61 results about "Multi-layer insulation" patented technology

A portable cooler having one or more ice sheets including built-in refrigerant cubes. The cooler comprises an outer fabric shell and one or more sets of spaced apart refrigerant cubes encapsulated in plastic to form ice sheets that are attached to the interior walls of the cooler. The walls of the cooler may also include one or more layers of thermal insulation. The ice sheets provide a visually pleasing appearance to the inside of the cooler suggestive of cooling effects. The ice sheets may be retained along the walls of the cooler by seams sewn along the lanes passing between the refrigerant cubes, by being retained in pockets formed by sidewall liners or by being secured into chambers defined by the cooler's outer walls and a plastic insert fitted into the cooler. The cooler may include a hinged top and bottom that can be folded flat for allowing the cooler to assume a compact configuration during storage or freezing of the refrigerant cubes.

A multilayer insulation with an array of rigid posts is provided. In particular, the posts are comprised of multiple post elements that are interconnected to radiation shields or sheets comprising the layers of the integrated multi-layer insulation structure. The post elements maintain spacing between adjacent sheets, thus maintaining a volume between the sheets. The post elements within a post can be attached to one another to form an integrated post structure. Moreover, neighboring posts can be interconnected to one another by beams. The post elements can also be configured so that, when the IMLI structure is not subjected to atmospheric pressure, the elements within a post are separated from one another to form gaps, thereby reducing heat transfer between layers.

The invention relates to fuel cell systems with improved thermal efficiency. The systems include a fuel cell that generates electrical energy using hydrogen and a fuel processor that produces hydrogen from a fuel. Some heat efficient systems described herein include a thermal catalyst that generates heat when the catalyst interacts with a heating medium. The heat is used to heat the fuel cell. The thermal catalyst may be disposed in, proximity to the fuel cell, or remote from the fuel cell and a heat transfer pipe conducts heat from the catalyst to the fuel cell. Another thermally efficient embodiment uses a recuperator to transfer heat generated in the fuel cell system to incoming fuel. A fuel cell package may also include a multi-layer insulation arrangement to decrease heat loss from the fuel cell and fuel processor, which both typically operate at elevated temperatures.

The invention provides a packaging structure and a display device. The packaging structure comprises a display substrate and a packaging lamination layer for packaging the display substrate, wherein the packaging lamination layer at least comprises a first inorganic packaging layer, a second inorganic packaging layer and an organic packaging layer clamped between the first inorganic packaging layer and the second inorganic packaging layer, the display substrate comprises a substrate and a multi-layer insulation layer arranged above the substrate, the display substrate is divided into a displayregion and a non-display region surrounding the display region, the multi-layer insulation layer in the non-display region is provided with a cofferdam, the multi-layer insulation layer is provided with at least one first groove at one side of the cofferdam close to the display region, and the organic packaging layer is at least partially arranged in the first groove. The packaging structure is advantaged in that the groove arranged on the display substrate is used for accommodating an organic material for preparation of the organic packaging layer, the quantity of cofferdams and the area ofthe non-display region are reduced, and the narrow framework is realized.

The invention discloses a high-temperature high heat flow simulator for spacecraft vacuum heat tests in a space environment simulating chamber. The simulator mainly comprises infrared light arrays, a high-temperature insulation component unit, moving units, a temperature measuring unit and a temperature controlling unit. A plurality of infrared lights in the infrared light arrays are provided with reflective screens, the infrared lights are arrayed and combined to form the infrared light arrays according to requirements of heat flux density and uniformity, baffles surround the periphery of the infrared light arrays, high-temperature multi-layer insulation components are mounted among the infrared lights, a mounting baseplate and the baffles, and a high temperature region is limited in region formed through specimen irradiated face and the infrared light array high-temperature insulation components. According to the high-temperature high heat flow simulator, by means of unique design of the infrared light arrays and the high-temperature insulation components, technical difficulties of high-temperature high heat flow simulation when vacuum heat tests are performed on a spacecraft are solved, high-temperature high heat flow space environment can be simulated when vacuum heat tests are performed on spacecrafts in series of deep space exploration and space shuttles, and the spacecrafts can be tested.

