Research in structures and materials for future space transportationsystems - An overview

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

doi:10.2514/3.28361

Cited by 12 publications

(1 citation statement)

References 16 publications

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“…TPS system concepts (Fig. 9) that may be used for hypersonic transportation (both HST and TAV/ATAV) have been verified by rigorous tests at temperatures beyond 1500 K [22,23].…”

Section: Materials Structures and Thermal Protectionmentioning

confidence: 95%

Advanced Hypersonic Transportation Perspectives

Gopalaswami

2023

joast

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High-speed transportation design concepts are examined for advanced civil aviation and space transportation applications. The design concept of transatmospheric vehicles, flying directly from earth to orbit, will enable launching and recovery of small telecommunication and remote sensing satellites, harvesting solar energy from space, and space tourism.Commonality of flight regimes in atmospheric flight, the similarity of fuels, propulsion technology, aerodynamic configuration design, and airframe structure materials used in these high-speed flight regimes for air and space transportation are discussed in detail.A single, Integrated Hypersonic Transport Programme, is recommended, based on small size, low risk, and low cost vehicles. A dual fuel, kerosene-hydrogen system meets the needs of such an Integrated Hypersonic Transportation Programme, with kerosene for take-off, powered landing and low speed ascent/descent flight. Hydrogen is used for high-speed cruise flight. India would greatly benefit by an Integrated Hypersonics Transportation Programme, with leading institutions like ISRO, NAL and ADA working together to jointly study, design and build a strong technology base for small, unmanned hypersonic flight demonstrators. This project could then lead on, safely and economically, to hypersonic Executive Jet aircraft, and small fully Reusable Trans-Atmospheric Vehicles for direct ascent of the hypersonic aerospacecraft to earth orbit.

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“…TPS system concepts (Fig. 9) that may be used for hypersonic transportation (both HST and TAV/ATAV) have been verified by rigorous tests at temperatures beyond 1500 K [22,23].…”

Section: Materials Structures and Thermal Protectionmentioning

confidence: 95%

Advanced Hypersonic Transportation Perspectives

Gopalaswami

2023

joast

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Thermostructural Design of a Flying Winglet Experimental Structure for the EXPERT Re-entry Test

Ferraiuolo

Riccio

Gigliotti

et al. 2009

Journal of Heat Transfer

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Within the framework of the European Experimental Re-entry Test Bed (EXPERT) Program, aimed at improving the understanding of physical phenomena occurring during the return of space vehicles from space to earth, the design of a flying winged experimental payload has been performed in order to assess the thermomechanical behavior and resistance of ultrahigh temperature ceramics (UHTC) in real flight aerothermal environment. The EXPERT flying winglet article is intended to reproduce such conditions. Particular interest covers the design of the interfaces between the UHTC winglet and the EXPERT capsule thermal protection systems since thermal stresses arise during the re-entry phase. The fixation of the winglet to the capsule is achieved by means of dedicated bolts that must tolerate mechanical loads occurring at the first stages of the flight, that is, lift-off, ascent, and separation stages. The thermostructural design is performed by employing ANSYS/Workbench finite element commercial code; simulations take into account transient thermostructural loading conditions, the elastic-fragile behavior of the ceramic materials, and the temperature dependent elastic-plastic behavior of the capsule thermal protection systems. In the postprocessing phase, UHTC critical areas have been identified by following two different approaches. The first approach is deterministic and consists in applying a maximum stress criterion, the stress at a node is compared with the temperature dependent strength at that node. The second approach, which is commonly employed for elastic-fragile materials, is probabilistic and consists in applying a Weibull-like failure criterion. Thermal and structural analyses simulating the re-entry phase have demonstrated that the maximum stresses and temperatures evaluated do not exceed their corresponding limits. Then, a configuration respecting all the requirements of the design has been identified, and its thermal and mechanical performances are discussed in detail.

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Space Radiation Effects on the Thermo-Mechanical Behavior of Graphite-Epoxy Composites

Milkovich

Herakovich

Sykes

1986

Journal of Composite Materials

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This investigation of composite material properties utilized T300/934 graphite-epoxy that was subjected to 1.0 MeV electron radiation for a total dose of 1.0 x 1010 rads at a rate of 5.0 x 107 rads/hour, simulating a worst-case exposure equivalent to 30 years in space. Mechanical testing was performed on 4-ply unidirectional laminates over the temperature range of -250°F (116 K) to +250°F (394 K). In-plane elastic tensile and shear properties as well as strength were obtained ( E1, E2, v 12, G12, XT, YT, S). The results show that electron radiation degrades the epoxy matrix and produces products that volatilize at the temperatures considered. These degradation products plasticize the epoxy at elevated temperatures and embrittle it at low temperatures, thereby altering the mechanical properties of the composite.

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Research in structures and materials for future space transportationsystems - An overview

Cited by 12 publications

References 16 publications

Advanced Hypersonic Transportation Perspectives

Advanced Hypersonic Transportation Perspectives

Thermostructural Design of a Flying Winglet Experimental Structure for the EXPERT Re-entry Test

Space Radiation Effects on the Thermo-Mechanical Behavior of Graphite-Epoxy Composites

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