43results about How to "Achieve thermal protection" patented technology

The invention discloses a slag combined type centrifuging and air quenching granulating plant with a thermal protection function and a method. The slag combined type centrifuging and air quenching granulating plant with the thermal protection function comprises a slag storage bin, a material injecting pipe, a granulating bin and a slag outlet, wherein the material injecting pipe is located on the lower portion of the slag storage bin, and the slag outlet is formed in the lower portion of the granulating bin; the slag combined type centrifuging and air quenching granulating plant with the thermal protection function is characterized in that a centrifuging and air quenching granulator is arranged inside the granulating bin, the centrifuging and air quenching granulator is located below the material injecting pipe, the top of a hollow rotating shaft is fixedly sleeved with the centrifuging and air quenching granulator, a sealing part is sleeved with the bottom of the hollow rotating shaft, the hollow rotating shaft communicates with an air outlet of a draught fan through the sealing part, and the hollow rotating shaft is driven by a motor; and a plurality of fins are arranged on the surface of the centrifuging and air quenching granulator 4, a plurality of air-quenching-wind nozzles communicating with the inner portion of the centrifuging and air quenching granulator are arranged on the periphery of the top of the centrifuging and air quenching granulator in the circumferential direction, and the air inlets of the air-quenching-wind nozzles are located at the inner side of the centrifuging and air quenching granulator. The slag combined type centrifuging and air quenching granulating plant with the thermal protection function can be widely applied to the fields of steel, metallurgy and the like.

The invention discloses a direct-drive combined engine flow channel adjustment structure and a control method thereof, comprising a plurality of electromagnetic direct drive units; the electromagnetic direct drive unit includes a stator and a mover; each stator is embedded and installed inside the flow channel body, And symmetrically distributed on the two side walls of the flow channel body; each mover is embedded in the interior of the adjustable wall plate, and symmetrically distributed on both sides of the adjustable wall plate close to the flow channel body, corresponding to the position of the stator ; By adjusting the alternating current input at the stator, the adjustable wall plate is moved; the present invention adopts the distributed arrangement of multiple electromagnetic direct drive units, which can be carried out with the minimum energy consumption according to the real-time force conditions such as the internal pressure of the flow channel and frictional damping. Distributed direct drive force output, and a complete distributed control scheme, combined engine full-channel multi-component collaborative control process, high structural integration, simple system, greatly improved system operating efficiency, and reduced system structural quality costs.

A gas oxygen / kerosene swirl cooled combustion chamber include a head base, body, nozzle, oxygen and kerosene systems, A main body of that head, a body and a nozzle are fixedly connecte from the top tothe bottom to form an integral structure, a combustion chamber cavity is arrange in the body, oxygen is tangentially injected into the combustion chamber cavity by a gas-oxygen system to form a double-swirling airflow structure of an outer swirl current and an inner swirl current, a kerosene system is connecte to the head, and kerosene is injected into the combustion chamber cavity and oxygen inthe inner swirl region to realize mixed combustion. The invention limits the mixing combustion process of the bipropellant to the central region of the combustion chamber, and achieves the purpose ofcooling the wall surface and preventing carbon deposition through the outer oxygen swirling flow. An open centrifugal nozzle and a rotary adjusting sleeve are designed at the head of the combustion chamber. After the fuel is atomized, the internal swirl region and oxygen are mixed to form a stable recirculation zone near the kerosene nozzle outlet, which ensures the reliable ignition and stable combustion of the propellant. The combustor has simple structure, no cooling, good maintenance performance and low cost.

The invention provides a low-speed cooling water thermal protection device and relates to the technical field of aircraft heat shielding ground testing. The low-speed cooling water thermal protection device comprises a water collecting cavity, a water inlet, a water outlet and water cooling channels. The water collecting cavity is of a hollow cylindrical structure. The water inlet is fixedly installed at one end of the outer wall of the water collecting cavity, and the water outlet is fixedly installed at the other end of the outer wall of the water collecting cavity. The multiple adjacent water cooling channels are arranged between the outer wall and the inner wall of the water collecting cavity in the axial direction of the water collecting cavity. Channel connection of cooling water of the water inlet and cooling water of the water outlet is achieved through the water cooling channels. By the adoption of the subcooled boiling design method, long-term thermal protection on a diffuser in the megawatt-grade thermal environment is achieved at the low flow rate and small pressure, and normal operation of a high-temperature hot gas flow wind tunnel is guaranteed; and long-term thermal protection on the diffuser in the high-temperature thermal structure wing tunnel is achieved, protection on the diffuser in the megawatt-grade thermal environment can be achieved at the low flow rate and small pressure, the difficulty of structural design is lowered, the requirement for cooling water amount is reduced, and normal operation of the gas flow wind tunnel is guaranteed.

