Evaluation of coated columbium for thermal protection systems application

Rummler, D. R.; Black, W. M.

doi:10.2514/6.1975-817

Cited by 4 publications

(2 citation statements)

References 1 publication

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“…Also shown by the open symbols are the fabricated unit masses of a full-scale TD-NiCr metallic panel 8 of a design similar to the L-605 system and a coated columbium panel. 9 The TD-Ni-Cr panel has successfully survived 100 simulated ascent and reentry thermal pressure cycles without excessive degradation. The solid curve shown for comparison is the unit mass of the Shuttle baseline RSI system, which consists of LI-900 tiles bonded directly to primary structure.…”

Section: Tps Modelsmentioning

confidence: 98%

Performance of Thermal Protection Systems in a Mach 7 Environment

Bohon

Sawyer

Hunt

et al. 1975

Journal of Spacecraft and Rockets

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The integrity and reusability of three flight-weight metallic and reusable surface insulation (RSI) thermal protection systems, designed for the space Shuttle entry environment, have been demonstrated. Each model successfully survived over 23 entry thermal cycles without serious degradation. The metallic systems were more tolerant of the hostile environment and provided a higher degree of reusability than did the RSI. Thermal expansion slip joints of the metallic TPS successfully prevented hot-gas ingress to the substructure. The RSI demonstrated high damage tolerance, and field repairs increased its reusability. Heat-transfer tests to further assess RSI gap heating indicate that stacked tile orientations may impose a penalty on tile thickness. Parameters influencing RSI impingement heating were determined and the heating data correlated. Nomenclature D= tile length (Figs. 11 and 12), m L = gap length (Fig. 10), m M t -local Mach number A p = panel differential pressure, Pa q = heat-transfer rate, w/m 2 Qf p = flat-plate heat-transfer rate, w/m 2 T -temperature, K s -surface dimension on tile perimeter (Fig. 11), m w -gap width (Fig. 10), m x -surface dimension from midpoint of tile (Fig. 12), m z = depth below tile surface (Fig. 10), m 5* = boundary-layer displacement thickness, m 6 = slope of tile forward-facing wall (Fig. 10), deg

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Section: Tps Modelsmentioning

confidence: 98%

Performance of Thermal Protection Systems in a Mach 7 Environment

Bohon

Sawyer

Hunt

et al. 1975

Journal of Spacecraft and Rockets

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“…Orbiter Study Application Areas 10 5 Orbiter Structural Design at Design Point IWing (Upper) 10 6 Ascent Environment History -Design Point I 11 7 Entry Environment History -Design Point I 11 8 Orbiter Structural Design at Design Point IIAft Fuselage (Lower) 12 9 Ascent Environment History -Design Point II 12 10 Entry Environment History -Design Point II 14 11 Orbiter Structural Design at Design Point IIIMain Landing Gear Door 14 12 Ascent Environment History -Design Point III 15 13 Entry Environment History -Design Point III 15 14 Orbiter Structural Design at Design Point IVForward Fuselage 16 15 Ascent Environment History -Design Point IV 16 16 Entry Environment History -Design Point IV 17 17 Candidate …”

mentioning

confidence: 99%

Assessment of Alternate Thermal Protection Systems for the Space Shuttle Orbiter

Hays

1983

Entry Vehicle Heating and Thermal Protection Systems: Space Shuttle, Solar Starprobe, Jupiter Galileo Probe

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

Kelly

Rummler

Jackson

1983

Journal of Spacecraft and Rockets

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This paper provides a review of some of the advances of the past decade in structures and materials that have application to future space transportation systems. The paper concentrates on metallic thermal protection systems and structures that could provide the structural efficiency, reliability, and durability dictated by future space utilization requirements. The need for completely reusable, onboard cryogenic fuel tanks is cited as the most challenging technical opportunity, and potential thermostructural concepts for tanks are identified. Other critical areas needing technology advances are discussed. Finally, the unique research opportunities offered by the Shuttle Orbiter experiments program for testing structures and thermal protection systems are explored.

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Evaluation of coated columbium for thermal protection systems application

Cited by 4 publications

References 1 publication

Performance of Thermal Protection Systems in a Mach 7 Environment

Performance of Thermal Protection Systems in a Mach 7 Environment

Assessment of Alternate Thermal Protection Systems for the Space Shuttle Orbiter

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

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