Abstract: A process for the production of a transverse thrust in a flying object in which a defined quantity of a monergol propellent substance is introduced into a propulsion unit, which is arranged transversely relative to a longitudinal axis of the flying object to produce a thrust transverse to the longitudinal axis of the flying object. The propulsion unit has a combustion chamber, a supersonic nozzle connected to the combustion chamber and a source of heat to combust the propellant substance and produce the desired thrust for a prescribed time.

Abstract: A process for the production of a transverse thrust in a flying object in which a defined quantity of a monergol propellent substance is introduced into a propulsion unit, which is arranged transversely relative to a longitudinal axis of the flying object to produce a thrust transverse to the longitudinal axis of the flying object. The propulsion unit has a combustion chamber, a supersonic nozzle connected to the combustion chamber and a source of heat to combust the propellant substance and produce the desired thrust for a prescribed time.

Abstract: Thrust-generating device with rocket engines arranged in pairs opposite each other for multiple ignition as well as individual and group activation and with an amount of fuel sufficient for the duration of the mission. The thrust-generating device is designed as a closed, storable, modular unit. The rocket engines are operated with liquid fuel and liquid oxidizing agent. At least one tank is provided for each fuel component. The tanks are in the filled, pressureless state before the activation of the thrust-generating device. The rocket engines and a fuel distributor of block design are integrated within a central bulkhead. The thrust-generating device is surrounded by a sealed outer jacket and is divided by the bulkhead into two separate chambers. The outer jacket is lined on the inside with a "self-sealing" film. The oxidizing agent is stored in one chamber, and the fuel in the other chamber. The empty spaces in the chambers contain an adsorbent filling.

Abstract: In an apparatus for generating a propellant gas, such as is used in propeng projectiles, at least one rotation chamber acts as a propellant gas generator containing a ring-shaped flow of propellant. A closed circuit is connected to the chamber for circulating a liquid propellant to it. Either monergolic or hypergolic propellants can be used with the rotation chamber being formed of at least two sub-chambers when hypergolic propellants are used. The two sub-chambers are connected by an overflow weir. The closed circuit which is provided for each of the chambers involved in the generation of the propellant gas, includes a valve for regulating the quantity of propellant disposed in a ring-shaped flow within the chamber. The valve regulates the amount of propellant required for the gas-generating operation.

Abstract: A method and apparatus for making holes in coal seams in a coal mining system in which hot working gas is employed to impinge on the coal under high pressure and speed in order to disintegrate it and particularly for making inclined or horizontal holes which connect vertical drill holes which lead from the surface to the coal seam and through which the medium for gasifying the coal underground is blown in. The vertical drill holes which lead from the coal seam to the surface are used for blowing out gasification gases which are produced by the operation as well as for delivering the hot working gas. With the method of the invention, a gasification medium of high temperature and pressure is advantageously produced directly at the locations where the disintegrated coal is gasified, the disintegrated coal being formed by a rocket combustion process.

Abstract: A method and apparatus for making holes in coal seams in a coal mining system in which hot working gas is employed to impinge on the coal under high pressure and speed in order to disintegrate it and particularly for making inclined or horizontal holes which connect vertical drill holes which lead from the surface to the coal seam and through which the medium for gasifying the coal underground is blown in. The vertical drill holes which lead from the coal seam to the surface are used for blowing out gasification gases which are produced by the operation as well as for delivering the hot working gas. With the method of the invention, a gasification medium of high temperature and pressure is advantageously produced directly at the locations where the disintegrated coal is gasified, the disintegrated coal being formed by a rocket combustion process.

Abstract: A method of producing an underground cavity in a driving shield advance operation comprises, prior to excavation, forming an annular slot corresponding to the contour and wall thickness of the shield ahead of the shield by using hot gas jets to form the slot and to separate a core from the surrounding rock formation, advancing the shield into the annular slot, and breaking out the core under the protection of the shield. The device for producing the underground cavity comprises a tubular drive shield adapted to be advanced into the cavity and having an interior support wall on which is rotatably supported a support member having an arm carrying a gas jet lance. The gas jet lance advantageously includes at least one gas nozzle directed forwardly to form an inwardly extending cavity ahead of the shield, and one or more nozzle discharges directing the gas laterally.

