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Sunday, May 17, 2020 | History

4 edition of Analysis of the shuttle orbiter reinforced carbon-carbon oxidation protection system found in the catalog.

Analysis of the shuttle orbiter reinforced carbon-carbon oxidation protection system

Analysis of the shuttle orbiter reinforced carbon-carbon oxidation protection system

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  • 34 Currently reading

Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC], [Springfield, Va .
Written in English

    Subjects:
  • Space shuttles

  • Edition Notes

    StatementS.D. Williams ... [et al.].
    SeriesNASA technical memorandum -- 104792.
    ContributionsWilliams, S. D., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL14667437M
    OCLC/WorldCa31736626

    1. AIAA paper Space Shuttle Orbiter – Leading Edge Structural Design/analysis materials allowables 2. AIAA Space Shuttle Orbiter Aerodynamics Induced by Asymmetric Boundary Layer Transition 3. NASA TP “Oxidation of Reinforced Carbon-Carbon Subject to Hypervelocity Impact”, by Curry et al., 4. The Reinforced Carbon-Carbon (RCC) system (including all RCC, supporting structure and attaching hardware) is an essential component of the Space Shuttle Orbiter Thermal Protection System (TPS) and has a Criticality Rating of 1 (loss of crew - loss of vehicle). and a sealant coating that provides additional oxidation protection.

      The Reinforced Carbon-Carbon (RCC) system (including all RCC, supporting structure and attaching hardware) is an essential component of the Space Shuttle Orbiter Thermal Protection System . Abstract. The reinforced carbon-carbon (RCC) heat shield components on the Space Shuttle's wings must withstand harsh atmospheric reentry environments where the wing leading edge can reach temperatures of 3, F. Potential damage includes impact damage, micro cracks, oxidation in the silicon carbide-to-carbon-carbon layers, and interlaminar disbonds.

    The Space Shuttle program was the fourth human spaceflight program carried out by the National Aeronautics and Space Administration (NASA), which accomplished routine transportation for Earth-to-orbit crew and cargo from to Its official name, Space Transportation System (STS), was taken from a plan for a system of reusable spacecraft of which it was the only item funded for. Criticism of the Space Shuttle program stemmed from claims that NASA's Shuttle program failed to achieve its promised cost and utility goals, as well as design, cost, management, and safety issues. Fundamentally, it failed in the goal of reducing the cost of space access. Space Shuttle incremental per-pound launch costs ultimately turned out to be considerably higher than those of expendable.


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Analysis of the shuttle orbiter reinforced carbon-carbon oxidation protection system Download PDF EPUB FB2

Preface. This technical memorandum is an expanded version of AIAAAblation Analysis of the Shuttle Orbiter Oxidation-Protected Reinforced Carbon-Carbon (RCC), presented at the sixth AIAAdASME Joint Thermophysics and Heat Transfer Conference, June, Colorado Springs, Size: 2MB. Ablation analysis of the Shuttle Orbiter oxidation protected reinforced carbon-carbon.

Williams, Donald M. Curry, Dennis C. Chao and Vuong T. PhamCited by: Get this from a library. Analysis of the shuttle orbiter reinforced carbon-carbon oxidation protection system.

[S D Williams; United States. National Aeronautics and Space Administration.;]. Reusable, oxidation-protected reinforced carbon-carbon (RCC) has been successfully flown on all Shuttle Orbiter flights. Thermal testing of the silicon carbide-coated RCC to determine its oxidation characteristics has been performed in convective (plasma Arc-Jet) heating facilities.

Reinforced carbon/carbon (RCC) protects the Space Shuttle Orbiter wing leading edge and nose cap from the heat of re-entry.

The oxidation protection system is based on a SiC conversion coating. This report is on oxidation microstructures observed in the reinforced carbon/carbon (RCC) used for the thermal protection of the wing leading edge and nose cap of the Space Shuttle Orbiter.

Consider first unprotected carbon/carbon. There is extensive literature on the oxidation of these materials. Oxidation begins to be significant above about °C. Reinforced carbon-carbon, or RCC, is one of the principle components of the thermal protection system of the orbiter.

It is used as a high-temperature aerodynamic structure on the leading-edge structural subsystem, which consists of the nose cap, chin panel, wing leading edge and associated seals and access pan-els.