A magnetic multi-layer insulation system for a cryogenic storage tank. The system includes multiple layers of insulation comprising a carrier support structure disposed between a first major surface of a magnetic material defining a north pole facing away from the carrier support structure, and a second and opposite major surface of a magnetic material defining a south pole facing away from the carrier support structure. A reflective surface, or metal foil, is disposed adjacent the magnetic poles to deflect radiation. The layers are repelled from one another without the use of spacers. In various embodiments, the magnetic material is a permanent magnet selected from the group consisting of Samarium-Cobalt, Alnico, Neodymium-Iron-Boron, an alloy of the Lanthanide group of elements, and mixtures and alloys thereof.

A portable cooler having one or more ice sheets including built-in refrigerant cubes. The cooler comprises an outer fabric shell and one or more sets of spaced apart refrigerant cubes encapsulated in plastic to form ice sheets that are attached to the interior walls of the cooler. The walls of the cooler may also include one or more layers of thermal insulation. The ice sheets provide a visually pleasing appearance to the inside of the cooler suggestive of cooling effects. The ice sheets may be retained along the walls of the cooler by seams sewn along the lanes passing between the refrigerant cubes, by being retained in pockets formed by sidewall liners or be being secured into chambers defined by the cooler's outer walls and a plastic insert fitted into the cooler.

The invention deals with insulation with improved separability from the processed broken stone designed as single-layer or multi-layer insulation surrounding an electric conductor where the principle is that at least one layer of the insulation is made of magnetic material and at the same time at least one layer is made of electrically non-conductive material. This magnetic material is beneficially produced as a mixture of the magnetic and non-magnetic main material component while it is especially advantageous if the content of the magnetic main material component in individual insulation layers is 5 to 60% of weight and the rest to 100% consists of the non-magnetic main material component, all related to the weight of individual layers, or even better, if the content of the magnetic main material component of individual insulation layers is 10 to 30% of weight, related to the weight of individual insulation layers. The magnetic main material component is beneficially produced on the basis of magnetite —Fe3O4, or on the basis of ferrite with the general formula MeIIFe2O4, where Me represents Co, Mn, Ni, Ca, Cu, Zn, Mg, or ferrite with the general formula LnIIFe2O4, where Ln represents noble earth elements, or on the basis of noble earth elements in the oxidation degree II, or on the basis of ferric oxide in the modification γ-Fe2O3, or on the basis of powder iron, or on the basis of a magnetic alloy of iron or on the basis of a mixture or alloy containing the above mentioned magnetic partial components, where advantageous magnetic alloys of iron are alloys containing at least noble earth elements, or especially advantageous magnetic alloys of iron are alloys containing at least another noble earth element and B and / or Co while advantageous metallic noble earth elements are Nd and Sm. Or the magnetic main material component is made on the basis of magnetically hard materials of the AlNiCo or FeCoCr type. The non-magnetic main material component is beneficially produced on the basis of plastic material, advantageously selected from the group of polymers or copolymers, mainly from the group of elastomers as silicone or butadienstyrene rubber or plastic materials as PVC, PE, PP, or PTFE.

A multi-layer insulation system for electrical conductors, an insulated electrical conductor, a process for preparing an insulated conductor, and an insulated conductor prepared by such a process are provided. The insulated electrical conductors are lightweight, qualify for temperature ratings of up to approximately 230 DEG C, and demonstrate mechanical durability and hydrolysis resistance. As such, these insulated conductors are particularly useful for aircraft wire and cable.

