Nieto et al 2018a - Revision history

Materiales.Compuestos at 10:29, 12 October 2022

2022-10-12T10:29:21Z

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Materiales.Compuestos at 15:28, 11 October 2022

2022-10-11T15:28:00Z

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Materiales.Compuestos at 07:59, 6 October 2022

2022-10-06T07:59:13Z

Materiales.Compuestos at 07:54, 6 October 2022

2022-10-06T07:54:31Z

Materiales.Compuestos at 07:52, 6 October 2022

2022-10-06T07:52:55Z

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 <span style="text-align: center; font-size: 75%;">'''Figure 4.''' Ring deployable structure composed of two chains of unit cells (one per semi-ring).</span></div>
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">[[File:Nieto et al 2018a-image9-c.png|centre|600x600px]]'''Figure 5.''' Modular Structure deployment synchronised by three chains of linear unit cells
+<span style="text-align: center; font-size: 75%;">'''Figure 5.''' Modular Structure deployment synchronised by three chains of linear unit cells
-</span></div>
+</div>
 COMET and PROSIX  have successfully developed and tested a 4 meter deployable ring with an inner cable network, demonstrating the viability of this unit cell, its synchronisation system, the possibility of combinations of these unit cells and the robustness and reliability of this kind of structures. Figure 6 shows the deployment test of a deployable conical ring structure, tested in December 2014.

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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 <span style="text-align: center; font-size: 75%;">'''Figure 3.''' Linear deployable structure composed of parallel chains of unit cells connected by rigid battens.</span></div>
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 <span style="text-align: center; font-size: 75%;">'''Figure 4.''' Ring deployable structure composed of two chains of unit cells (one per semi-ring).</span></div>

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 Figures 3 to 5 show the deployable structures commented above.
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 <span style="text-align: center; font-size: 75%;">'''Figure 3.''' Linear deployable structure composed of parallel chains of unit cells connected by rigid battens.</span></div>

