78results about "Cosmonautic components" patented technology

Exemplary embodiments described herein may include lightweight, low stow volume solar concentrator.

A collapsible space enclosure system is disclosed, designed for efficient transport and deployment in the field of mechanical engineering. The system described addresses the technical problem of cumbersome and inefficient collapsible structures by providing a system that integrates a telescopic lifting central section with an upper and lower portion for balanced vertical retraction and extension. The system includes folding panels connected to the central structure, configured to fold in two for compact shipment. Actuators enable continuous 360° rotation and balanced vertical movement. Parallelogram linkage assemblies facilitate simultaneous lateral retraction and vertical lifting. Retractable strut channel assemblies allow for the installation of add-on retractable spaces, increasing floor area. This system is particularly useful for military, commercial, and recreational applications, offering a streamlined and versatile solution for rapid deployment and compact storage.

The invention relates to a system for full-supercooling large-flow liquid methane filling and a using method of the system. The full-supercooling large-flow liquid methane filling system is stable, reliable, high in automation degree, capable of dynamically adjusting the supercooling temperature and flow of liquid methane and high in accuracy, and comprises a storage box, a pressurization module, a recovery module, a methane filling module, a control module and a nitrogen filling module, and the pressurization module comprises a methane pressurization tank; the methane filling module comprises a methane filling tank, the nitrogen filling module comprises a nitrogen filling tank and a subcooler, the recovery module comprises a methane recovery tank, and the control module pressurizes the methane recovery tank and the methane filling tank by controlling the pressurization module and adjusts the filling flow and temperature of methane to prevent condensation by controlling the methane filling module and the nitrogen filling module. Flow stabilization and backflow are carried out by controlling the methane filling module and the recovery module.

The invention discloses a liquid oxygen circulation supercooling system, and relates to the technical field of liquid oxygen storage management, liquid oxygen is stored in a liquid oxygen storage tank, the liquid oxygen enters a self-pressurization vaporizer from a vaporization liquid inlet pipe to be vaporized, oxygen generated by vaporization enters the liquid oxygen storage tank from a vaporization steam exhaust pipe, so that the pressure in the liquid oxygen storage tank is increased, and the liquid oxygen is discharged into a pipe needing to be cooled after being increased; the supercooling process is realized when the liquid oxygen in the pipe needing to be cooled flows through the cooler, and the liquid oxygen flows back to the liquid oxygen storage tank again after being supercooled; the device is applied before a launching task starts, liquid oxygen in the liquid oxygen storage tank is supercooled through continuous liquid oxygen circulating flow, compared with supercooling when liquid oxygen is injected into a rocket, supercooling is conducted in advance in the storage stage, injection peak flow does not need to be matched, the size of the device is smaller, and the manufacturing cost is lower.

A header rail 10 for transporting gas cylinders (30, fig 3) on lorries has an elongate non-metal (e.g. composite such as glass / carbon fibre) central core 12, with metal collars 14 spaced apart along t

The present invention relates to a reinforced bulging tank of a launch vehicle and a manufacturing method therefor. The tank is made of metal material with good plasticity. Firstly, the tank is manufactured by welding annealed plastic metal materials, wherein internal longitudinal reinforcing ribs and internal annular frames / annular plates of barrel sections are welded with a barrel section shell by a low energy laser welding method, and tank bottoms are progressively welded by a plurality of conical sections. Weldments are strengthened and formed through internal pressure bulging under the constraint of external tooling. The outer walls of the barrel sections are not radially deformed under the constraint of a plurality of small width metal rings, and the metal rings are not connected to each other axially. The strength of the materials can be greatly improved by a deep cooling bulging technology.

The invention relates to the technical field of propellant storage and management, in particular to a liquid oxygen tank for a space gas station, the liquid oxygen tank comprises a pressure-resistant shell, a mixing channel assembly, a superconducting coil assembly and an exhaust port, the mixing channel assembly is of a double-layer thin-wall circular tube structure and comprises an inner-layer circular tube and an outer-layer circular tube; one end of the inner-layer circular tube is in clearance fit with an assembly hole in the inner wall of the pressure-resistant shell, and the other end of the inner-layer circular tube extends out of the pressure-resistant shell to form a liquid inlet; the outer-layer circular pipe integrally surrounds the outer part of the inner-layer circular pipe, and one end, close to the liquid inlet, of the outer-layer circular pipe extends out of the pressure-resistant shell to form a liquid outlet; the superconducting coil assembly is wound on the outer wall of the inner-layer circular tube; and the exhaust port is formed in the pressure-resistant shell. According to the device, liquid oxygen can be injected or discharged in a microgravity environment, a container for storing and managing a liquid oxygen propellant is provided for a space gas station, and therefore on-orbit liquid oxygen discharging management and repeated liquid oxygen filling of a spacecraft are achieved.