Ablation analysis of the Shuttle Orbiter oxidation protected reinforced carbon-carbon Hypervelocity impact testing of Shuttle Orbiter thermal protection system tiles.

1 January Thermal Structural Analysis of the Reinforced Carbon-Carbon Chin Panel. Thermal Structures and Materials for High-Speed Flight August 33rd. space shuttle orbiter systems THERMAL PROTECTION SYSTEM The thermal protection system consists of various materials applied externally to the outer structural skin of the orbiter to maintain the skin within acceptable temperatures, primarily during the entry phase of the mission.

Reusable, oxidation-protected reinforced carbon-carbon has been successfully flown on all Shuttle Orbiter flights.

Reinforced Carbon-Carbon. Reinforced Carbon-Carbon is a lightweight heat-shielding material used on the wing leading edge and nose cap of the Shuttle. NASA Glenn researchers studied the material to gain a deeper understanding of how it degrades with each mission cycle.

Reusable, oxidation-protected reinforced carbon-carbon (RCC) has been successfully flown on all Shuttle Orbiter flights. Thermal testing of the silicon. Reinforced Carbon-Carbon. A diffusion reaction occurs between the dry pack and carbon-carbon in which the outer layers of the carbon-carbon are converted to silicon carbide (whitish-gray color) with no thickness increase.

RCC is placed over the blanket and is attached by metal standoffs for additional protection from the forward orbiter. Carbon -Carbon (C-C) composites can absorb heat without deformation because of its low coefficient of the thermal expansion in the fiber direction (mm) and (mm) in the perpendicular direction, and wear rates (mm) and (mm) in the fiber direction and.

the Space Shuttle) increases by about $10, for every pound of launch weight and in order to keep space expeditions economically viable in the 21st century, it is imperative that the launch cost be reduced by an order of magnitude.

The thermal protection systems used on the Space Shuttles are reinforced carbon/carbon (RCC) at the nose and. This SiC coating is necessary to provide oxidation protection to the Space Shuttle Orbiter’s wing leading edge during the high heating experienced on re-entry of the orbiter through the Earth’s atmosphere.

The high temperature processing results in voids in the carbon–carbon substrate and micro-cracks in the SiC coating. The development and application of advanced nondestructive evaluation techniques for the Reinforced Carbon‐Carbon (RCC) components of the Space Shuttle Orbiter Leading Edge Structural Subsystem (LESS) were identified as a crucial step toward returning the shuttle fleet to service.

In order to help meet this requirement, eddy current techniques have been developed for application to RCC.

MR&D Work on Space Shuttle Repair. Since the Columbia Space Shuttle tragedy, MR&D has been significantly involved with analysis and design, fabrication and testing efforts associated with refractory composite materials and structures designs for the thermal protection system repairs of the NASA Space Shuttle.

In this study, coated reinforced carbon-carbon (RCC) samples of similar structure and composition as that from the NASA space shuttle orbiter’s thermal protection system were fabricated with slots in their coating simulating craze cracks. These specimens were used to study oxidation damage detection and characterization using NDE methods.

Understanding Carbon Reinforced Carbon. by Martin Grolms | Apr 1, As carbon-carbon brake discs and pads they are a standard component of Formula One and aircraft brake systems. C/C is well-suited to structural applications at high temperatures, or where thermal shock resistance or a low coefficient of thermal expansion is needed.

The Space Shuttle thermal protection system (TPS) is the barrier that protected the Space Shuttle Orbiter during the searing 1, °C (3, °F) heat of atmospheric reentry. A secondary goal was to protect from the heat and cold of space while in orbit.A breach in the thermal protection system: heat-resistant tiles, thermal blankets, and reinforced carbon-carbon.

What is "foam shedding," and why didn't NASA see it as a serious problem? Chunks of insulating foam breaking off, and NASA did not see it as a serious problem as they had observed it so many times on orbiters that returned safely.A thermal math model for the Space Shuttle Reinforced Carbon-Carbon (RCC) Plug Repair was developed to increase The Shuttle Orbiter Leading Edge Structural coating, MCM, is also used to increase oxidation protection of the system and is brushed over the SiC coating.