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 The unit cell selected in paragraph 4 has been combined as in previous fig. 4 in a simple elliptical ring. Fig. 11 shows the deployed and semi-deployed status of this structure.
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 Once the unit cell and the linear architecture have been selected, unit cell requirements have been derived for the linear structures. The unit cell has been sized and designed according to these requirements and this unit cell has been assembled in order to build a 20 meter deployable linear structure. Figure 8 shows the modular deployable linear structure design in folded and deployed positions.
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 The stiffness of the deployed configuration has been calculated, providing an eigenfrequency of 1.3 Hz. In order to fully accomplish with the structure requirements, the structure has been reinforced with cable crossings (in magenta in figure 9) in order to increase its stiffness.
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 Actuation margins of the deployment have been calculated according to ECSS-E-ST-33-01C, resulting in values higher than 1.
+[[File:Nieto_et_al_2018a-image25.png|centre|600x600px]]
-[[Image:Nieto_et_al_2018a-image25.png|600px]]
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 The same kinds of friction, springs and cables have been introduced in the functional analyses, obtaining actuation margins higher than 1. Reliability of the deployment has also been checked by means of altering these characteristics, providing successful deployments. Fig. 12 shows a frame of one of these analyses.
+[[File:Nieto_et_al_2018a-image29.png|centre|600x600px]]
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 Once all the options were compared, and based on the project requirements, the unit cell selected for the deployment of both ring and linear structures has been determined to be composed of two consecutive V-folding rectangles with a common non-deployable side. The synchronization of both V-folding rectangles will be done via cables and pulleys. This cables and pulleys system can connect adjacent unit cells so a chain of unit cells can be built. These chains do not necessarily have to be coplanar. Figure 2 shows this unit cell.
+[[File:Nieto_et_al_2018a-image6.jpeg|centre|600x600px]]
-[[Image:Nieto_et_al_2018a-image6.jpeg|600px]]
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Figure 1'''. Planar bar linkages for space applications used or candidates for space ring deployable structures.</div>
+<span style="text-align: center; font-size: 75%;">'''Figure 1'''. Planar bar linkages for space applications used or candidates for space ring deployable structures.</span></div>
 ==='''3.2''' Linear Deployable Structures===
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Figure 2.''' Unit Cell for the present project: Two parallel V-folding rectangles synchronized by cables and pulleys. </div>
+<span style="text-align: center; font-size: 75%;">'''Figure 2.''' Unit Cell for the present project: Two parallel V-folding rectangles synchronized by cables and pulleys. </span></div>
 Each V-folding is self-deployed by a spring. By this way, the deployment of the unit cell is passive. The need of active motorization is suppressed, and only a cable is needed to control the unit cell deployment.
@@ Line 88: / Line 88: @@
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Figure 3.''' Linear deployable structure composed of parallel chains of unit cells connected by rigid battens.</div>
+<span style="text-align: center; font-size: 75%;">'''Figure 3.''' Linear deployable structure composed of parallel chains of unit cells connected by rigid battens.</span></div>
@@ Line 99: / Line 99: @@
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Figure 4.''' Ring deployable structure composed of two chains of unit cells (one per semi-ring).</div>
+<span style="text-align: center; font-size: 75%;">'''Figure 4.''' Ring deployable structure composed of two chains of unit cells (one per semi-ring).</span></div>
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 | [[Image:Nieto_et_al_2018a-picture-Text Box 9.svg|center|72px]]
 |}
-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">[[File:Nieto et al 2018a-image9-c.png|centre|600x600px]]'''Figure 5.''' Modular Structure deployment synchronised by three chains of linear unit cells
+<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-</div>
+<span style="text-align: center; font-size: 75%;">[[File:Nieto et al 2018a-image9-c.png|centre|600x600px]]'''Figure 5.''' Modular Structure deployment synchronised by three chains of linear unit cells
 COMET and PROSIX  have successfully developed and tested a 4 meter deployable ring with an inner cable network, demonstrating the viability of this unit cell, its synchronisation system, the possibility of combinations of these unit cells and the robustness and reliability of this kind of structures. Figure 6 shows the deployment test of a deployable conical ring structure, tested in December 2014.
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Figure 7.''' The three architectures considered: top-left: conical ring, top-right: cylindrical ring; bottom: double cylindrical ring</div>
+<span style="text-align: center; font-size: 75%;">'''Figure 7.''' The three architectures considered: top-left: conical ring, top-right: cylindrical ring; bottom: double cylindrical ring</span></div>
 Three different diameters (6 m, 12 m and 24 m), were taken into account. Table 1 shows the mass efficiency of each configuration analysed for the same deployed stiffness requirements.
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Table 1.''' Comparison of mass efficiency (kg/m<sup>2</sup>) of different ring configuration with the same deployed stiffness performance</div>
+<span style="text-align: center; font-size: 75%;">'''Table 1.''' Comparison of mass efficiency (kg/m<sup>2</sup>) of different ring configuration with the same deployed stiffness performance</span></div>
 [[File:Nieto_et_al_2018a-image19.png|centre|339x339px]]
