried by the hinge during operation. This is about double the snapback moment.

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confidence: 99%

Quasi-Static Folding and Deployment of Ultrathin Composite Tape-Spring Hinges

Mallikarachchi

Pellegrino

2011

Journal of Spacecraft and Rockets

Self Cite

111

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“…4, the natural frequency increases to 7.5 Hz as the skirt width increases up to 185 mm, then it decreases for F/D=0.6 whereas it has a maximum of 8.9 Hz about 175mm for F/D=0. 8 . This suggest that the design parameters (such as F/D, number of plies, skirt with) should be optimized for high stiffness/mass ratio.…”

Section: Figure 2 Aku's Flexible Shell Reflector A) and B) Deployed mentioning

confidence: 99%

“…Shell reflectors have thin flexible reflective surface and some reinforcing Soykasap et al presented a foldable shell structure concept for P-band dual polarization antenna to be used for the measurement of terrestrial biomass levels from a spacecraft in LEO 8 . The antenna looks like a giant tape spring with a length of 17.29 m, a width of 2.82 m, an area of 50 m 2 .…”

Section: Introductionmentioning

confidence: 99%

Preliminary Design of Deployable Flexible Shell Reflector of an X-band Satellite Payload

Soykasap

Karakaya

Gayretli

et al. 2015

2nd AIAA Spacecraft Structures Conference

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Preliminary design of a self-deployable CFRP flexible shell reflector is presented for Xband satellite payload. The requirements, space qualified materials and their properties, finite element modeling of the reflector of 3 m diameter are given. The natural frequency, thermo-elastic and folding analysis of the reflector are performed. Folding concepts based on rolling two opposite edges of the reflector in a compact volume are studied. The folding and deployment of the reflector are demonstrated by a half size reflector manufactured. It is found that the developed flexible shell reflector has high potential for X-band payload with high stiffness/mass ratio, ease of manufacturing and low cost. NomenclatureCFRP = carbon fiber reinforced plastic CTE = coefficient of thermal expansion D = diameter E 1 = longitudinal elastic modulus E 2 = transverse elastic modulus F/D = focal length to diameter ratio G 12 = shear modulus LEO = low earth orbit RMS = root mean square RF = radio frequency  L S = longitudinal tensile strength  L S = longitudinal compressive strength  T S = transverse tensile strength  T S = transverse compressive strength S LT = shear strength SBR = spring back reflector SSBR = stiffened spring back reflector TDRS = tracking and data relay satellite  12 = major Poisson's ratio  21 = minor Poisson's ratio

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“…These problems have gained a great deal of attention related to deployment analysis of deployable structures for space applications. [9][10][11][12][13][14][15][16][17][18][19][20][21][22][23] However, despite such effort, little attention has been given to deployment analysis of large SAR antenna considering flexibility, which is an important intrinsic property of such a large structure.…”

Section: Introductionmentioning

confidence: 99%

Deployment analysis and optimization of a flexible deployable structure for large synthetic aperture radar antennas

Wang

Guo

Yang

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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Flexible deployment analysis and optimization of a novel deployable structure for deploying and supporting a 28 m long satellite synthetic aperture radar antenna are carried out in this study. Three stages are conducted in the deploying process: (1) acceleration, (2) uniform velocity, and (3) deceleration phases. The deployment experiments of the ground prototype show that the deployment angles among the antenna panels in the acceleration and deceleration phases are desynchronized. Flexible deployment dynamics is analyzed, and three indexes are identified to describe the deployment including deployment synchronism, steady driving torque, and maximum strain energy. An approach to optimize the auxiliary spring is presented to solve the desynchronized deployment problem. The response surface method is employed to model the optimization objective. The optimization and experimental results prove the feasibility of the proposed deployment analysis and optimization theory. The results of this work could be applied to other large deployable structures.

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Folding Large Antenna Tape Spring

Cited by 41 publications

References 14 publications

Quasi-Static Folding and Deployment of Ultrathin Composite Tape-Spring Hinges

Quasi-Static Folding and Deployment of Ultrathin Composite Tape-Spring Hinges

Preliminary Design of Deployable Flexible Shell Reflector of an X-band Satellite Payload

Deployment analysis and optimization of a flexible deployable structure for large synthetic aperture radar antennas

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