A method for measuring a three-dimensional temperature field of a liquid in a receptacle, in particular of cryogenic liquids, wherein a local liquid density is determined by means of electrical capacitance tomography and the local temperature is derived based on the local liquid density and a local liquid pressure, and an apparatus for carrying out such a method.
The invention relates to a rocket engine (100, 200, 300, 400) comprising a first tank (102) and a second tank (106), wherein the first tank is filled with a fuel and the second tank with an oxidising agent, such as liquid hydrogen peroxide, for feeding at least one main engine (120) of the rocket engine, which main engine can preferably be repeatedly ignited. A gas generator (140) is assigned to the rocket engine and is designed to produce vaporous hydrogen peroxide. After flowing through at least one turbine, the hydrogen peroxide can be at least partially supplied to a separator unit (160) which is designed to break down vaporous hydrogen peroxide into steam and gaseous oxygen. Alternatively or in addition, the hydrogen peroxide can be supplied to an electrolysis unit (302, 402) which is designed to generate gaseous oxygen and gaseous hydrogen from the hydrogen peroxide supplied to it and/or the steam downstream of it. The invention also relates to a method for operating the rocket engine and to a spacecraft.
F02K 9/42 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid or gaseous propellants
F02K 9/48 - Feeding propellants using pumps driven by a gas turbine fed by propellant combustion gases
F02K 9/88 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by thrust or thrust vector control using auxiliary rocket nozzles
A seat system for use in a crew escape system of a space transport vehicle comprises a seat having a backrest with a supporting surface. The seat is configured to be installed in a cabin area of the crew escape system so it can rotate about a first axis between a first position where the seat faces a first direction, and a second position where faces a second direction that is opposed to the first direction. The seat system further comprises a control unit configured to control a rotation of the seat at least between the first position and the second position in dependence on at least one signal which is indicative of a trajectory of the crew escape system.
A seat system (10) for use in a crew escape system (500) of a space transport vehicle (1000) comprises a seat (12) having a backrest (14) with a supporting surface (16) which, when the seat (12) is used by a crew member (106), is suitable to support an upper body of the crew member (106), and being configured to be installed in a cabin area (100) of the crew escape system (500) so as to be rotatable about a first axis (R1) at least between a first position, wherein the supporting surface (16) of the backrest (14) faces a first direction (D1), and a second position, wherein the supporting surface (16) of the backrest (14) faces a second direction (D2), the second direction (D2) being opposed to the first direction (D1). The seat system (10) further comprises a control unit (25) which is configured to control a rotation of the seat (12) at least between the first position and the second position in dependence on at least one signal which is indicative of a trajectory of the crew escape system (500).
B64G 1/52 - Protection, safety or emergency devicesSurvival aids
B60N 2/14 - Seats specially adapted for vehiclesArrangement or mounting of seats in vehicles the seat or part thereof being movable, e.g. adjustable the whole seat being movable rotatable, e.g. to permit easy access
A connection system for a cryogenic tank with a tank wall formed with a first material. A connector is provided for a component to be connected to the tank. The connector is formed with a second material, and the connector is positioned on an exterior side of the tank and essentially congruent with a passage opening of the tank wall. At least one sealing element is provided, and the first and the second material have different thermal expansion coefficients. A counterpart formed with the second material is positioned on an interior side of the tank, and is connected with the connector via at least two fastening elements, such that the tank wall is clamped between the counterpart, the connector and the at least one sealing element, and a slight displaceability of the connector and the counterpart parallel to the tank wall remains to compensate for thermally induced mechanical stresses.
The invention relates to a connection system (100) for a cryogenic tank (102), the tank wall (104) of which is formed with a first material (106), wherein the connection system (100) has a connector (110) for a component (116) to be connected to the tank (102), and wherein the connector (110) is formed with a second material (120), and the connector (110) is positioned on an exterior side of the tank (124) and essentially congruent with a passage opening (126) of the tank wall (104), and wherein at least one sealing element (130) is provided, and the first and the second material (106, 120) have different thermal expansion coefficients (a1,2). The invention provides that a counterpart (140) formed with the second material (120) be positioned on an interior side of the tank (136), and can be connected with the connector (110) with the help of at least two fastening elements (146, 148), such that the tank wall (104) is clamped between the counterpart (140), the connector (110) and the at least one sealing element (130), and a slight displaceability of the connector (110) and the counterpart (140) parallel to the tank wall (104) remains in order to compensate for thermally induced mechanical stresses. The connector (110) and counterpart (140) are materially uniform, which results in identical thermal shrinkage and expansion rates in the case of high temperature fluctuations within a range of 200 C, both of which prevent transverse forces acting on the fastening elements (146, 148) from arising.
A part of a spacecraft, for instance an upper stage, is configured to re-enter into the atmosphere and to be reused for several missions. The part is equipped with a reusable kit comprising non-ablative heat shields, for example constructed with an outer surface formed of Ceramic Matrix Composites, such as Ultra High Temperature Ceramic Matrix Composites, and optionally at least one decelerator and/or at least one parachute and/or parafoil system.
A hydrogen tank having a tank structure at least partially delimiting a tank space and comprising a cooling shield formed in a lightweight construction. A conduit system, connected to the tank space, of a pressure relief system for discharging gaseous hydrogen from the tank space is formed in the cooling shield. At least one para-ortho catalyst for accelerated conversion of parahydrogen into orthohydrogen is arranged in the conduit system. A vehicle is provided having a hydrogen drive and such a hydrogen tank. A method for cooling the tank structure of such a hydrogen tank is provided.