The invention relates to a storage system (1) for a pressurized gaseous fuel, comprising at least two pressurized gas containers (2), which are coupled to one another and to filling and withdrawal connections via a line system (6), and at least one temperature-control device (15), wherein the temperature-control device (15) is arranged in the line system (6). The storage system according to the invention is characterized in that the temperature-control device (15) is arranged in a connecting line (13) between at least two of the pressurized gas containers (2).

The invention relates to a terminating device of a fibre composite material structure, wherein the terminating device comprises a fibre composite material connecting portion for connecting a tubular fibre composite material structure to a connecting device, wherein the connecting portion has at least one fibre deflecting member in its interior, wherein the course of the long fibres from the fibre composite material structure follows the shape of a fibre deflection portion of a fibre deflection member so that their fibre direction is deflected at the fibre deflection portion, and wherein the long fibres do not completely wrap around the fibre deflection members with which they are associated, the fibre deflection members being made of fibre composite material. According to the invention, the connecting device has a first element and a second element, wherein the second element has a contact area with the fibre composite material structure on its outer circumference and a contact area with the first element on its inner circumference, wherein each of the elements has a conical shape in the contact area with the other element. Advantageously, the conical shape of the elements of the connecting device can create a wedge, which causes the elements of the connecting device to generate a radial preload in the fibre composite material after the fibre composite material has been applied.

A number of techniques, structures, and materials for thermally insulating a cryogenic propellant tank barrel section are presented. Thermal insulation for a tank, such as tanks for use in space flight missions, may be a dual wall vacuum jacket system where one wall is the propellant tank wall and the other wall is a metallic foil that is welded to portions of the propellant tank wall. The metallic foil may act as a vapor barrier and a vacuum seal. A structural and breathable insulation that is durable and functional in a range from cold to relatively high temperatures may be used to maintain a standoff distance between the two walls. The volume between the propellant tank wall and the metallic foil may be purged with a gas that has a liquefaction temperature greater than that of the cryogenic propellant that will be in the propellant tank during operations.

A double-wall tank comprising an inner vessel surrounded by an outer jacket. The double-wall tanks comprising arrangements for coupling an inner vessel relative to an outer jacket which include roller bearings between the inner vessel and the outer jacket. Also an aircraft having at least one double-wall tank with the roller bearings.

Various embodiments relate generally to additive manufacturing and construction techniques to form structures with embodiments directed to computer software and systems, and control systems, and, more specifically, to a computing and a mechanical platform configured to implement local material to form a structure by selecting or filtering a subset of particulate that is deposited in a form at which adaptive levels of energy are applied to construct structures in-situ in a vacuum additively (e.g., three-dimensionally, or in “3D”), whereby adaptive levels of energy may be generated by one or more lasers and may be configurable to control temperatures associated with, for example, crystallization of indigenous particulate.

The application provides a gravity unloading attitude adjusting device and method suitable for heavy load assembly, four gravity unloading units are arranged on a carrying vehicle, a single gravity unloading unit comprises a plane air floating support mechanism, a support column, a vertical hydraulic cylinder and a spherical air floating support mechanism; a load platform is supported by the four gravity unloading units, the load platform is driven by an attitude adjusting driving unit to carry out six-degree-of-freedom position adjustment, so that the assembly body reaches a target assembly position. In the position adjustment process, the plane air floating support mechanism provides translational freedom and rotation freedom around the vertical direction, the four vertical hydraulic cylinders and the spherical air floating support mechanisms thereon jointly provide tilting freedom in any direction and vertical movement freedom, and support force is provided to offset the gravity of the load platform and its load, gravity unloading is realized, the driving load of the attitude adjusting driving unit is greatly reduced, the accuracy and feedback speed of the attitude adjusting process are provided, and oscillation is effectively avoided or reduced.

The application discloses a micro electric propulsion storage and supply system, characterized in that the system comprises a storage module, a pressure regulating module, a flow regulating module, a power module and a control module, wherein the storage module, the pressure regulating module and the flow regulating module are sequentially connected through stainless steel pipelines, and the modules and the pipelines are connected through standard sleeves; the power module supplies power to the pressure regulating module and the flow regulating module, and the control module realizes pressure and flow control. The system adopts a combination of a miniature mechanical pressure reducing valve and a pressure sensor as the pressure regulating module, realizes smaller volume and mass relative to a Bang-Bang type, and has lower cost relative to a proportional type, so that balance is achieved between the reduction of the volume and mass of the system and economy; the flow regulating module adopts a pasting mode of a capillary tube and a silicon rubber heating belt, so that the silicon rubber heating belt can be directly pasted to the metal capillary tube, and an outer shell of the capillary tube is not needed, thereby reducing the volume and mass of the module and improving the heating efficiency.