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Figure 8.''' Linear Structure in folded, intermediate, and deployed positions.</div>
+<span style="text-align: center; font-size: 75%;">'''Figure 8.''' Linear Structure in folded, intermediate, and deployed positions.</span></div>
 The stiffness of the deployed configuration has been calculated, providing an eigenfrequency of 1.3 Hz. In order to fully accomplish with the structure requirements, the structure has been reinforced with cable crossings (in magenta in figure 9) in order to increase its stiffness.
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Figure 9.''' Deployable linear structure first bending mode</div>
+<span style="text-align: center; font-size: 75%;">'''Figure 9.''' Deployable linear structure first bending mode</span></div>
 This configuration provides an excellent deployment ratio between stowed and deployed length of less than 5%, which is a very promising value not only for this particular mission specification, but for longer masts.
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Figure 10.''' Reliability analysis with multibody dynamic simulation.</div>
+<span style="text-align: center; font-size: 75%;">'''Figure 10.''' Reliability analysis with multibody dynamic simulation.</span></div>
 Deployment accuracy (SRO) has also been assessed, providing values of 1.2 mm (6·10<sup>-5</sup> x Length).
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Figure 11.''' Deployable ring structure, folded and deploying.</div>
+<span style="text-align: center; font-size: 75%;">'''Figure 11.''' Deployable ring structure, folded and deploying.</span></div>
 Ratio between the folded diameter and the deployed diameter is lesser than 10%, providing excellent perspectives regarding its launcher accommodation.
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Figure 12.''' Multibody dynamic simulation of the ring deployment.</div>
+<span style="text-align: center; font-size: 75%;">'''Figure 12.''' Multibody dynamic simulation of the ring deployment.</span></div>
 Deployment accuracy (SRO) of the single ring has also been assessed, providing values of 0.42 mm.
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Figure 13.''' Cable network integrated in the deployable ring structure.</div>
+<span style="text-align: center; font-size: 75%;">'''Figure 13.''' Cable network integrated in the deployable ring structure.</span></div>
 The stiffness of the designed reflector structure has been measured by means of a free-free modal analysis, resulting in a first eigenfrequency of 1.15 Hz, which mode can be seen in fig. 14.
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Figure 14.''' First eigenvalue of deployable reflector with integrated network.</div>
+<span style="text-align: center; font-size: 75%;">'''Figure 14.''' First eigenvalue of deployable reflector with integrated network.</span></div>
 The mass of the designed reflector is less than 0.35 kg/m<sup>2</sup>.
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Figure 15.''' RMS error (m) distribution of the design faceted surface (global RMS=1.68 mm).</div>
+<span style="text-align: center; font-size: 75%;">'''Figure 15.''' RMS error (m) distribution of the design faceted surface (global RMS=1.68 mm).</span></div>
 Concerning thermo-elastic stability, the RMS error of the deformed surface after best-fitting adjustment for the worst case (-170 °C) is 1.71 mm, as it can be seen in fig. 16.
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Figure 16'''. RMS error (m) distribution after best-fitting adjustment for the worst thermo-elastic case (global RMS=1.71 mm).</div>
+<span style="text-align: center; font-size: 75%;">'''Figure 16'''. RMS error (m) distribution after best-fitting adjustment for the worst thermo-elastic case (global RMS=1.71 mm).</span></div>
 ==9 Resume of requirements==
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Table 2.''' Resume of linear deployable structure requirements compliance (until today)</div>
+<span style="text-align: center; font-size: 75%;">'''Table 2.''' Resume of linear deployable structure requirements compliance (until today)</span></div>
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Table 3'''. Resume of ring deployable structure with integrated network requirements compliance (until today)</div>
+<span style="text-align: center; font-size: 75%;">'''Table 3'''. Resume of ring deployable structure with integrated network requirements compliance (until today)</span></div>
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 ==1 Scope of the study ==
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 Three different diameters (6 m, 12 m and 24 m), were taken into account. Table 1 shows the mass efficiency of each configuration analysed for the same deployed stiffness requirements.
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
 '''Table 1.''' Comparison of mass efficiency (kg/m<sup>2</sup>) of different ring configuration with the same deployed stiffness performance</div>
 Other considerations, regarding accuracy, thermal stability, deployment reliability, storage efficiency, kinematic simplicity, number of equal parts and cost were taken into account and weighted. The simple cylindrical ring resulted to be more adequate for the purpose of this project.
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 Once the main features of the designed linear and ring structures has been shown, tables 2 and 3 present a summary of the main deployable structures requirements and the values obtained.
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 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Table 2.''' Resume of linear deployable structure requirements compliance (until today)</div>
+'''Table 3'''. Resume of ring deployable structure with integrated network requirements compliance (until today)</div>
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-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-'''Table 3'''. Resume of ring deployable structure with integrated network requirements compliance (until today)</div>
 ==10 Conclusion and further works==