F17C 1/16 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of plastics materials
F17C 1/14 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of aluminiumPressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of non-magnetic steel
9.
SPACECRAFT TANK WITH HEAT EXCHANGER, SPACECRAFT AND METHOD FOR COOLING THE CONTENTS OF A TANK
A spacecraft tank 100 for hydrogen is disclosed. The spacecraft tank 100 has a pressure relief system 20 for discharging gaseous hydrogen Wg from a tank chamber T which comprises a heat exchanger 21 at least a section of which protrudes into the tank chamber T and which has a para-ortho catalyst for the accelerated conversion of parahydrogen into orthohydrogen. A spacecraft with a hydrogen drive and a spacecraft 100 of this type are also disclosed. A method is also disclosed for cooling the contents of a tank with liquid hydrogen Wf and gaseous hydrogen Wg in a tank chamber T of a spacecraft tank 100 which comprises a pressure relief system 20 with a heat exchanger 21 at least a section of which protrudes into the tank chamber T and which has a para-ortho catalyst for the accelerated conversion of parahydrogen into orthohydrogen. The method comprises a conversion of parahydrogen into orthohydrogen by means of the heat exchanger 21 as well as a discharge of at least a portion of a hydrogen mixture produced by the conversion.
Disclosed is a hydrogen tank 100 having a tank structure 10 at least partially delimiting a tank space T and comprising a cooling shield 11 formed in a lightweight construction. A conduit system 21, connected to the tank space T, of a pressure relief system 20 for discharging gaseous hydrogen Wg from the tank space T is formed in the cooling shield 11. At least one para-ortho catalyst for accelerated conversion of parahydrogen into orthohydrogen is arranged in the conduit system. Further disclosed are a vehicle having a hydrogen drive and such a hydrogen tank 100 as well as a method for cooling the tank structure of such a hydrogen tank.
A rocket engine section includes a combustion chamber body having an inner wall and a channel carrying a cooling medium extending outside and along the inner wall. The rocket engine section further comprises a porous portion integrally formed with the inner wall and integral with the inner wall and adapted to allow the cooling medium carried in the channel to pass from the channel to the interior of the combustion chamber body. A porosity of the porous portion determines a volume flow rate and/or mass flow rate of the cooling medium let through into the interior of the combustion chamber body.
The invention discloses an ocean current power plant 1 with an electric generator 22 and a turbine, which comprises a stator 30 and a rotor 10 that is rotatable about the stator, for driving the electric generator 22. The rotor comprises a plurality of rotor arms 11, which respectively have a carrier mechanism 12 and multiple rotor blades 14 that are pivotably mounted on the carrier mechanism.
F03B 13/22 - Adaptations of machines or engines for special useCombinations of machines or engines with driving or driven apparatusPower stations or aggregates characterised by using wave or tide energy using wave energy using the flow of water resulting from wave movements, e.g. to drive a hydraulic motor or turbine
F03B 17/06 - Other machines or engines using liquid flow, e.g. of swinging-flap type
F03G 7/00 - Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for
H02K 1/22 - Rotating parts of the magnetic circuit
H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
13.
Rocket combustion chamber wall having cooling channels and method for making thereof
A combustion chamber suitable in particular for use in an engine comprises a combustion space, a combustion space wall delimiting the combustion space, and a plurality of cooling channel webs extending from a surface of the combustion space wall which faces away from the combustion space and separating mutually adjacent cooling channels from one another. The cooling channel webs are each provided with a projection extending from an end face of the cooling channel webs which faces away from the combustion space. Furthermore, the combustion chamber comprises a plurality of cover elements, wherein each cover element extends along a longitudinal axis of a cooling channel delimited by two mutually adjacent cooling channel webs between the projections of the mutually adjacent cooling channel webs and is form-fittingly connected to the projections of the two mutually adjacent cooling channel webs in order to cover the cooling channel.
A rocket propulsion system comprising a first cryogenic tank and a second cryogenic tank, wherein the first cryogenic tank is filled with a first propellant, and the second cryogenic tank is filled with a second propellant, for purposes of feeding at least one repeatedly ignitable main propulsion unit in a propulsion phase of the rocket propulsion system. For purposes of tank pressurization via at least a low level of acceleration in a ballistic phase, a first auxiliary propulsion unit can be operated by means of a first gas pressure accumulator, and at least one further auxiliary propulsion unit can be operated by means of a further gas pressure accumulator, and the rocket propulsion system is assigned an energy conversion unit, which is designed at least to charge the first and the second gas pressure accumulator, preferably in the ballistic phase.
H01M 8/0656 - Combination of fuel cells with means for production of reactants or for treatment of residues with means for production of gaseous reactants by electrochemical means
15.
CARRIER ROCKET SYSTEM WITH CARRIER ROCKET AND LAUNCH ASSISTANCE UNIT
A carrier rocket system, with a carrier rocket, together with a launch assistance unit, which is detachably connected, or connectable, to the carrier rocket. The carrier rocket system is set up to take off in a horizontal launch via the launch assistance unit when thrust is generated by at least one propulsion unit of the carrier rocket. The launch assistance unit can be detached from the onward-flying carrier rocket after supersonic velocity has been reached, and is set up to fly back to the earth's surface after its detachment from the carrier rocket. The launch assistance unit preferably provides all the necessary structural supports to enable a carrier rocket that has been designed for a vertical launch to use one or more of its essential components without structural modifications. Also disclosed are a take-off method for a carrier rocket system, and a manufacturing method for a carrier rocket system.
