Lockheed Martin Corporation

Janine M Thornton

William H Willcockson

Suraj Prakash Rawal

Daniel R Morgenthaler

Edward Nathan Harris

Kenneth P Romeo

Michael A Sasdelli

Michael G Thornton

The present invention discloses an insulated reentry heat shield for minimizing heat transfer to a spacecraft structure or the like during atmospheric reentry. The heat shield ( ) comprises an outer heat resistant layer ( ) including an ablative first material backed by an inner insulating layer ( ) including an insulating second material. The outer and inner layers ( ) are bonded to one another by a middle layer ( ) disposed therebetween. The middle layer is formed by disposing at least one layer of a phenolic loaded third material between the outer and inner layers and heating all three layers simultaneously to remove phenolic volatiles from the middle layer. In one embodiment, the ablative first material is carbon-carbon, the insulating second material is carbon foam, and the phenolic loaded third material is carbon scrim cloth. The present invention also discloses a method for use in constructing a heat shield. The method includes the steps of preparing an outer heat resistant layer comprised of an ablative first material and attaching the outer heat resistant layer to an inner insulating layer comprised of an insulating second material. The outer heat resistant layer is attached to the inner insulating by disposing at least one layer of a phenolic loaded scrim cloth or felt material between the outer heat resistant layer and the inner insulating layer and heating the outer heat resistant layer, the layer(s) of phenolic loaded scrim cloth or felt material, and the inner insulating layer simultaneously to remove phenolic volatiles from the scrim cloth or felt material.

Insulated reentry heat shield

An integrated sample return capsule for use in returning materials to Earth from space, such as core samples from other celestial bodies and experiments from orbiting platforms. The sample return capsule incorporates thermal protection, structural integrity and impact mitigation into a single system capable of safely and securely returning the materials without requiring decelerating parachutes. In one embodiment, the integrated sample return capsule includes a forward facing heat shield and a back shell attached to the rear of the heat shield. The heat shield and the back shell define an interior enclosure. The back shell includes an access, such as a door or a removable panel, there through to the interior enclosure. Materials to be returned may be sealed in a sample containment vault, and the sealed vault may be placed into the interior enclosure through the access. An optional support deck may be provided within the interior enclosure for receiving the sample containment vault and supporting the vault within the interior enclosure.

Integrated sample return capsule

The invention is a material for use in an inflatable aerodynamic braking device for a spacecraft. In detail, the invention includes a plurality of high temperature resistant barrier outer layers. Preferably, the outer layer is made of Aluminoborosilicate fabric. At least one carbon cloth layer is disposed behind said outer layers. A plurality of thermal radiation barrier intermediate layers are disposed behind the at least one carbon cloth layer. The intermediate layers include a plurality of metal foil layers, at least one additional carbon cloth layer interspersed between the metal foil layers. A plurality of metal-coated polymeric layers are disposed behind the metal foil layers, preferably a polyimide fabric coated with Aluminum. The metal foil layers are Aluminum and Titanium. At least one inflatable gas barrier interior layer is disposed behind the intermediate layers, preferably made of a polyimide material. The outer, intermediate and interior layers are sewn together by high temperature resistant thread, preferably Silicon Carbide thread.

Material assembly for an inflatable aerodynamic braking device for spacecraft deceleration and the like

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Elizabeth, CO, United States of America

Janine M Thornton