The present invention proposes a variable channel ramjet and its design and adjustment method, which includes an air inlet, a combustion chamber and a nozzle. A fixed partition is installed in the combustion chamber to separate the combustion chamber flow channel into a common channel and a Two runners, the end of the fixed partition close to the air inlet is installed with an adjustable partition, the adjustable partition can be rotated, and the change of the engine flow path can be realized by adjusting the position of the adjustable partition. In the present invention, by installing a fixed partition in the combustion chamber and adjusting the adjustable partition connected to it, the flow channel of the engine can be adjusted, and the inlet throat can be adjusted at the same time without setting the nozzle adjustable device. and combustion chamber thermal throat effects.

The present invention provides an equalization circuit and its design method and battery management system, wherein the equalization circuit includes: a control sub-circuit, including a control terminal, a first terminal and a second terminal, the control terminal is used for accessing a control signal, and the control signal is used for Control the conduction state between the first end and the second end; the first series branch includes a first balancing resistor and a first thermistor connected in series, and the first series branch is connected in series between the first end and the battery module between the signal input terminals of the first battery cell; the second series branch includes a second balancing resistor and a second thermistor connected in series, and the second series branch is connected in series between the second terminal and the first battery module Between the signal input terminals of the two battery cells. In this way, if the current in the series branch increases and the temperature of the equalizing resistor rises, the resistance of the thermistor increases rapidly with the temperature rise, so that the current in the series branch decreases, and the temperature of the equalizing resistor decreases accordingly, realizing Thermal protection for battery modules.

The invention discloses a missile-borne dual-frequency active antenna, comprising a structural cavity, an RDSS antenna, a sky-chain antenna, a duplexer, a low-noise amplifier and a connector; The duplexer is fixed in the first cavity of the structural cavity, and the low noise amplifier is installed on the surface of the duplexer; the RDSS antenna and the sky chain antenna are respectively installed in the second cavity spaced from the first cavity. The cavity and the third cavity are electrically connected with the duplexer through the inner conductor connector; one end of the connector is electrically connected with the low noise amplifier, and the other end protrudes from the bottom of the structural cavity to connect external equipment; The structural cavity of the cavity realizes the overall shielding and cavity isolation of the internal components to improve the mutual isolation and anti-interference of the dual antennas; the invention improves the anti-interference ability, reduces the volume of the active antenna and ensures the output Signal quality has the advantages of high integration, low noise figure, high isolation, and high suppression.

The invention relates to magnetic composite microspheres, and a preparation method and application thereof, belonging to the technical field of chemical material preparation. The preparation method comprises the following steps: synthesizing Fe3O4@SiO2-MPS (modified polystyrene); mixing, adding acetonitrile, carrying out ultrasonic dispersion, adding isopropyl acrylamide, glycidyl methacrylate, N,N'-methylene-bis acrylamide and azodiisobutyronitrile, mixing, and carrying out oil-bath heating; distilling to obtain part of acetonitrile, and stopping the reaction; carrying out magnetic separation on the obtained, and repeatedly washing with ethanol and water; and drying in a vacuum drying oven to obtain the product. The product is used for cellulase immobilization. The synthesized magnetic composite microspheres have superparamagnetism, can enhance the enzyme activity restorability and heat stability when being used for cellulase immobilization, and implements thermal protection on the cellulase.

The invention discloses a large-temperature-difference water spray cooling device capable of bearing an ultra-high temperature and relates to the field of ground thermal protection / prevention of aircrafts. The large-temperature-difference water spray cooling device comprises a gas inlet, a first water distribution pipe layer, a second water distribution pipe layer, a high-temperature-resistant barrel and a gas outlet, wherein the gas inlet and the gas outlet are formed in two ends of the high-temperature-resistant barrel respectively; the first water distribution pipe layer is arranged in the position closer to the gas inlet; the second water distribution pipe layer is arranged in the position farther from the gas inlet. The large-temperature-difference water spray cooling device capable of bearing the ultra-high temperature is designed for the first time in China, can work for a long time in an extreme environment at the temperature of 3,600 K, and has the capacity of cooling high-temperature gas to 700 K within 40 milliseconds, wherein the flow of the high-temperature gas is as high as 0.38 million cubic meters per hour. With development of the large-temperature-difference water spray cooling device capable of bearing the ultra-high temperature, construction of a large combustion gas flow test device is possible, and an effective test means is provided for development of a novel aerospace craft.