A combustion chamber section for a combustion chamber for a rocket engine, the combustion chamber section including a combustion chamber body enclosing a combustion chamber volume and having coolant channels disposed therein, and at least one baffle integrally formed with the combustion chamber body and projecting from the combustion chamber body into the interior of the combustion chamber. The at least one baffle includes at least one coolant channel fluidly connected to at least one of the coolant channels in the combustion chamber body. Furthermore, an additive layer manufacturing method for manufacturing such a combustion chamber section is described.
A combustion chamber for a rocket engine, the combustion chamber including a combustion chamber body enclosing a combustion chamber volume and a nozzle portion tapering in a longitudinal direction of the combustion chamber and adjoining the combustion chamber body. The combustion chamber body has at least one first portion and a second portion, wherein an inner surface of the at least one first portion facing the combustion chamber volume is closer to a cross-sectional center of the combustion chamber body than an inner surface of the second portion of the combustion chamber body. Furthermore, a additive layer manufacturing method for manufacturing such a combustion chamber is described.
The invention relates to a mounting assembly with a spherical bearing for mounting a rocket engine and a rocket having such mounting assembly. The spherical bearing includes a spherical bearing base, a spherical retaining ring and a suspension link with a spherical end arranged in a space between the spherical bearing base and the spherical retaining ring. The spherical bearing base is part of an injector head of the rocket engine or is part of a fuel tank, the parts having a spherical shape.
F02K 9/60 - Constructional partsDetails not otherwise provided for
F16M 11/12 - Means for attachment of apparatusMeans allowing adjustment of the apparatus relatively to the stand allowing pivoting in more than one direction
A tank for the storage of liquid or gaseous substances with a fiber-reinforced plastic sheathing, which limits at least one interior space for holding the materials to be stored. At least one circumferential section of the fiber-reinforced plastic sheathing comprises an evacuable sandwich structure, which completely encloses the circumferential section. As a result, the tank has a low weight with a high thermal insulation capacity. Furthermore, a reliable explosion protection of the tank is provided. Furthermore, a method for manufacturing a tank for the storage of liquid or gaseous substances is provided.
B65D 81/38 - Containers, packaging elements, or packages, for contents presenting particular transport or storage problems, or adapted to be used for non-packaging purposes after removal of contents with thermal insulation
An insulation material for thermal and/or acoustic insulation. The insulation material comprises a plurality of layered sheets, including one or more flexible polyimide aerogel film/s being at least partially covered with a reflective coating on one or both of its surfaces. A method is provided for thermally and/or acoustically insulating an entity. The method comprises at least partially shielding, covering and/or enveloping the entity with an insulation material comprising comprises a plurality of layered sheets, including one or more flexible polyimide aerogel film/s being at least partially covered with a reflective coating on one or both of its surfaces.
G10K 11/168 - Plural layers of different materials, e.g. sandwiches
B32B 27/28 - Layered products essentially comprising synthetic resin comprising copolymers of synthetic resins not wholly covered by any one of the following subgroups
B32B 27/08 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of synthetic resin of a different kind
B32B 3/26 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids
21.
INSULATION MATERIAL FOR THERMAL AND/OR ACOUSTIC INSULATION
Disclosed is an insulation material (10, 10', 10", 10"') for thermal and/or acoustic insulation. The insulation material comprises a plurality of layered sheets (1, 2, 3, 4, 5, 6, 7, 8), including one or more flexible polyimide aerogel film/s being at least partially covered with a reflective coating (2a, 2b, 4a, 4b, 6a, 6b, 7a, 7b) on one or both of its surfaces. Further disclosed is a method for thermally and/or acoustically insulating an entity. The method comprises at least partially shielding, covering and/or enveloping the entity with an insulation material (10, 10', 10", 10"') according to an embodiment of the present invention.
B32B 5/18 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by features of a layer containing foamed or specifically porous material
B32B 27/28 - Layered products essentially comprising synthetic resin comprising copolymers of synthetic resins not wholly covered by any one of the following subgroups
A combustion chamber structure for a rocket engine includes a hot gas wall (12) that surrounds a combustion chamber (40) and has a plurality of first coolant channels (50) and a plurality of second coolant channels (52). The plurality of first (50) and second (52) coolant channels extend from a first longitudinal end (16) of the hot gas wall (12) to a second longitudinal end (18) of the hot gas wall (12) opposite to the first longitudinal end (16). The combustion chamber structure (10) further comprises a first manifold (20) forming a first coolant chamber (30) and a second manifold (22) forming a second coolant chamber (32) being fluidly separated from the first coolant chamber (30). The first (20) and second (22) manifolds are provided at the first longitudinal end (16) of the hot gas wall (12) and extend in a circumferential direction of the hot gas wall (12). The first coolant chamber (30) is fluidly connected to each of the plurality of first coolant channels (50) and the second coolant chamber (32) is fluidly connected to each of the plurality of second coolant channels (52).
