Blue Origin, LLC

John Paul Brendel

Adam Keith Norman

Christopher Patrick Hupf

Stefano Gulli

Chris Hupf

Sean Lay

Pierce Louderback

A high temperature thermal protection systems for rockets, and associated methods, is disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end. The launch vehicle is elongated along a vehicle axis extending between the first and second ends and carries a propulsion system having at least one nozzle positioned at the second end of the launch vehicle. A thermal protection apparatus positioned around the nozzle is used to provide cooling and/or insulation to the nozzle during the flight of the launch vehicle. The thermal protection apparatus can include multiple fabric layers and an insulation layer stacked and stitched together. The fabric layers can include metal alloy fibers. In representative systems, the thermal protection apparatus can further include provisions for water that saturates the insulation layer to provide further insulating and/or cooling effects.

High temperature thermal protection system for rockets, and associated methods

Embodiments disclosed herein include fastener assemblies. In an embodiment, a fastener assembly comprises a sleeve with a hole, an inner surface, and top and bottom ends. The top end has a planar surface, and the inner surface has a cylindrical surface. The fastener assembly includes a fastener downwardly extending through the hole, and having a drive slot, a head, a shank, and a threaded region. The head is positioned within the bottom end. The head is separated from the threaded region by the shank. The fastener assembly comprises a cover disposed on the top end and having an access hole and top and bottom surfaces. The cover is welded to the sleeve to define an inner cavity between the cover, sleeve, and fastener head. The access hole is positioned over the drive slot. The cover, sleeve, and fastener comprises materials having high temperature, strength and oxidation resistances.

Quick-access fastener assembly for high temperature applications

A metal encapsulated ceramic tile thermal insulation system for rockets and associated methods is disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end and includes a heat shield positioned at the second end. The heat shield includes a plurality of thermal protection apparatuses, where individual of the thermal protection apparatuses include ceramic tiles encapsulated by inner and outer metal layers, which are positioned on opposing top and bottom surfaces of the ceramic tiles. The plurality of thermal protection apparatuses includes a plurality of pins positioned within corresponding holes drilled through the ceramic tiles and are secured to the metal layers. The outer metal layer can protect the ceramic tile from tool strikes and debris and can also prevent water from reaching and being absorbed by the ceramic tile.

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Kent, WA, United States of America

John Paul Brendel