The invention relates to a fluid compression apparatus comprising a housing having a compression chamber, an intake system communicating with the compression chamber which is configured to allow fluid to be compressed into said compression chamber, and a mobile piston for ensuring the compression of the fluid in the compression chamber. The apparatus further comprises a discharge port which is configured to allow the exit of compressed fluid from the compression chamber, the compression chamber being defined by a portion of the body of the piston and a fixed wall of the apparatus, the piston being translationally mobile along a longitudinal direction. The invention is characterized in that the piston has a tubular portion mounted around a fixed central guide, a first terminal end of the central guide forming the fixed wall delimiting a part of the compression chamber. The apparatus also comprises a sealing system formed between the central guide and the piston according to the longitudinal direction of translation of the piston, the intake system being located at a first end of the apparatus, the discharge port being located at a second end of the apparatus.

Aircraft fuel system including a fuel vessel containing a non-mixture fuel. A protective vessel is arranged about the fuel vessel such that the fuel vessel is contained within the protective vessel and a protective space is defined between an outer surface of a vessel wall of the fuel vessel and an inner surface of a vessel wall of the protective vessel. At least one mounting structure fixedly positions the fuel vessel within the protective vessel. A fuel consumption device configured to consume the non-mixture fuel. A fuel output fluidly connects an interior of the fuel vessel to the fuel consumption device, the fuel output being fluidly isolated from the protective space. A relief output fluidly connects the protective space to a relief flow path, the relief output and relief flow path configured to vent gas from the protective space and remove any non-mixture fuel from the protective space.

Aircraft fuel system including a fuel vessel containing a non-mixture fuel. A protective vessel is arranged about the fuel vessel such that the fuel vessel is contained within the protective vessel and a protective space is defined between an outer surface of a vessel wall of the fuel vessel and an inner surface of a vessel wall of the protective vessel. At least one mounting structure fixedly positions the fuel vessel within the protective vessel. A fuel consumption device configured to consume the non-mixture fuel. A fuel output fluidly connects an interior of the fuel vessel to the fuel consumption device, the fuel output being fluidly isolated from the protective space. A relief output fluidly connects the protective space to a relief flow path, the relief output and relief flow path configured to vent gas from the protective space and remove any non-mixture fuel from the protective space.

A system and a method for liquefied fuel storage are provided. The system includes a first module including a first outer vessel wall and a cryotank, a second module including a second outer vessel wall and a submerged pump at partially inside the second outer vessel wall, and a third module including a third outer vessel wall. The first, the second, and the third outer vessel walls are connected to provide an enclosure as an outer vessel.

A system and a method for liquefied fuel storage are provided. The system includes a first module including a first outer vessel wall and a cryotank, a second module including a second outer vessel wall and a submerged pump at partially inside the second outer vessel wall, and a third module including a third outer vessel wall. The first, the second, and the third outer vessel walls are connected to provide an enclosure as an outer vessel.

A tube-array-type liquid nitrogen container includes a container body having a mouth; a tube array component received in the container body; and a top cap sealing the mouth from above. The top cap is rotatable in the mouth. The tube array component is composed of a plurality of holding tubes. The holding tube is opened at one end thereof, wherein the opening thereof faces the top cap. The top cap has at least one tube access passing therethrough. Each tube access is atop covered by a tube access cover. The tube-array-type liquid nitrogen container uses a tube-array component composed of the a plurality of holding tubes to store the freezing tubes, and is cooperated with the rotatable top cap and an external robotic arm, thereby improving space utilization and thermal insulation, effectively ensuring safety of the freezing tubes, and facilitating automatic storage of freezing tubes.

A tube-array-type liquid nitrogen container includes a container body having a mouth; a tube array component received in the container body; and a top cap sealing the mouth from above. The top cap is rotatable in the mouth. The tube array component is composed of a plurality of holding tubes. The holding tube is opened at one end thereof, wherein the opening thereof faces the top cap. The top cap has at least one tube access passing therethrough. Each tube access is atop covered by a tube access cover. The tube-array-type liquid nitrogen container uses a tube-array component composed of the a plurality of holding tubes to store the freezing tubes, and is cooperated with the rotatable top cap and an external robotic arm, thereby improving space utilization and thermal insulation, effectively ensuring safety of the freezing tubes, and facilitating automatic storage of freezing tubes.

A readily combustible portion (110) includes a readily combustible exposed surface (111) that is exposed to a flow channel (CA). A combustion-resistant portion (140), which comprises a material that is more resistant to combustion than the readily combustible portion (110), covers an outer surface of the readily combustible portion (110) on the opposite side from the readily combustible exposed surface (111) in a direction orthogonal to a length direction parallel to a direction in which a hybrid rocket is propelled. The combustion-resistant portion (140) includes a thick portion (120) that serves as a stopper that prevents peeling of the readily combustible portion (110) from the combustion-resistant portion (140) in a direction from a starting end surface (100a) toward a terminating end surface (100b).

An engine-driven cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for condensing a chilled air stream into liquid air for an aircraft use. The first air cycle machine includes a plurality of components operably coupled to a gearbox of a gas turbine engine and configured to produce a cooling air stream based on a first engine bleed source of the gas turbine engine. The second air cycle machine is operable to output the chilled air stream at a cryogenic temperature based on a second engine bleed source cooled by the cooling air stream of the first air cycle machine.

An engine-driven cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for condensing a chilled air stream into liquid air for an aircraft use. The first air cycle machine includes a plurality of components operably coupled to a gearbox of a gas turbine engine and configured to produce a cooling air stream based on a first engine bleed source of the gas turbine engine. The second air cycle machine is operable to output the chilled air stream at a cryogenic temperature based on a second engine bleed source cooled by the cooling air stream of the first air cycle machine.