Other

The United States of America As Represented by the Administrator of the

Howard E Goldstein

Daniel B Leiser

Marnell Smith

James C Fletcher

Robert A Frosch

David A Stewart

Demetrius A Kourtides

Salvatore R Riccitiello

Paul M Sawko

James M Beggs

Victor W Katvala

Carlos A Estrella

William C Pitts

Norman B Zimmerman

Composite flexible multilayer insulation systems (MLI) were evaluated for thermal performance and compared with currently used fibrous silica (baseline) insulation system. The systems described are multilayer insulations consisting of alternating layers of metal foil and scrim ceramic cloth or vacuum metallized polymeric films quilted together using ceramic thread. A silicon carbide thread for use in the quilting and the method of making it are also described. These systems are useful to provide lightweight thermal insulation for a variety of uses, particularly on the surface of aerospace vehicles subject to very high temperatures during flight.

Composite flexible blanket insulation

The present invention discloses a ceramic reusable externally applied thermal protection system (TPS). The system functions by using the composite device created by combining an upper shell, thermal insulation and lower tile components shown in FIG. 2. The upper shell effectively separates its primary functions as a toughened outer-surface and load carrier. In a preferred embodiment, a structurally strong ceramic/ceramic upper shell is manufactured from ceramic cloth upon which additional ceramic material has been deposited and maintains the configuration of the upper shell. The lower tile is composed of lightweight ceramic normally acceptable in this application. One or more lightweight rigid or flexible insulation materials are used in the cavity created by combining the upper shell and lower tile. The assembly of the overall tile is facilitated by attachment means effective to withstand the temperature and stress conditions. These attachment means include a self-locking wedge and complementary surface, ceramic pins, augers and the like. The device is useful on the interior surface of a kiln or the like and is also attached to the exterior surface of an aerospace vehicle for thermal protection.

Ceramic/ceramic shell tile thermal protection system and method thereof

A high temperature stable and solar radiation stable thermal control coating either useful as such, applied directly to a member to be protected, or applied as a coating on a re-usable surface insulation (RSI) has a base coat layer and an overlay glass layer. The base coat layer has a high emittance, and the overlay layer is formed from discrete, but sintered together glass particles to give the overlay layer a high scattering coefficient. The resulting two-layer space and thermal control coating has an absorptivity-to-emissivity ratio of less than or equal to 0.4 at room temperature, with an emittance of 0.8 at 1200.degree. F. It is capable of exposure to either solar radiation or temperatures as high as 2000.degree. F. without significant degradation. When used as a coating on a silica substrate to give an RSI structure, the coatings of this invention show significantly less reduction in emittance after long term convective heating and less residual strain than prior art coatings for RSI structures.

High temperature glass thermal control structure and coating

A flexible, adjustable refractory filler (1) is disclosed for filling gaps between ceramic tiles (10, 11) forming the heat shield of a space shuttle vehicle, to protect its aluminum skin (20) during atmospheric re-entry. The easily installed and replaced filler (1) consists essentially of a strip of ceramic cloth (3) coated, at least along both its longitudinal edges (4, 5), with a room temperature vulcanizable silicone rubber compound with a high emittance colored pigment. The filler may have one or more layers (2, 3), as the gap width requires. Preferred materials are basket-weave aluminoborosilicate cloth, and a rubber compounded with silicon tetraboride as the emittance agent and finely divided borosilicate glass containing about 7.5% B.sub.2 O.sub.3 as high temperature binder. The filler cloth strip or tape is cut to proper width and length, inserted into the gap, and fastened with previously applied drops of silicone rubber adhesive.

Adjustable high emittance gap filler

A refractory composite insulating material prepared from silica fibers and aluminosilicate fibers in a weight ratio ranging from 1:19 to 19:1, and about 0.5 to 30% boron oxide, based on the total fiber weight. The aluminosilicate fiber and boron oxide requirements may be satisfied by using aluminoborosilicate fibers and, in such instances, additional free boron oxide may be incorporated in the mix up to the 30% limit. Small quanitites of refractory opacifiers, such as silicon carbide, may be also added. The composites just described are characterized by the absence of a nonfibrous matrix.

Fibrous refractory composite insulation

The present invention relates to reaction cured glass and glass coatings prepared by reacting a compound selected from the group of substances consisting of silicon tetraboride, silicon hexaboride, other boron silicides, boron and mixtures thereof with a reactive glass frit composed of a porous high silica borosilicate glass and boron oxide. The glassy composites of the present invention are useful as coatings on low density fibrous porous silica insulations used as heat shields and for articles such as reaction vessels that are subjected to high temperatures with rapid heating and cooling and that require resistance to temperature and repeated thermal shock at temperatures up to about 1482.degree. C (2700PF).

Reaction cured glass and glass coatings

A reusable silica surface insulation (RSI) material is provided by bonding amorphous silica fibers with colloidal silica at an elevated temperature. The surface insulation is ordinarily manufactured in the form of blocks (i.e., tiles).

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Saratoga, CA, United States of America

Howard E Goldstein