Abstract: A method of producing fractures or gaps in geological formations of crystalline rocks in order to utilize the heat of the earth surrounding the gaps, comprises, drilling at least one bore into the rock, producing a pressure fluid in the bore adjacent the rock by introducing pressure gas-producing propellants into the bores to a location within the rock formation and reacting the pellants after they have been sealed off from the top of the bore and discharging the fluid pressure into the bore to put the rock under a pressure above its breaking limit so as to produce a large surface gap. The apparatus advantageously comprises a pressure gas generator which operates from a monergolic propellant which is decomposed catalytically and which includes a sealing bellows arranged around a reaction chamber at the bottom of the bore which is sealed at the upper end or to the rear and is connected with the pressure gas chamber and an outlet into the forming gap having a non-return valve therein.

Abstract: A device for extracting crude oil out of an extraction bore of a previously tapped deposit, comprises, a combustion chamber having at least one reaction chamber portion and an evaporation chamber portion arranged in axial relationship with a constricted nozzle portion therebetween. Advantageously, an additional constricted nozzle portion separates a turbulence chamber from a front reaction chamber and the second constriction separates the front reaction chamber from a rear evaporation chamber. The evaporation chamber in turn feeds through a nozzle section to a narrow discharge into the extraction bore. A fuel and chemical oxygen or an oxygen carrier are directed into the combustion chamber preferably in front of the first constriction and forms high temperature combustion gases into which the water is directed in a manner to intermix the water with the combustion gases and to form superheated steam which is then discharged into the extraction bore.

Abstract: A thermal drilling device which operates in a rotary or circumferentially oscillatory motion and which is particularly adapted for drilling geological formations comprises a drill body which has an interior combustion chamber with a bottom having an outlet defining a discharge nozzle. Means are provided for adding fuel components into the combustion chamber and for igniting them to generate hot gaseous products of combustion which are discharged through a nozzle slot arranged at the bottom of the combustion chamber. The nozzle slot extends diametrically of the drilling area at the bottom and slot outline or a plurality of slots arranged symmetrically relative to the longitudinal axis of the drilling body.

Abstract: A propelling or driving force generating system for propelling a device such as projectile in a fire arm comprises a combustion chamber cylinder formed at the end of a barrel containing a bore for the passage of a projectile and in which is movable in pressure differential piston. The piston includes an annular ring portion having surfaces on respectively axially opposite ends which are exposed to pressure forces existing in intermediate chambers defined between these surfaces and end walls of the surrounding cylinder in widened annular portions of the cylinder. The cylinder and piston are provided with one or more passages for the passage of a propellant component into the combustion chamber. The various propellant components which are preferably of a nature such that they will react hypergolically, are connected through valve means in these passages and by a central plunger element of said valve means into the combustion chamber.

Abstract: A thermal drilling device which operates in a rotary or circumferentially oscillatory motion and which is particularly adapted for drilling geological formations comprises a drill body which has an interior combustion chamber with a bottom having an outlet defining a discharge nozzle. Means are provided for adding fuel components into the combustion chamber and for igniting them to generate hot gaseous products of combustion which are discharged through a nozzle slot arranged at the bottom of the combustion chamber. The nozzle slot extends diametrically of the drilling area at the bottom and slot outline or a plurality of slots arranged symmetrically relative to the longitudinal axis of the drilling body. In one embodiment the nozzle slot has a radially extending portion with the circumferential width of the slot increasing in a radial outward direction.

Abstract: An arrangement for producing rotational energy, particularly for generating thrust gases in rocket combustion chambers using hypergolically reacting propellants, comprises a rocket combustion chamber having a closed end and a gas discharge end with an impeller mounted in the closed end. The impeller has a plurality of spaced vanes which extend radially and which define flow ducts therebetween having discharge ends which extend substantially tangential to the combustion periphery. The apparatus includes means for directing hypergolically reacting propellant components into the combustion chamber at a location in which they are deposited at the inner radial ends of the flow ducts. The oxygen carrier propellant is supplied radially inside of the other propellant component so that it forms a cooling veil along the impeller.