A multi-layer insulation (MLI) blanket with enhanced contamination inhibiting properties and a method for inhibiting the formation of organic residues on the outer surface of a MLI blanket are provided. In one embodiment, a MLI blanket (10) attachable to a spacecraft or other structure includes a plurality of metallized layers (20, 30, 40, 50) separated by mesh layers (60, 62, 64). An anti-contamination coating (80) comprised of a photocatalytic material is disposed between a high emittance layer (70) that overlies the outer surface (20A) of the outer metallized layer (20) and an outer electrically conductive layer (90). When exposed to ultraviolet or near-ultraviolet radiation components present in solar radiation, the anti-contamination coating (80) catalyzes the breakdown of organic residues on the outer surface of the MLI blanket (10) thereby maintaining the reflective properties of the MLI blanket (10) and ensuring that solar absorptance of the MLI blanket (10) is maintained at or below an acceptable threshold level.

The present invention involves a low-temperature insulating paper, and relates to a preparation method of said low-temperature insulating paper and its applications. The invention prepares the low-temperature insulating paper with superfine alkali-free glass fiber and wet paper preparation process; the definite quantity of said low-temperature insulating paper is 10-20 g / m2 and the thickness is 0. 06 - 0. 09 g / m2. The preparation method of said low-temperature insulating paper includes: beating, stirring and scattering the superfine alkali-free glass fiber, and drying after stripping in paper machine, last coiling and preparing the products. The low-temperature insulating paper in the invention can be used for vacuum multi-layer insulation structure of copious cooling liquid accumulating container and complement pipes. The low-temperature insulating paper in the invention has good adiabaticity, the degassing ratio is small in vacuum, the profiling performance is good, and it has long life and wide uses.

The thermal control method of the non-attitude satellite, paste or spray the high-emissivity thermal control coating on the equipment in the star, fill the thermal conductive filler between the equipment installed on the partition and the installation surface, and spray the high-emissivity thermal control coating on the inner surface of the rest of the structure star Floor. The inner surface of the cabin board is covered with multi-layer heat insulation components to reduce the impact of drastic changes in heat flow outside the outer orbit of the star. Except for the installation surface of the instrument and equipment, the structural star module is pasted with third-order gallium arsenide solar cells. From the perspective of top-level system design, the present invention is based on the whole star isothermal design idea, fully utilizes the whole star structure heat storage, and utilizes solar cells as energy supply equipment and temperature control means at the same time, and adopts three-dimensional direction 3D isothermal heat pipe combination and integration The 3D isothermal device composed of a metal frame solves the problem of ensuring the temperature level of the entire satellite when there is no attitude control.

The invention discloses a vacuum heat insulating low-temperature pipe joint, which comprises inner pipes for low-temperature liquid to flow through and outer pipes sleeved outside the inner pipes and connected with the inner pipes, wherein a vacuum space is formed between each inner pipe and each outer pipe; spliced positions of the two inner pipes are welded together through a bushing; heat preserving barrels are sleeved on the joints of the two outer pipes; the two end parts of each heat preserving barrel are provided with a welded loop which is welded with the outer walls of the outer pipes respectively; a section of internal heat isolating pipe and a section of external heat isolating pipe which are sleeved together and extend towards the two outer sides are arranged between the end parts of the joints and the inner pipe walls of the two outer pipes respectively to constitute a vacuum interlayer enclosed space between the inner pipe and the outer pipe; a plurality of vacuum heat insulating layers are formed outside the bushing at the spliced position of each inner pipe; a steel wire is arranged outside the heat insulating layers for fixing; and the heat preserving barrel at the joint of each outer pipe is provided with a vacuumizing valve. The vacuum heat insulating low-temperature pipe joint has the characteristics of low heat leakage, simple and attractive appearance andthe like.

