Assessment of alternate thermal protection systems for the Space Shuttle Orbiter

Kelly, H. N.; Webb, Granville L.

doi:10.2514/6.1982-899

Cited by 9 publications

(1 citation statement)

References 8 publications

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“…Ablative heatshield materials not only protect a vehicle from excessive heating, they also act as an aerodynamic body and sometimes as a structural component (2,3). Intensity and duration of heating, thermostructural requirements and shape stability (4,5), potential for particle erosion (6), weight limitations (7)(8)(9)(10), and reusability (11) are some of the factors which must be considered in selection of an ablative material. Some typical ablative environments are shown in Figure 1.…”

Section: The Ablation Environmentmentioning

confidence: 99%

Ablative Materials

Favaloro¹

2000

Kirk-Othmer Encyclopedia of Chemical Technology

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The word ablation is derived from the suppletive past particle of the Latin auferre, which means to remove. It was originally used in the geologic sense to describe the combined, predominantly thermal, processes by which a glacier wastes. The present use of the word maintains the thermal aspect and describes the absorption, dissipation, and blockage of heat associated with high speed entry into the atmosphere. Thus ablative, thermal protection materials are used to protect vehicles from damage during atmospheric reentry. The need for these materials was first realized during the development of operational ballistic missiles in Pennemunde, Germany, when a large percentage of V-2s failed to reach their targets because of missile skin disintegration caused by aerodynamic heating (1). Ablative materials are also used to protect rocket nozzles and ship hulls from propellant gas erosion, as protection from laser beams, and to protect land-based structures from high heat environments.

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Section: The Ablation Environmentmentioning

confidence: 99%

Ablative Materials

Favaloro¹

2000

Kirk-Othmer Encyclopedia of Chemical Technology

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Ablative Materials

2007

Van Nostrand's Scientific Encyclopedia

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X-33 Hypersonic Boundary-Layer Transition

Berry

Horvath

Hollis

et al. 2001

Journal of Spacecraft and Rockets

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Boundary layer and aeroheating characteristics of several X-33 configurations have been experimentally examined in the Langley 20-Inch Mach 6 Air Tunnel. Global surface heat transfer distributions, surface streamline patterns, and shock shapes were measured on 0.013-scale models at Mach 6 in air. Reynolds numbers based on model length of 0.9 to 6.6 million; and body-flap deflections of 0, 10 and 20-deg. The effects of discrete and distributed roughness elements on boundary layer transition, which included trip height, size, location, and distribution, both on and off the windward centerline, were investigated. The discrete roughness results on centerline were used to provide a transition correlation for the X-33 flight vehicle that was applicable across the range of reentry angles of attack. The attachment line discrete roughness results were shown to be consistent with the centerline results, as no increased sensitivity to roughness along the attachment line was identified. The effect of bowed panels was qualitatively shown to be less effective than the discrete trips; however, the distributed nature of the bowed panels affected a larger percent of the aft-body windward surface than a single discrete trip.

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Assessment of alternate thermal protection systems for the Space Shuttle Orbiter

Cited by 9 publications

References 8 publications

Ablative Materials

Ablative Materials

Ablative Materials

X-33 Hypersonic Boundary-Layer Transition

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