A header rail 10 for transporting gas cylinders (30, fig 3) on lorries has an elongate non-metal (e.g. composite such as glass / carbon fibre) central core 12, with metal collars 14 spaced apart along t

The invention discloses a liquid oxygen methane carrier rocket low-temperature filling system and method, and belongs to the technical field of aerospace power. Comprising a filling target container, a measurement control system, a methane filling system, a liquid oxygen filling system and an oxygen supercooling system. The methane filling system is communicated with the methane storage tank and is used for filling methane into the methane storage tank; the liquid oxygen filling system is communicated with the liquid oxygen storage tank and is used for providing liquid oxygen for the oxygen storage tank; the oxygen supercooling system is connected with the liquid oxygen filling system so as to provide supercooled liquid oxygen; the measurement control system is connected with the methane filling system, the liquid oxygen filling system and the oxygen supercooling system through a control circuit so as to monitor and control the operations thereof; the system adopts a tank car extrusion propellant filling mode. The device has the characteristics of low cost, short construction period, adjustable filling flow and controllable temperature. The rear end of methane filling pipeline equipment is remotely controlled, and safety is guaranteed. The system has engineering application value for multiple flight tests of a reusable rocket.

An object of the system according to the embodiment is to analyze a signal or a radio wave from outer space and estimate information regarding an unknown region or a living body.SOLUTION: A system includes a signal collection unit, a generation AI analysis unit, and an estimation unit. The signal collection unit collects signals and radio waves from outer space. The generation AI analysis unit analyzes the signals and radio waves collected by the signal collection unit in the generation AI. The estimation unit estimates information on an unknown region of the universe or a living body on the basis of a result analyzed by the generation AI analysis unit.SELECTED DRAWING: Figure 1

The objective is to reduce the effects of Coriolis force in an artificial gravity generator. [Solution] An artificial gravity generating device comprising: a driving source 1; a rotating shaft member 2 that is rotated by the driving source 1; an arm 3 attached to the rotating shaft member 2; and a first box-body 6 that can accommodate a person and is connected to the arm 3 via a joint member 4 that can rotate in any direction and can be tilted in any direction by the joint member 4, thereby reducing the effects of the Coriolis force acting during rotation; and wherein the rotation of the rotating shaft member 2 causes the first box-body 6 to rotate around the rotating shaft member 2, thereby generating centrifugal force.

Provided is a system, method and device for payload positioning. The system includes a rover configured to travel to a site and hold the payload, a sensor module attached to the rover for obtaining sensor data of the site, a robotic arm for equipping and stowing away the sensor module, attaching to a connection point of the payload, and controlling a position of the payload when attached to the connection point.

This invention relates to a mass-optimized geogrid system and method for stabilizing regolith and other granular soils in extraterrestrial and extreme Earth environments. Mass reduction is achieved both locally—within individual geogrid layers through optimization of lattice geometry, variable mesh density, and reinforcement at stress concentrations—and globally, by varying the spacing and distribution of layers according to structural demands. The geogrid may be fabricated from materials that are locally sourced or compositionally traceable to in-situ resource utilization (ISRU) processes in environments such as the Moon, Mars, or terrestrial polar and desert regions where conventional construction materials are limited or costly to transport. The method includes restructuring the regolith by size-sorting and compaction to produce a particle-size distribution proportionally matched to the mesh openings, enhancing mechanical interlock and shear resistance. Structural efficiency can be tuned and verified through physical testing and finite-element analysis for scalable, repeatable construction.

A header rail (10) comprises an elongate non-metal central core (12), a plurality of metal collars (14) spaced apart along the central core (12) and each surrounding a respective hole (16) passing through the central core (12), a pair of metal brackets (18) each located at a respective end of the central core (12) and connected to the central core (12), and an external non-metal coating (20) covering the central core (12).

The invention provides a satellite on-orbit assembly structure relative pose resolving method and system, and the method comprises the steps: constructing a satellite on-orbit assembly structure relative pose measurement system through two sets of five-degree-of-freedom measurement equipment, and building a mathematical model of a three-dimensional displacement measurement device and a two-dimensional deflection angle measurement device; a measurement model of five-degree-of-freedom measurement equipment is deduced and established based on a geometrical relationship, a pose conversion parameter linear resolving model is obtained through processing according to a pose conversion small spinor theory, pose conversion parameters are iteratively calculated through a least square method, and the method is suitable for pose measurement and resolving of most satellite in-orbit assembly or adjustment structures. Good application prospects are realized.