The invention discloses an actively-shielding type experiment device of a low-temperature superconducting magnet system. The actively-shielding type experiment device comprises a vacuum sealing tank, a multi-layer heat insulating layer, an anti-radiation copper screen, a refrigerating machine, superconducting coils, a cold guide mechanism, suspended rod supporting mechanisms and a gas collection plate. The multi-layer heat insulating layer is located in the vacuum sealing tank, the anti-radiation copper screen is located in the multi-layer heat insulating layer, the superconducting coils are located in the anti-radiation copper screen and suspended onto a flange of the vacuum sealing tank through the suspended rod supporting mechanisms, a first-level cold end of the refrigerating machine located outside the vacuum sealing tank penetrates through the vacuum sealing tank, is in hot connection with the anti-radiation copper screen and provides cooling capacity, and a second cold end of the refrigerating machine penetrates through the anti-radiation copper screen and is connected with the superconducting coils through the cold guide mechanism, and the gas collecting plate is arranged on the first-level cold end of the refrigerating machine. By means of the actively-shielding type experiment device, the magnetic field environment outside the superconducting magnet coils can be actively shielded, the structure of the low-temperature superconducting magnet system is greatly simplified, flux leakage of a central magnetic field is lowered, and the shielding effect outside the low-temperature superconducting magnet system is improved.

The invention discloses a heat-insulating connection device for metal surfaces in space. The upper metal surface [5] and the lower metal surface [7] are connected by bolts [9] and nuts [3]. The upper metal surface [5] and the lower metal surface [7] are connected by bolts [9] and nuts [3]. The joints between the bolts [9] between the lower metal surfaces [7] are partially padded with glass fiber reinforced plastic pads [4], and the rest of the area is filled with multi-layer heat insulation components [6]. The imide heat-insulating bushing [8], the nut [3] and the upper metal surface [5] are sheathed with a fiberglass washer [1] and a spring washer [2]. The invention solves the problem of heat isolation between space metal surfaces, and achieves beneficial effects such as low cost, high reliability, and good heat insulation effect.

A multilayer insulation material is provided. The insulation material preferably includes a plurality of substantially air-impermeable material layers joined together, with at least one space being provided between a pair of adjacent material layers thereof. At least one layer of a foam material and / or aerogel material can be interposed between a pair of adjacent material layers. At least one reflective layer can be provided for inhibiting radiative heat transfer across the insulation material. In accordance with another aspect of the disclosure, a construction panel is provided, having a structural panel portion having predetermined material properties for performing a predetermined function, and a plurality of substantially air-impermeable material layers joined to the structural panel portion, at least one space being provided between a pair of adjacent material layers thereof.

A scissor type magnetic sensor having an improved back edge bias structure. The back edge bias structure extends beyond the sides of the sensor stack for improved bias moment and is formed on a flat topography that provide for improved magnetic biasing. The sensor is formed by a method that includes first defining a sensor width and then depositing a multi-layer insulation layer that includes a dielectric layer that is resistant to ion milling and the depositing a fill layer over the dielectric layer that is removable by ion milling. After the multi-layer insulation layer has been deposited the back edge (i.e. stripe height) of the sensor is formed by masking and ion milling. This ion milling removes portions of the non-magnetic, electrically insulating fill layer that extend beyond the stripe height and beyond the sides of the sensor, leaving the dielectric layer there-beneath.

A dielectric region, such as a ferroelectric dielectric region of an integrated circuit capacitor, is protected by a multi-layer insulation structure including a first relatively thin insulation layer, e.g., an aluminum oxide or other metal oxide layer, and a second, thicker insulating layer, e.g., a second aluminum oxide or other metal oxide layer. Before formation of the second insulation layer, the first insulation layer and the dielectric preferably annealed, which can increase a remnant polarization of the dielectric region. The first insulation layer can serve as a hydrogen diffusion barrier during formation of the second insulation layer and other overlying structures. In this manner, degradation of the dielectric can be reduced. Devices and fabrication methods are discussed.