A guide vane arrangement configured for use in a turbo pump, wherein the guide vane arrangement includes a first guide vane and a second guide vane, wherein the second guide vane is arranged adjacent to the first guide vane such that a flow channel is defined between a leading surface of the first guide vane and a trailing surface of the second guide vane. The trailing surface of the second guide vane comprises a trailing portion which is arranged adjacent to a trailing edge of the second guide vane and which is arranged at a first angle with respect to a virtual plane defined by a trailing edge of the first guide vane and the trailing edge of the second guide vane, a leading portion which is arranged adjacent to a leading edge of the second guide vane and which is arranged at a second angle with respect to the virtual plane defined by the trailing edge of the first guide vane and the trailing edge of the second guide vane, the second angle being larger than the first angle, and an intermediate portion which is arranged between the trailing portion and the leading portion and which is arranged at a third angle with respect to the virtual plane defined by the trailing edge of the first guide vane and the trailing edge of the second guide vane, the third angle being smaller than the first angle.
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
19 - Non-metallic building materials
20 - Furniture and decorative products
Goods & Services
Rocket engines for space vehicles Satellites Propulsion system for space vehicles; apparatus for locomotion by land, water, air and space, namely, land rovers for space exploration, airborne platforms for serving spacecrafts and conducting space applications, and structural parts and structural fittings for all of the aforementioned goods; motors for space vehicles for locomotion by land, water, air and space, namely, motors for lunar rovers, space shuttles and rockets and structural parts and structural fittings for all the aforementioned goods; space vehicles, namely, space launch vehicle in the nature of self-propelled rockets; spacecraft; space carrier system for space transportation comprised of an orbiter space shuttle and space vehicle for space exploration Rocket launching platforms, not of metal; liquid storage tanks of masonry for cryogenic liquids for use in space travel; liquid storage tanks of masonry for hydrogen and oxygen for use in space Plastic and plastic composite material storage tanks for cryogenic liquids not of metal; plastic and plastic composite material storage containers for liquid hydrogen and oxygen liquids not of metal
25.
Launch vehicle with solar cells, manufacturing method and transport method
A launch vehicle to transport at least one payload into an earth orbit, wherein the launch vehicle comprises a plurality of solar cells on its outer surface. Furthermore, a manufacturing method for a launch vehicle with a plurality of solar cells on its outer surface and a transport method for at least one payload using a launch vehicle with a plurality of solar cells on its outer surface are provided.
H02S 40/36 - Electrical components characterised by special electrical interconnection means between two or more PV modules, e.g. electrical module-to-module connection
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
20 - Furniture and decorative products
Goods & Services
Propulsion system for space vehicles. Satellite. Apparatus for locomotion by, land, water, air and space; Motors for apparatus for locomotion by land, water, air and space and parts therefor; Space launch vehicle; Rocket stage; Spacecraft; Carrier system for space transportation; Orbiter; Vehicle for space exploration. Storage for cryogenic liquids not of metal; Storage for liquid hydrogen and oxygen liquids not of metal.
27.
Cooling of a vaporized content of a liquefied gas for the purpose of powering machinery, plants or vehicles
A fuel system for a liquefied gas drive system. The fuel system has a liquefied gas tank and a cooling system for the vaporized content of liquefied gas, which comprises a liquid nitrogen tank, a nitrogen pump, a heat exchanger, and a nitrogen cooler, which are connected to each other in a pipework circuit. The heat exchanger is arranged in the interior of the liquefied gas tank. Also disclosed are a vehicle, a plant and a machine, in each case with a fuel system, and a method for cooling the vaporized content of liquefied gas of a liquefied gas drive system.
B63J 2/14 - HeatingCooling of liquid-freight-carrying tanks
F25J 1/00 - Processes or apparatus for liquefying or solidifying gases or gaseous mixtures
F25J 1/02 - Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen
Disclosed is a fuel system (1) for a liquefied gas drive system. The fuel system has a liquefied gas tank (21) and a cooling system (10) for the vaporised content of liquefied gas, which comprises a liquid nitrogen tank (11), a nitrogen pump (12), a heat exchanger (13), and a nitrogen cooler (14), which are connected to each other in a pipework circuit. The heat exchanger (13) is arranged in the interior of the liquefied gas tank (21). Also disclosed are a vehicle, a plant and a machine, in each case with a fuel system (1), and a method for cooling the vaporised content of liquefied gas of a liquefied gas drive system.
F17C 13/00 - Details of vessels or of the filling or discharging of vessels
B63B 25/14 - Load-accommodating arrangements, e.g. stowing or trimmingVessels characterised thereby for bulk goods fluid closed pressurised
B63B 25/16 - Load-accommodating arrangements, e.g. stowing or trimmingVessels characterised thereby for bulk goods fluid closed heat-insulated
F02M 21/02 - Apparatus for supplying engines with non-liquid fuels, e.g. gaseous fuels stored in liquid form for gaseous fuels
F25J 1/02 - Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen
A tank device for a tank liquid comprises a pressure vessel with a first chamber for the tank liquid and second chamber arranged in an interior of the tank. The first and second chamber are closed off with respect to each other and are in operative connection via at least one membrane which separates the first and second chambers and is capable of vibration. The tank device further comprises a controllable element for effecting a pressure surge in the pressure vessel, a pressure sensor for detecting a pressure vibration resulting from the pressure surge and a temperature sensor for measuring a temperature prevailing in the pressure vessel. An evaluation device of the tank device is configured to determine a current gas volume in the pressure vessel from a respectively detected pressure vibration and a measured temperature to thereby calculate the mass of the tank liquid.