The application provides a lunar surface protection device and relates to the technical field of space protection.The lunar surface protection device provided by the application adopts a modular design combining a composite material plate and a prefabricated framework, the prefabricated framework is manufactured on the earth, a shape memory hinge is used as a folding node, the prefabricated framework is folded to a compressed form, the volume size is greatly reduced, the lunar surface protection device is convenient for transportation between the earth and the moon, and the carrying pressure of a carrier rocket is reduced.The lunar surface protection device fully utilizes lunar in-situ resources, completes the manufacturing of the composite material plate, realizes the combination of the manufacturing on the earth and the moon, can reduce the operation steps of manufacturing the protection structure in the extreme environment on the lunar surface, and improves the manufacturing efficiency of the protection structure.

Methods and systems are presented for sintering a material, which may be in a granulated or powdered form, in a mold using microwave radiation. These methods and systems may lead to a sintered object that contracts (e.g., shrinks) away from sides of the mold so that it is able to be easily released from the mold. Accordingly, for example, sides of the mold need not be angled (e.g., with draft angles), which is generally done to molds to allow for the molded object to be releasable, such as by lifting or dumping out the molded part. A particular advantage of these methods and systems, besides not needing to distort a mold shape with draft angles, is that the contraction caused by microwave sintering may likely avoid chemical reactions or adhesion between the sides of the mold and the sintered object because the contraction causes a gap therebetween.

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. Also a vehicle having a hydrogen drive and such a hydrogen tank, and a method for cooling the tank structure of such a hydrogen tank.

Valve (1) for a fluid reservoir, comprising an inner portion configured to be arranged inside the reservoir (3), the inner portion comprising at least one portion of a sensor (34, 35) for measuring at least one parameter characterising the fluid, the valve (1) being capable of receiving information from a computer (5), external to the valve (1), characterised in that the valve (1) also comprises an outer portion configured to be arranged outside the reservoir (3), the outer portion comprising an internal computer (7) comprising: - a first acquisition means (9) configured to acquire data from at least one sensor (34, 35), - a communication means (11) using a wired digital communication interface capable of communicating bidirectionally with the external computer (5), - a control means (13) configured to take into account information received from the external computer (5) and data from at least one sensor (34, 35) for controlling at least one actuator (100) of the valve (1), the at least one actuator (100) being connected to the control means (13) by at least one electrical connection (15), and - a means (17) for measuring at least one current parameter in the electrical connection (15).

The vessel includes first and second hollow shells including first and second inner surfaces, respectively, for receiving a portion of a pressure vessel (PV). The first hollow shell includes a fibrous layer at least partially impregnated with a resin and an energy dissipative material substantially concentric with the first inner surface and disposed between the first inner surface and the fibrous layer. The second hollow shell includes a fibrous layer at least partially impregnated with a resin and an energy dissipative material substantially concentric with the second inner surface and disposed between the second inner surface and the second fibrous layer. The first and second hollow shells are attachable to one another to define a volume for at least partially enclosing the PV.

A diffuser for separating a gas component and a liquid component of a liquid-gas mixture to reduce slosh in vehicle systems is described herein. The diffuser includes a wall with a gas end, a liquid end, and multiple vanes partially extending from the liquid side to the gas side. The vanes are spaced apart from each other by a given distance to permit the liquid to flow toward the liquid end via capillary action.

Systems and methods for manufacturing modular bricks from regolith on the surface of the moon for radiation protection and lunar habitation are provided. For example, regolith can be used to manufacture modular bricks that form maintainable and reusable structures that can provide protection from radiation on the lunar surface. In some embodiments, hollow bricks can be filled with loose regolith to leverage its radiation protection capabilities by increasing an amount of material within the structure while reducing the amount of processed material, thereby increasing the radiation protection afforded by the structure. The bricks can be shaped like hexagonal prisms to promote stacking with one another in the absence of binding materials while also allowing for tolerance during positioning. Manufacturing of the bricks can involve melting lunar regolith in a heating device, casting it into hollow hexagonal prism bricks, filling these bricks with regolith, and assembling them into structures.

The invention relates to a tank container system (100), in particular for pressure tank containers and very particularly for high-pressure tank containers for storing a gaseous fuel for driving a vehicle. The invention also relates to a system for accommodating such a tank container system. According to a first aspect, the stated problem is solved by a tank container system (100) for mounting on a vehicle, which tank container system comprises a first and a second carrier (110, 120), wherein the first and the second carrier (110, 120) comprise brackets (131, 132) for a tank container (150), wherein the brackets (131, 132) are each provided in pairs, wherein a first bracket (131) of each bracket pair is located on the first carrier (110) and a second bracket (132) of each bracket pair is located on the second carrier (120), wherein each bracket pair comprises a floating bearing (135) and a fixed bearing (136). The brackets (131, 132) are designed to be interchangeable, wherein the first carrier (110) and the second carrier (120) each comprise a device (111, 121) in which the first bracket (131) and the second bracket (132) are mounted so as to be displaceable and fixable in the longitudinal direction of the associated carrier (110, 120).