The invention discloses a low-temperature propellant in orbit zero-evaporation passive adiabatic storage tank. The low-temperature propellant in orbit zero-evaporation passive adiabatic storage tank includes an inner container and an outer container, the inner container and the outer container are connected and supported by a support rod, a sandwich cavity is formed between the inner container andthe outer container, and the outer wall surface of the outer container is wrapped with a multi-layered adiabatic layer; the inner container is connected with a first filling pipe and a first discharge pipe, a first regulating valve is mounted on the first filling pipe, and a first safety valve is mounted at the outlet of the first discharge pipe; the sandwich cavity is connected with a second filling pipe and a second discharge pipe, a second regulating valve is mounted on the second filling pipe, and a second safety valve is mounted on the outlet of the second discharge pipe; the multi-layered adiabatic layer is composed of metal reflective screens and non-metal spacers or adopts the constitution of alternating the metal reflective screens with local fasteners; and the metal reflective screens can adjust the voltage to change the emissivity of an emission screen. The variable emissivity reflective screens and fluid heat storage of the sandwich cavity are adopted to regulate the storage tank through the directions of heat transfer of a shadow area and a light area and the distribution relationship, and lossless storage of a low-temperature propellant in space is realized.

The invention discloses an oil-immersed type sleeve multilayer insulation non-uniform damping experimental method. The method comprises that firstly, an oil-immersed type sleeve multilayer insulationnon-uniform damping experimental platform is built, after the frequency domain characteristic parameters of an oil-immersed type sleeve are obtained, the weight factor at the characteristic frequencypoint is obtained through calculation, so that a damping state evaluation weight index is determined, sleeve damping state parameters are estimated based on the frequency domain characteristic quantity, and furthermore, the damping state of the test sample is estimated to achieve the purpose of controlling the damping state of the test sample. The experimental method and platform provided by the invention can realize the multi-layer insulation controllable non-uniform damping of the oil-immersed type sleeve.

The invention provides a low-temperature composite heat insulation layer, a preparation method thereof and application of the low-temperature composite heat insulation layer in a vehicle-mounted low-temperature hydrogen storage tank. The composite heat insulation layer comprises a hollow microsphere layer and a multi-layer heat insulation layer; the hollow microsphere layer comprises a support body and hollow microsphere powder; the support body is filled with the hollow microsphere powder to form the hollow microsphere layer; and the multi-layer heat insulation layer comprises at least one of a uniform-density multi-layer heat insulation material layer, a variable-density multi-layer heat insulation material layer, a uniform-density integrated heat insulation film and a variable-density integrated heat insulation film. According to the composite heat insulation layer, the hollow microsphere layer and the multi-layer heat insulation layer are used in a composite mode, and the advantages of the two heat insulation layers are exerted. In high vacuum, hollow microspheres in point contact can prolong a solid heat conduction path and reduce solid heat transfer to the maximum extent. The multi-layer heat insulation layer can effectively block radiation heat transfer. The two heat insulation layers are matched to prepare the composite heat insulation layer, and the composite heat insulation layer has more excellent heat insulation performance.

A high-heat-retention ladle for carrying molten aluminum includes a ladle body defining therein a storage space, which contains molten aluminum therein, the ladle body including a molten metal inlet and a molten metal outlet, which allow the storage space to communicate with outside, a cover opening and closing the inlet of the ladle body, and a stopper opening and closing the outlet of the ladle body. Each of the ladle body and the cover has an outer shell, which defines a contour thereof, and a multi-layer insulation structure inside the outer shell. The multi-layer insulation structure includes two or more refractory layers. The molten aluminum contained inside the storage space has a temperature drop rate of 5° C. / min or less. It is possible to carry the molten aluminum for a long time in a heat-insulated state and cast a product by directly pouring the molten aluminum into a mold.