F17C 13/02 - Special adaptations of indicating, measuring, or monitoring equipment
G01F 22/02 - Methods or apparatus for measuring volume of fluids or fluent solid material, not otherwise provided for involving measurement of pressure
F02K 9/50 - Feeding propellants using pressurised fluid to pressurize the propellants
A heater apparatus configured to provide heat to at least one component of a spacecraft. The heater apparatus comprises a combustion chamber for a hypergolic propellant, and a heat radiator configured to radiate heat from the combustion chamber towards the at least one component to be heated. A spacecraft comprises at least one component to be heated and a heater apparatus configured to heat the at least one component to be heated. A method for heating at least one component of a spacecraft. The method comprises generating heat in a combustion chamber for a hypergolic propellant, and radiating at least a portion of the heat towards the at least one component.
A method for the degassing of hypergolic propellants includes introducing hypergolic propellant into a vacuum-tight vessel, cooling the vacuum-tight vessel containing the hypergolic propellant, and applying a pressure that is reduced as compared to the atmospheric pressure to the hypergolic propellant.
A gas inlet (10), in particular for use in an ion thruster, comprises a housing (12) which is made of a gas-tight ceramics material and which is provided with a first gas feed channel (14) and a second gas feed channel (16) arranged downstream of the first gas feed channel (14). The gas inlet (10) further comprises an insert (18) which is arranged in the second gas feed channel (16) and is made of a porous ceramics material, wherein the geometry and pore structure of the insert (18) are such that the insert (18) forms a desired flow resistance for a gas stream flowing through the second gas feed channel (16) which is greater than a flow resistance acting on a gas stream flowing through the first gas feed channel (14), and wherein a ratio of a length (11) of the first gas feed channel (14) to a length (13) of the insert (18) is at least 1:2.
A valve for closing a fluid line, comprising: an inlet element with an inlet line; an outlet element with an outlet line; a closing element which, in a first state, allows a fluid passage between the inlet line and the outlet line and which, in a second state, closes the fluid passage, wherein the closing element, in the first state, is fixedly connected to the inlet element or the outlet element and, in the second state, is detached from the inlet element or the outlet element; an actuator which, when actuated, is configured to move the closing element from the first state towards the second state; and a pretension element which is pretensioned and is configured to move the closing element into the second state after actuation of the actuator.
F16K 17/40 - Safety valvesEqualising valves with fracturing member, e.g. fracturing diaphragm, fusible joint
F16K 31/02 - Operating meansReleasing devices electricOperating meansReleasing devices magnetic
F03G 7/06 - Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for using expansion or contraction of bodies due to heating, cooling, moistening, drying, or the like
F16K 27/00 - Construction of housingsUse of materials therefor
F16K 49/00 - Means in or on valves for heating or cooling
A gas injection device for injecting an expulsion gas into a tank for a liquid. The gas injection device comprises an inlet pipe for receiving the gas and a distributor portion for releasing the gas through a plurality of capillary passages. The inlet pipe has a first end configured to be connected to a gas supply line and a second end located within a chamber in the distributor portion. The capillary passages respectively extend in a direction adapted to a periphery of the chamber. A tank for a liquid is provided, the tank comprising a gas injection device. A spacecraft is provided comprising such a tank.
A combustion chamber structure, particularly for a rocket engine, which comprises a liner surrounding a combustion chamber with an outer surface facing away from the combustion chamber on which coolant channels extending in a longitudinal direction of the liner are formed. The liner forms, at one longitudinal end, a coolant chamber extending in the circumferential direction of the liner for collecting and/or distributing a coolant. The combustion chamber structure further comprises a connecting structure that fluidly connects the coolant chamber to the coolant channels.
An injection apparatus for a rocket engine comprises an injection plate which delimits a combustion chamber upstream. The injection apparatus further comprises a plurality of coaxial injection elements distributed in the injection plate, each of which injection elements forms an inner outlet opening, delimited by a central sleeve body, for a first propellant component and an outer outlet opening for a second propellant component. The outer outlet opening is formed between the central sleeve body and a wall section which surrounds the central sleeve body in an annular manner. At least in a partial number of the injection elements, the central sleeve body projects from the wall section in the direction towards the combustion chamber. In particular, the central sleeve body projects relative to the injection plate into the combustion chamber.
A rocket propulsion system comprises a combustion chamber, an oxygen supply system, comprising an oxygen supply duct and being configured to supply oxygen to the combustion chamber, and a hydrogen supply system, comprising a hydrogen supply duct and being configured to supply hydrogen to the combustion chamber. An ignition unit of the propulsion system, to which at least portions of the oxygen and the hydrogen supplied to the combustion chamber can be supplied, is configured to initiate combustion of the oxygen-hydrogen mixture in the combustion chamber. The propulsion system further comprises a cooling duct extending along an inner surface of a combustion chamber wall and through which at least a portion of the oxygen supplied to the combustion chamber, at least a portion of the hydrogen supplied to the combustion chamber or a combustion gas mixture emerging from the ignition unit flows.
F02K 9/64 - Combustion or thrust chambers having cooling arrangements
F02K 9/95 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by starting or ignition means or arrangements
F02K 9/42 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid or gaseous propellants
A method for operating a rocket propulsion system comprises the steps of supplying oxygen to a combustion chamber, supplying hydrogen to the combustion chamber and combusting the oxygen-hydrogen mixture in the combustion chamber. The rocket propulsion system is operated alternately in a first operating mode, in which oxygen and hydrogen are supplied to the combustion chamber in a first mass mixing ratio of oxygen to hydrogen, and in a second operating mode, in which oxygen and hydrogen are supplied to the combustion chamber in a second mass mixing ratio of oxygen to hydrogen that is greater than the first mass mixing ratio.
