Research in structures and materials for future space transportation systems - An overview

Kelly, H. N.; Rummler, D. R.; Jackson, L. R.

doi:10.2514/6.1979-859

Cited by 8 publications

(5 citation statements)

References 5 publications

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“…More recent results indicate that a reduction of approximately 25% in metallic standoff panel masses can be achieved through advanced design. 10 This reduction would carry over to each of the metallic standoff systems studied here.…”

Section: Materials Considerationsmentioning

confidence: 97%

“…This assumption is supported by the development of FRCI. 10 If not, however, it may be necessary to pay the mass penalty associated with the more durable metallic standoff systems. The ability to fabricate curved and intersecting surfaces and the effect of local hot spots because of shock impingement must be assessed before this option can be chosen.…”

Section: Study Limitationsmentioning

confidence: 99%

“…Titanium would represent the next choice for a low-mass RSI/structure combination. The development of higher temperature aluminum alloys [to 750K/(890°F)] 10 and lower mass aluminum honeycomb structures 7 may eventually offset these benefits. The increased insulation requirements for internal systems and payloads necessary for these warm structures would also reduce the benefits somewhat.…”

Section: Structural Materials Effects On Tps Requirementsmentioning

confidence: 99%

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Lifting entry vehicle mass reduction through integrated thermostructural/trajectory design

Wurster

1983

Journal of Spacecraft and Rockets

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The study described in this paper examines the impact of thermostructural/trajectory design integration on advanced-winged entry vehicle mass. A variety of thermal protection system (TPS) concepts are considered, and entry trajectories tailored specifically to each concept in terms of peak heat rate and total heat load are used in conjunction with an aerodynamic heating/thermal analysis program to determine the TPS requirements. Results indicate that for an aluminum structure, either the reusable surface insulation (RSI) or the hybrid TPS (RSI forward, Ren£ 41 metallic standoff aft) has the potential to yield the lowest mass system. The metallic standoff system is, however, quite competitive and, with the 25% reduction in the panel mass anticipated, could surpass the RSI system. Results also indicate that significant improvements in hot-structure design are necessary before such a system can become competitive. An assessment is made of the potential impact of higher temperature structure materials on combined TPS/structure mass. Results indicate that the greatest reduction in mass is obtained with the first 200K increase in temperature capability over that of aluminum and, thus, the potential for the lowest mass system appears to lie with either a graphite/polyimide or a titanium structure.Nomenclature lift coefficient specific heat at constant pressure, J/kg • K acceleration due to gravity, m/s 2 altitude, km thermal conductivity, W/m-K vehicle length, m lift-to-drag ratio reference heat rate, kW/m 2 reference heat load, MJ/m 2 thickness, cm temperature, K Earth-relative velocity, m/s body centerline location, m angle of attack, deg density, kg/m 3 ultimate tensile strength, kN/m 2

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Section: Materials Considerationsmentioning

confidence: 97%

Section: Study Limitationsmentioning

confidence: 99%

Section: Structural Materials Effects On Tps Requirementsmentioning

confidence: 99%

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Lifting entry vehicle mass reduction through integrated thermostructural/trajectory design

Wurster

1983

Journal of Spacecraft and Rockets

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“…The TPS conceptssuccessfully tested on the Space Shuttle for over thirty years -have been proved to be quite ineffective with respect to the reusability requirement: in fact, the TPS tiles are subjected to a complex after flight inspection/reparation management, which is not very efficient from a time/cost point of view [3][4]. To overcome these limitations, for highly aero-thermally stressed structures the TPS concepts may be substituted by "hot structure" concepts, in which the structure itself is conceived to resist the aero-thermal fluxes without employing TPS tiles [2][3][4][5]. The present work refers to the SHS project and in particular illustrates the process performed in order to size the pin that has to guarantee the connection between two parts of the USV-SHS nose represented schematically in figure 1.…”

mentioning

confidence: 96%

Contact sensitivity analysis of a coupling pin for the nose cap of a launch re-entry vehicle

Ferraiuolo

Riccio

Tescione

et al. 2006

57th International Astronautical Congress

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The present work has been developed within CIRA USV-SHS activities. The Sharp Hot Structures Project (SHS) is focused on the applicability of modified diboride compounds to the manufacturing of high performance and slender shaped hot structures. The final products of the research are, on the short term, an innovative nose cap and a wing leading edge. The aim of the work is to size the coupling pin and the corresponding contact area with massive ZrB2-SiC and C/SiC-Graphite dome, ensuring structural integrity of the components connected. The use of a coupling pin is necessary since adhesive ceramics present several attaching difficulties. The design variables considered in the thermal-structural design of the coupling pin are: pin length, hole length, pin and hole shapes and diameters. The coupling pin is made of the same material of the massive cone to avoid the coming up of thermal stresses caused by the mismatch between coefficients of thermal expansion; however, metallic coupling pin will be analysed because of the reduced manufacturing costs. The results of this work will be useful to prepare a prototype of the Nose cap concept that will be on-ground tested into the arcjet Plasma Wind Tunnel, available at CIRA. Ansys commercial code, employing finite element modelling, has been adopted in order to perform non-linear contact analyses.Downloaded by CARLETON UNIVERSITY LIBRARY on July 30, 2015 | http://arc.aiaa.org |

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“…The former influences the total weight of the vehicle, the latter influences the vehicle efficiency (Thornton, 1996;Kelly et al, 1983;Shih et al, 1988). In order to perform the thermo-structural sizing of the component it is necessary to evaluate the stress and temperature distribution.…”

Section: Introductionmentioning

confidence: 99%

A New Methodology to Preliminary Design Structural Components of Re-Entry and Hypersonic Vehicles

Ferraiuolo¹,

Manca²

2011

Wind Tunnels and Experimental Fluid Dynamics Research

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Research in structures and materials for future space transportation systems - An overview

Cited by 8 publications

References 5 publications

Lifting entry vehicle mass reduction through integrated thermostructural/trajectory design

Lifting entry vehicle mass reduction through integrated thermostructural/trajectory design

Contact sensitivity analysis of a coupling pin for the nose cap of a launch re-entry vehicle

A New Methodology to Preliminary Design Structural Components of Re-Entry and Hypersonic Vehicles

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