A multi-layer insulation (MLI) blanket with enhanced contamination inhibiting properties and a method for inhibiting the formation of organic residues on the outer surface of a MLI blanket are provided. In one embodiment, a MLI blanket (10) attachable to a spacecraft or other structure includes a plurality of metallized layers (20, 30, 40, 50) separated by mesh layers (60, 62, 64). An anti-contamination coating (80) comprised of a photocatalytic material is disposed between a high emittance layer (70) that overlies the outer surface (20A) of the outer metallized layer (20) and an outer electrically conductive layer (90). When exposed to ultraviolet or near-ultraviolet radiation components present in solar radiation, the anti-contamination coating (80) catalyzes the breakdown of organic residues on the outer surface of the MLI blanket (10) thereby maintaining the reflective properties of the MLI blanket (10) and ensuring that solar absorptance of the MLI blanket (10) is maintained at or below an acceptable threshold level.

The invention relates to a shockproof structure of a high-precision small-torque standard device. Three jacks are distributed under a marble base for fixing the high-precision small-torque standard device and a glass protective cover evenly, and a layer of elastic shock insulation materials are arranged between the jacks and a concrete base. The concrete base is provided with a shockproof ditch, the glass protective cover covers the high-precision small-torque standard device and is made of double layers of glass, a film is attached between double layers of glass, a movable door allowing the device to be adjusted manually and conveniently is arranged on the glass protective cover, and silicon sheets are attached around the movable door. By means of multi-layer insulation design, ground shock can be effectively prevented. By means of three-point type structural design, the base of the device can be ensured to be horizontal and stable while shock is prevented. By means of the multi-layer glass protective cover with the film, influence caused by air flowing is prevented, and electrostatic influence can be shielded. Therefore, the effective and comprehensive shockproof technology is provided.

The invention provides a large vacuum heat-insulation liquid hydrogen transportation device. The invention aims at solving a defect that with small transportation capacity and high safeguard requirements of existing rail transportation methods, a demand of short-distance large-capacity transport cannot be satisfied. The device provided by the invention comprises a low-temperature vacuum multi-layer insulation-structured 300m<3> liquid hydrogen storage tank and an automatic multi-mode steering transportation vehicle. The low-temperature vacuum multi-layer insulation-structured 300m<3> liquid hydrogen storage tank is arranged on the automatic multi-mode steering transportation vehicle. The large vacuum heat-insulation liquid hydrogen transportation device provided by the invention has functions of liquid hydrogen short-distance transportation, long-time storage, trans-filling, and filling. The large vacuum heat-insulation liquid hydrogen transportation device has the characteristics of large capacity, good heat-insulation performance, and convenient and flexible transportation. The transportation vehicle has built-in power, and can perform functions such as multi-mode arbitrary steering, front-and-back driving, platform upward-downward elevation, and the like. With a road transportation mode, 300m<3> of liquid hydrogen can be transported to an application site one time, such that subsequent application demands can be satisfied.

The invention discloses a high-water resistance control cable. The high-water resistance control cable comprises a circular insulation reinforced tube; a Y-shaped insulating separation plate is arranged inside the insulation reinforced tube; four insulating separation plate are radially and uniformity arranged on the outer wall of the insulation reinforced tube; two arc-shaped separation plates One are connected between the two insulating separation plates on the left side; two arc-shaped separation plates Two are connected between the two insulating separation plates on the right side; three main wire cores are arranged between the Y-shaped insulating separation plate and the inner wall of the insulation reinforced tube; and each main wire core includes a main conductor as well as a trifluoropropyl fluorinated silicone rubber insulation layer and a semi-conductive shielding layer which successively coat the outer side of the main conductor. According to the high-water resistance control cable of the invention, control wire cores are provided with oval rubber frames; and connection plates are connected between the left side of each oval rubber frame and one insulating separation plate adjacent to the left side of the corresponding oval rubber frame as well as the right side of each oval rubber frame and one insulating separation plate adjacent to the right side of the corresponding oval rubber frame, and therefore, the high-water resistance control cable has the advantages of compact structure, strong load-bearing capacity, little possibility of being fractured, multi-layer insulation and shielding, stable and reliable work and great buffering anti-vibration effect of semi-conductive expansion buffer layers.