F02K 9/64 - Combustion or thrust chambers having cooling arrangements
F02K 9/95 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by starting or ignition means or arrangements
A rocket propulsion system comprises a combustion chamber, a hydrogen-oxygen supply system connected to the combustion chamber, which hydrogen-oxygen supply system is configured to conduct hydrogen and oxygen into the combustion chamber, and a coolant supply system connected to the combustion chamber, which coolant supply system is configured to conduct a combustible coolant into the combustion chamber. An ignition system of the rocket propulsion system is configured to initiate combustion of the hydrogen-oxygen-coolant mixture in the combustion chamber.
F02K 9/95 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by starting or ignition means or arrangements
40.
Thrust nozzle with double contour and smooth transition
A thrust nozzle, in particular thrust nozzle for a rocket engine, with a convergent wall section, a throat section and a divergent wall section. The divergent wall section has a first region adjacent to the throat section, the wall contour of which region corresponds to a truncated ideal nozzle, and the divergent wall section has a second region facing away from the throat section, which region has a wall contour deviating from the first region.
A catalyst chamber with a catalyst bed embedded therein for a monopropellant thruster of a rocket engine. The catalyst chamber comprises an inlet having a first cross-sectional area through which a propellant can be introduced into the catalyst chamber and an outlet having a second cross-sectional area through which the propellant and/or resulting reaction products can be introduced into a combustion chamber of the thruster. The outlet is connected to the inlet via a catalyst volume of the catalyst chamber. At least one helical wall member is arranged within the catalyst chamber and is dividing the catalyst volume into two or more segments such that an effective length of the catalyst bed of each segment passed through by the propellant and/or its reaction products is larger than a geometrical length of the catalyst chamber defined between the inlet and the outlet along a direction of extension of the catalyst chamber.
A bending frame extends the travel of an actuator for a mechanically actuated component. The bending frame includes a plurality of bendable longitudinal struts, which are arranged about a longitudinal axis on which the travel of the actuator runs. The longitudinal struts each extend in the direction of the longitudinal axis, and an application of force enacted by the actuator long the actuation path on the longitudinal struts causes same to bend in a direction perpendicular to the longitudinal axis. Respective cross struts extend out toward the longitudinal axis from each of the longitudinal struts, wherein a first end of a respective cross strut is articulated to a respective longitudinal strut and a second end of the respective cross strut opposite to the first end is provided in order to transmit force to the component in the direction of the longitudinal axis for the purpose of actuation thereof. The longitudinal struts and the cross struts interact with one another such that bending of the longitudinal struts causes the second ends of the cross struts to be displaced in the direction of the longitudinal axis, thereby extending the travel for mechanically actuating the component.
B60T 8/36 - Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration having a fluid pressure regulator responsive to a speed condition including a pilot valve responding to an electromagnetic force
43.
Valve assembly, in particular for space travel drive systems, which is closed when not actuated
A valve assembly includes an inlet and an outlet, which open into a working chamber of the valve assembly, and an actuator. In a non-actuated state of the actuator, a flow passage between the inlet and the outlet is blocked. The actuator is optionally a shape-memory actuator that can be actuated one time or comprises a shape-memory actuator, which suddenly changes its external shape upon reaching a conversion temperature, which is dependent on the alloy composition thereof, and which can be generated by a controllable electrical heating device of the valve assembly. The actuator irreversibly destroys a pipe element separating the inlet from the outlet in the working chamber upon actuation, whereby the inlet and the outlet are connected to one another with respect to flow via the working chamber.
A valve arrangement for an aerospace component includes an inlet, an outlet, and an actuator that can be actuated by a heating element. In a non-actuated state of the actuator, the valve is open to allow flow between the inlet and the outlet. The actuator is a single-use effect shape memory actuator that is compressed in the martensitic state along a longitudinal axis of the actuator and integrated into the valve arrangement. Through the activation of the heating element upon reaching a predetermined transformation temperature, the actuator undergoes a change in length, whereby it is gradually pressed against a seal seat that is embodied at the inlet or the outlet.
F03G 7/06 - Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for using expansion or contraction of bodies due to heating, cooling, moistening, drying, or the like
H01L 21/20 - Deposition of semiconductor materials on a substrate, e.g. epitaxial growth
H01L 31/0304 - Inorganic materials including, apart from doping materials or other impurities, only AIIIBV compounds
H02J 50/70 - Circuit arrangements or systems for wireless supply or distribution of electric power involving the reduction of electric, magnetic or electromagnetic leakage fields
H02J 50/30 - Circuit arrangements or systems for wireless supply or distribution of electric power using light, e.g. lasers
H01L 31/0693 - SEMICONDUCTOR DEVICES NOT COVERED BY CLASS - Details thereof adapted as photovoltaic [PV] conversion devices characterised by at least one potential-jump barrier or surface barrier the potential barriers being only of the PN homojunction type, e.g. bulk silicon PN homojunction solar cells or thin film polycrystalline silicon PN homojunction solar cells the devices including, apart from doping material or other impurities, only AIIIBV compounds, e.g. GaAs or InP solar cells
H02J 17/00 - Systems for supplying or distributing electric power by electromagnetic waves
H01L 31/056 - Optical elements directly associated or integrated with the PV cell, e.g. light-reflecting means or light-concentrating means the light-reflecting means being of the back surface reflector [BSR] type
H01L 31/054 - Optical elements directly associated or integrated with the PV cell, e.g. light-reflecting means or light-concentrating means
H01L 31/18 - Processes or apparatus specially adapted for the manufacture or treatment of these devices or of parts thereof
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
42 - Scientific, technological and industrial services, research and design
Goods & Services
Instrumentation simulators; Simulation software for use in digital computers; Simulators for training personnel in the driving of space vehicles, in particular spacecraft; Simulators for the operation of space vehicles, in particular spacecraft; Simulators for the steering and controlling of space vehicles, in particular spacecraft; Measuring, signalling and checking (supervision) apparatus; Electric and electronic monitoring apparatus; Modems; Electrical signal transmitters and receivers; Programs recorded on data carriers. Satellites for transportation. Science and technology services; Simulation software.
