Abstract: A safety system for aircraft passenger seats is described. A pallet that can be removably coupled to seats can also be removably coupled to the aircraft floor and one or more brackets, tension fittings, or machined straps that can be coupled to structural beams or components in an aircraft. A keel tension fitting can be attached to a keel beam and then be coupled to the pallet and thereby the seats. By attaching to the keel beam the safety system allows the seating arrangement (pallet and seats) to withstand greater stresses and forces, resulting in increased safety.

Abstract: A safety system for aircraft passenger seats is described. A pallet that can be removably coupled to seats can also be removably coupled to the aircraft floor and one or more brackets, tension fittings, or machined straps that can be coupled to structural beams or components in an aircraft. A keel tension fitting can be attached to a keel beam and then be coupled to the pallet and thereby the seats. By attaching to the keel beam the safety system allows the seating arrangement (pallet and seats) to withstand greater stresses and forces, resulting in increased safety.

Abstract: A safety system for aircraft passenger seats is described. A pallet that can be removably coupled to seats can also be removably coupled to the aircraft floor and one or more brackets, tension fittings, or machined straps that can be coupled to structural beams or components in an aircraft. A keel tension fitting can be attached to a keel beam and then be coupled to the pallet and thereby the seats. By attaching to the keel beam the safety system allows the seating arrangement (pallet and seats) to withstand greater stresses and forces, resulting in increased safety.

Abstract: A pressure bulkhead of an aircraft and an associated method of installation are disclosed. The pressure bulkhead comprises an upper bulkhead portion sealingly separating a first pressurized compartment disposed above a floor of the aircraft from an unpressurized zone of the aircraft, and a lower bulkhead portion sealingly separating a second pressurized compartment disposed below the floor of the aircraft from the unpressurized zone of the aircraft. The method of installation can comprise installing the lower bulkhead portion before the upper bulkhead portion in order to facilitate the installation of other components.

Abstract: Techniques and systems to reduce contact of a cable with a top drive. A cable guide may be mounted to one or more bails supporting the top drive and may operate to extend a distance between a cable passing along a length of the top drive. The cable guide may include both an upper guide assembly and a lower guide assembly. Each of the upper guide assembly and the lower guide assembly may both be coupled to one or more bails supporting the top drive in a serial manner.

Abstract: A system of spacecraft radiators comprising pre-formed thermal-transfer modules joined together by at least one solid-state welding process. Critical failure points are eliminated by forming the thermal-transfer modules as a single unitary piece, preferably by an extrusion process. The thermal-transfer modules allow the formation of larger radiator assemblies, which may comprise a wide range of sizes and physical geometries.

Abstract: A system of spacecraft radiators comprising pre-formed thermal-transfer modules joined together by at least one solid-state welding process. Critical failure points are eliminated by forming the thermal-transfer modules as a single unitary piece, preferably by an extrusion process. The thermal-transfer modules allow the formation of larger radiator assemblies, which may comprise a wide range of sizes and physical geometries.

Abstract: Techniques and systems to reduce contact of a cable with a top drive. A cable guide may be mounted to one or more bails supporting the top drive and may operate to extend a distance between a cable passing along a length of the top drive. The cable guide may include both an upper guide assembly and a lower guide assembly. Each of the upper guide assembly and the lower guide assembly may both be coupled to one or more bails supporting the top drive in a serial manner.

Abstract: A system of spacecraft radiators comprising pre-formed thermal-transfer modules joined together by at least one solid-state welding process. Critical failure points are eliminated by forming the thermal-transfer modules as a single unitary piece, preferably by an extrusion process. The thermal-transfer modules allow the formation of larger radiator assemblies, which may comprise a wide range of sizes and physical geometries.

Abstract: A portable thermal-control system adapted to support space-related research and exploration. Embodiments of the present invention assist in preventing overheating of small payloads being transported from an orbiting space vehicle to a planetary surface by small atmospheric-entry vehicles. Other embodiments of the present invention provide thermal control within an extra-vehicular activity (EVA) suit. Each embodiment utilizes at least one phase-change material, cooled significantly below the freezing temperature, to absorb heat.

Abstract: A system of spacecraft radiators comprising pre-formed thermal-transfer modules joined together by at least one solid-state welding process. Critical failure points are eliminated by forming the thermal-transfer modules as a single unitary piece, preferably by an extrusion process. The thermal-transfer modules allow the formation of larger radiator assemblies, which may comprise a wide range of sizes and physical geometries.

Abstract: A system of spacecraft radiators comprising pre-formed thermal-transfer modules joined together by at least one solid-state welding process. Critical failure points are eliminated by forming the thermal-transfer modules as a single unitary piece, preferably by an extrusion process. The thermal-transfer modules allow the formation of larger radiator assemblies, which may comprise a wide range of sizes and physical geometries.

Abstract: A portable thermal-control system adapted to support space-related research and exploration. Embodiments of the present invention assist in preventing overheating of small payloads being transported from an orbiting space vehicle to a planetary surface by small atmospheric-entry vehicles. Other embodiments of the present invention provide thermal control within an extra-vehicular activity (EVA) suit. Each embodiment utilizes at least one phase-change material, cooled significantly below the freezing temperature, to absorb heat.

Abstract: A system of spacecraft radiators comprising pre-formed thermal-transfer modules joined together by at least one solid-state welding process. Critical failure points are eliminated by forming the thermal-transfer modules as a single unitary piece, preferably by an extrusion process. The thermal-transfer modules allow the formation of larger radiator assemblies, which may comprise a wide range of sizes and physical geometries.