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-J. Nieto<sup>(1)</sup>, J. Fayos<sup>(2)</sup>, A. Pipó<sup>(3)</sup>, C. Montesano<sup>(4)</sup>, E. Ozores<sup>(5)</sup>, J. Santiago-Prowald<sup>(5)</sup></div>
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-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;"><sup> (1)</sup> Comet Ingeniería, C/ Convento Carmelitas, 2-2, 46010, Valencia, Spain. Email: [mailto:jnieto@comet-ingenieria.es jnieto@comet-ingenieria.es]</span></div>
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-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;"><sup>(2)</sup> Comet Ingeniería, C/ Convento Carmelitas, 2-2, 46010, Valencia, Spain.  Email: [mailto:jfayos@comet-ingenieria.es jfayos@comet-ingenieria.es]</span></div>
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-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;"><sup>(3)</sup> Prosix Engineering, Avda. de Carlos I, 2-6, 20011, San Sebastián, Spain. Email: [mailto:alvaro.pipo@prosix.es alvaro.pipo@prosix.es]</span></div>
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-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;"><sup>(4)</sup> Airbus Defence and Space, EADS CASA Espacio, Avda. de Aragón 404, 28022, Madrid, Spain. </span></div>
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-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">Email: [mailto:carlos.montesano@airbus.com carlos.montesano@airbus.com]</span></div>
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-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;"><sup>(5)</sup> Airbus Defence and Space, EADS CASA Espacio, Avda. de Aragón 404, 28022, Madrid, Spain. </span></div>
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-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">Email: [mailto:eduardo.ozores@airbus.com eduardo.ozores@airbus.com]</span></div>
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-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;"><sup>(6)</sup> European Space Agency, ESTEC, Keplerlaan 1, PB 299, NL-2200 AG Noordwijk, The Netherlands. </span></div>
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-<div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
-<span style="text-align: center; font-size: 75%;">Email: [mailto:Julian.Santiago.Prowald@esa.int Julian.Santiago.Prowald@esa.int]</span></div>
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-{| style="width: 87%;border-collapse: collapse;"
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-|  colspan='2'  style="vertical-align: top;"|<span id='_GoBack'></span><big>Estructuras modulares desplegables</big>
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-|  style="border-bottom: 1pt solid black;vertical-align: top;"|<span style="text-align: center; font-size: 75%;"> [[Image:Nieto_et_al_2018a-image1.png|54px]] </span>
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-|  style="border-top: 1pt solid black;border-bottom: 1pt solid black;vertical-align: top;"|<span style="text-align: center; font-size: 75%;">Historia del artículo:</span>
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-<span style="text-align: center; font-size: 75%;">Recibido 5 de Mayo 2017</span>
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-<span style="text-align: center; font-size: 75%;">En la versión revisada 5 de Mayo 2017</span>
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-<span style="text-align: center; font-size: 75%;">Aceptado 31 de Mayo 2017</span>
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-<span style="text-align: center; font-size: 75%;">Accesible online 21 de Junio 2017 </span>
-|  rowspan='3' style="vertical-align: top;"|<span style="text-align: center; font-size: 75%;">Antenas y telescopios de gran apertura y largas longitudes focales tienen importantes aplicaciones espaciales en el campo de las telecomunicaciones, la observación terrestre y distintas misiones científicas. En este contexto, una actividad en la que se está trabajando en ESA TRP, desarrollada por COMET Ingeniería, PROSIX ingeniería y Aribus DS (CASA espacio), es el diseño de estructuras modulares que se puedan ensamblar a partir de celdas unitarias, desarrollando partes representativas de mástiles desplegables (estructuras lineales) y anillos (aperturas de antenas o radiotelescopios). Este trabajo presenta el estado actual del proyecto y los resultados obtenidos hasta la fecha. Los resultados de este trabajo se confir</span><span style="text-align: center; font-size: 75%;">marán durante el próximo PDR que se celebrará en ESA-ESTEC. </span>
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-|  style="border-top: 1pt solid black;border-bottom: 1pt solid black;vertical-align: top;"|<span style="text-align: center; font-size: 75%;">Palabras clave:</span>
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-<span style="text-align: center; font-size: 75%;">Estructuras modulares</span>
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-<span style="text-align: center; font-size: 75%;">Estructuras desplegables</span>
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-<span style="text-align: center; font-size: 75%;">Antenas</span>
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-<span style="text-align: center; font-size: 75%;">Estructuras espaciales</span>
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-|  colspan='2'  style="vertical-align: top;"|<big>Modular deployable structures</big>
-|-
-|  style="vertical-align: top;"|<span style="text-align: center; font-size: 75%;"> [[Image:Nieto_et_al_2018a-image2.png|54px]] </span>
-|  style="vertical-align: top;"|
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-|  style="vertical-align: top;"|<span style="text-align: center; font-size: 75%;">Keywords:</span>
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-<span style="text-align: center; font-size: 75%;">Modular structures</span>
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-<span style="text-align: center; font-size: 75%;">Deployable structures</span>
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-<span style="text-align: center; font-size: 75%;">Antennas</span>
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-<span style="text-align: center; font-size: 75%;">Space structures</span>
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-|  style="vertical-align: top;"|<span style="text-align: center; font-size: 75%;">Large aperture antennas and telescopes, long baselines and long focal lengths in space have important applications for Telecommunications, Earth Observation and Science missions. Within this context, an ESA TRP activity is currently under development, carried out by COMET Ingeniería, PROSIX Engineering and Airbus DS (CASA Espacio), with the aim of designing overall structural assemblies based on unit cells developing representative parts of deployable masts (linear structures) and rings (antenna or radiotelescope aperture). This paper presents the current status of this project and the results obtained until the date of presentation of this paper. The results of these paper will be confirmed during next PDR to be celebrated at ESA-ESTEC.</span>
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 ==1 Scope of the study ==