47.
Device for opening or closing a seal set of a valve
A device for opening or closing a seal seat of a valve arranged in a pipe for liquid or gaseous media includes a one-time only activation of the valve using a shape memory actuator. The shape memory actuator changes its external shape abruptly when a transformation temperature is reached that is dependent upon its alloy composition. The transformation temperature can be generated by a controllable electrical heating device of the device.
F16K 11/048 - Multiple-way valves, e.g. mixing valvesPipe fittings incorporating such valvesArrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only lift valves with valve seats positioned between movable valve members
F16K 31/02 - Operating meansReleasing devices electricOperating meansReleasing devices magnetic
F03G 7/06 - Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for using expansion or contraction of bodies due to heating, cooling, moistening, drying, or the like
B64G 1/40 - Arrangements or adaptations of propulsion systems
A valve assembly for switching and/or regulating a medium flow of an aerospace engine includes a drive, a valve and a flexible separator element. The drive includes one or more electrically actuatable actuators, which change their length in the direction of a longitudinal axis of the valve assembly when a control voltage is applied to the actuators. The valve includes a valve piston, which can be moved back and forth along the longitudinal axis by the drive and which has a valve member. The flexible separator element delimits a working space of the valve from the drive, as a result of which the medium, which flows through the valve or is present in the working space, is hermetically separated from the drive.
F02C 7/232 - Fuel valvesDraining valves or systems
F16K 1/14 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with ball-shaped valve members
F16K 41/10 - Spindle sealings with diaphragm, e.g. shaped as bellows or tube
A valve for one-time opening a fluid line for venting a technical system includes an inlet for connecting to the fluid line, an outlet, and a controllable closure arranged between the inlet and the outlet. In the non-activated state the controllable closure closes a passage between the inlet and the outlet. The closure includes a material that changes its phase state in dependence on a control parameter, whereby the passage is irreversibly opened in the activated state.
A device for regulating pressure and/or mass flow of a gaseous or liquid fluid conveyed through a line in a space propulsion system includes a first, piezoelectrically actuatable regulating valve and at least two second, magnetically actuatable regulating valves. The regulating valves are connected to each other and to a line input in such a way that in a nominal mode the pressure and the mass flow of the fluid can be set by the first regulating valve, and a connection or isolation of the first regulating valve with or from the line input can be produced by the second regulating valves. In an emergency mode the pressure and the mass flow of the fluid can be set by the second regulating valves.
A plasma generator having a housing surrounding an ionization chamber, at least one working-fluid supply line leading into the ionization chamber, the ionization chamber having at least one outlet opening, at least one electric coil arrangement which surrounds at least one area of the ionization chamber, the coil arrangement being electrically connected with a high-frequency alternating-current source (AC) which is constructed such that it applies a high-frequency electric alternating current to at least one coil of the coil arrangement, is wherein a further current source (DC) is provided which is constructed such that it applies a direct voltage or an alternating voltage of a frequency lower than that of the voltage supplied by the high-frequency alternating current source (AC) to at least one coil of the coil arrangement.
A coaxial valve for regulating and blocking a fluid medium having a valve housing having at least one inlet opening, at least one outlet opening and a flow duct connecting the inlet opening to the outlet opening; a tubular valve sleeve disposed in an axially movable manner in a portion of the flow duct and having an inflow and an outflow opening for the medium, wherein the inflow and outflow openings open into the flow duct; a closure member disposed in the valve housing and arranged coaxially with the valve sleeve and configured to close the inflow opening; and a drive configured to axially move the valve sleeve and having an electric servomotor and a transmission part coupled between the servomotor and the valve sleeve, the transmission part configured to transmit an axial movement to the valve sleeve.
An ion drive for a spacecraft, including a high-frequency generator for generating an alternating electromagnetic field for the ionization of a propellant and an acceleration system for the charge carriers, is provided. The ion drive includes a voltage source with which the high voltages that are necessary for the acceleration system can be derived from the currents and/or voltages generated by the high-frequency generator for generating the alternating electromagnetic field.
Microthruster includes a combustion chamber comprising a substrate material, a fuel inlet, and a gas outlet. A first resistance heater is arranged in the combustion chamber. A catalyst is structured and arranged to decompose fuel entering the combustion chamber. First substrate material sections are heated by the first resistance heater to at least one of a predetermined temperature and a predetermined temperature range.
A device for coupling ionization energy into an ion or electron source, which is excited inductively or inductively-capacitively is provided. The device includes: a discharge vessel for a gas, which is to be ionized; a coupling coil, which is wound around the discharge vessel and feeds in a high frequency energy, which is required for plasma excitation; a coupling capacitor, which is electrically coupled to the coupling coil; a high frequency generator, which is electrically coupled to the coupling coil. The high frequency generator forms, together with the at least one coupling capacitor, a resonant circuit. The high frequency generator includes a PLL controller for automatic impedance matching of the resonant circuit, so that the resonant circuit can be driven at a resonant frequency.
