Abstract: An arrangement of outlet devices for releasing into the atmosphere cryogenic, combustible exhaust vapors in the near-surface, flow-swept, outer area of aircraft, land vehicles and watercraft. The arrangement provides at least one outlet device on the top side of a component at the top end of a pylon, which is favorable in terms of flow, in the free, undisturbed air flow. Each outlet device is arranged, designed and oriented such that the exhaust vapor is released in at least one directed jet oriented to the rear or to the rear and upward, with or without a lateral component, and is kept away from air inlets, hot exhaust gas jets and other sources of ignition, as well as from surfaces of components.

Abstract: Fuel supply system for multijet airplanes using cryogenic fuel with one tank or one tank group for each engine or for all engines on one side of the longitudinal central plane of the airplane, and, if desired, with an additional, common tank or an additional, common tank group for all engines. A transfer line with shut-off valve leads from each tank/tank group associated with a defined engine or with the engines of one side of the airplane to at least one other tank/tank group and/or, if desired, to the tank/tank group common to all engines. If desired, at least one transfer line leads from the common tank/tank group to at least one other tank/tank group.

Abstract: Process for the temperature stratification-free storage of a cryogenic liquid in a thermally insulated tank under gravitation conditions or under gravitation and movement conditions, which generate a liquid volume with a clearly limited, unmoving or only moderately moving liquid level as well as with a gas space located above it in the storage volume of the tank. Liquid is pumped off from the area near the bottom of the tank continuously or at time intervals, it is fed into the area of the gas space, and it is directed vertically or at an acute angle toward the liquid level there in the form of at least one high-energy jet.

Abstract: Cryosystem for cryogenic liquids which contain small amounts of foreign fluids with higher melting and boiling points, wherein the cryosystem comprises at least one tank, pipelines and assembly units and is used under defined gravitation conditions. The pipelines slope, at least in some areas, toward the tank, and areas of the pipelines and assembly units, from which the cryogenic liquid and the foreign fluids cannot flow back into the tank under the action of gravity, are provided with drain openings and drain lines, which open into the tank or into at least one additional collection tank.

Abstract: An ignition system for rocket engine combustion chambers which are operated by non-hypergolic propellant components and particularly for the pre-combustion chambers of main stream engines of this type, comprises a main combustion chamber having injector means for injecting a propellant component into the combustion chamber for combustion therein. Since the propellant components employed are non-hypergolically reactive, they are ignited by an ignition agent which is produced by the pressure of a first propellant component which is non-hypergolically reactive with the ignition agent into the combustion chamber. The second propellant component which reacts with the ignition agent hypergolically is also introduced into the combustion chamber so that ignition takes place immediately.