Device for damping oscillations of a combustion chamber that includes at least one resonator connected to a pre-chamber in a vibration-damping manner. The pre-chamber is connected to a combustion chamber in a vibration-damping manner via at least one passage channel. This abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.
09 - Scientific and electric apparatus and instruments
11 - Environmental control apparatus
12 - Land, air and water vehicles; parts of land vehicles
42 - Scientific, technological and industrial services, research and design
Goods & Services
Measuring, signalling and checking (supervision) apparatus;checking, supervision, life-saving and teaching apparatus. Gas generators. Watercraft, namely submarines and parts thereof, included in class 12. Scientific and technological services.
A coaxial valve includes a valve box having an inlet opening, an outlet opening, and a common flow channel. An axially movable cylindrical valve casing has an opening for a fluid inlet port and an opening for a fluid outlet port, both of which are joined up in the flow channel. A coaxially positioned shutoff mechanism located inside the valve box closes off the inlet port or the outlet port of the valve casing. To provide for axial movement, the valve casing has at least one external circular groove. The drive casing has at least one inner circular groove, which is adapted to the outer circular groove so that the inner and outer grooves are engaged, via inside ball bearings, to create a ball planetary gear and ball rotary spindle drive. The drive casing is turnable and forced to turn by a drive motor inside of the valve box.
A coaxial valve with a valve box, that has at least one inlet opening and at least one outlet opening and features a common flow channel, a cylindrical valve casing, which is prevented from turning at one segment of the flow channel, but is intended to be axially movable and which features an opening for the fluid inlet port as well as an opening for the fluid outlet port, both of which join up in the flow channel, a shutoff mechanism located inside the valve box which is positioned coaxially to the valve casing and which is designed to close off the inlet port or the outlet port of the valve housing, and the drive to the axial movement of the valve casing which is marked by the fact that the valve casing is enclosed at least in sections at its outermost surface by at least one grooved external circular groove, that the valve casing at the segment of the grooved external circular groove is enclosed by one drive casing which is coaxial to the drive casing, that it has at its internal diameter at least one inner circular groove, one which is adapted to the outer circular groove so that the inner and outer grooves are engaged via the inside ball bearings, to create a ball planetary gear and ball rotary spindle drive, and that the drive casing in the valve box is turnable, but firmly seated axially and forced to turn by the drive motor which is intended to be inside of the valve box.
F16K 31/50 - Mechanical actuating means with screw-spindle
F16K 1/12 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with streamlined valve member around which the fluid flows when the valve is opened
F16K 31/04 - Operating meansReleasing devices electricOperating meansReleasing devices magnetic using a motor
Control and/or drive device for a flying body for ejecting hot gas streams of a combusted fuel combination of at least a first and second component. Device includes a first hollow chamber body structured and arranged to contain first component, a second hollow chamber body structured and arranged to contain second component, a controllable fuel valve arranged between first hollow chamber body and second hollow chamber body to control feed of first component to second hollow chamber body, and a plurality of outlets structured and arranged to eject respective hot gas streams for influencing a flight path of flying body. Second hollow chamber body is formed as a combustion chamber for combusting the at least first and second components within second hollow chamber body to generate respective hot gas streams, and plurality of outlets are connected to the second hollow chamber body.
F02K 1/00 - Plants characterised by the form or arrangement of the jet pipe or nozzleJet pipes or nozzles peculiar thereto
F02K 9/28 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using solid propellants having two or more propellant charges with the propulsion gases exhausting through a common nozzle
12 - Land, air and water vehicles; parts of land vehicles
13 - Firearms; explosives
16 - Paper, cardboard and goods made from these materials
37 - Construction and mining; installation and repair services
41 - Education, entertainment, sporting and cultural services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Machine tools and machines for manufacturing parts for use in turbojet engines, ram jet engines, pulse jet engines and missiles with rocket engines; Motors and engines of all kinds for fixed or mobile installations (except for land vehicles), including gas turbine engines, heat engines, electrothermal engines, jet engines, nuclear engines, combined propulsion engines, rocket engines, hypersonic engines, cryogenic rocket motors, rocket motors for satellite launchers and for ballistic and tactical missiles, rocket engines and vernier engines for satellites; Ion engines, thrusters, plasma engines, plasma sources, arc-jets; Aircraft engine thrust reversers; Parts of the aforesaid motors and engines, thrust reversers and And engines,Including combustion chambers, thrust nozzles, air intakes. Aircraft and space vehicles of all kinds, including manned and unmanned space vehicles; launch vehicles,Rockets for space travel; satellites; Space shuttles for space travel, including with hypersonic engines; Space stations; braking apparatus for vehicles, Railway vehicles and Aircraft,Including brake drums, Brake linings, Brake disks and Brake shoes. Missiles with rocket engines; Missiles. Pamphlets, periodicals, brochures, books. Construction, Aircraft repair and maintenance,Space vehicles, space stations, missiles, rockets and carrier rockets; Construction of industrial buildings and test beds for propulsion units for rocket engines; Repair and reconditioning of aeronautical engines and space propulsion units; Rocket chambers, thrust nozzles and air inflows; Repair and maintenance of friction-stressed parts, including braking devices, in particular brake drums, brake linings, brake discs and brake segments; Provision of information in connection with the aforementioned services. Instruction and training; Conducting seminars. Statements, Design and Restoration of computer dates and Software; Engineering; Engineering consultancy; Laboratory services; Scientific and insdustrial research; Provision of information in relation to the foregoing.
