34 results about "High velocity" patented technology

This invention relates to a method and apparatus for resolving velocity ambiguity based on constant frequency assistance. The method includes the following steps: a radar sequentially transmits a constant frequency band signal and a linear continuously modulated pulse train, and acquires the radar echo signal; both the constant frequency band echo signal and the sawtooth band echo signal are mixed to obtain a constant frequency band intermediate frequency signal and a sawtooth band intermediate frequency signal; the constant frequency band intermediate frequency signal is processed by a fast Fourier transform to obtain a target true velocity estimate; the sawtooth band intermediate frequency signal is sequentially processed by a two-dimensional fast Fourier transform, a two-dimensional constant false alarm rate (CFAR) processing, and a centroid condensation processing to obtain a target range velocity estimate; based on a velocity matching method using a Fourier rotation factor, the target true velocity estimate is matched with the target range velocity estimate to obtain the true velocity of all targets. This method not only resolves velocity ambiguity but also improves velocity accuracy, offering advantages such as high velocity measurement accuracy, high real-time performance, and simplicity.

This application provides a precise ranging and velocity measurement method for hypersonic targets based on one-dimensional imaging detection, comprising: step 10, one-dimensional range imaging of the hypersonic target; step 20, range measurement of the hypersonic target; step 30, coarse velocity estimation of the hypersonic target; and step 40, fine velocity measurement of the hypersonic target. This application provides high ranging accuracy and relatively high velocity measurement accuracy.

Apparatuses, systems, and methods are described herein for high velocity erosion. The apparatus comprises a container, a propellant stored in the container, wherein the propellant is stored under pressure in the container, an applicator, the applicator being in fluid communication with the container, the applicator comprising a heater, and a controller for controlling the heater and the flow of propellant from the applicator, wherein the applicator is structured to discharge the propellant at a high velocity.

This utility model relates to the field of snow blowing technology and discloses a variable vent cross-section snow blowing device, including a fan, a motor, a distributor, upper and lower hydraulic cylinders, a steering hydraulic cylinder, an adjusting screw, a left air duct, a right air duct, a vent flap, a vent adjusting plate, a wind direction adjusting plate, bearings, a connecting seat, a rotating shaft, and a sealing block. The fan and the distributor are fixedly connected by bolts, and the fan is driven by the motor. The distributor's interior adopts a "human"-shaped distribution device, with the left and right air ducts installed on the left and right sides of the distributor, respectively. The left and right air ducts are adjusted up and down by the upper and lower hydraulic cylinders. The vent flaps are installed on the left and right sides of the left and right air ducts, respectively. This utility model achieves functions such as left and right snow blowing adjustment, wind speed and volume adjustment, and vent up and down adjustment by adjusting the vent wind direction, vent height above the ground, and vent cross-sectional area. It can achieve high flow rate or high velocity blowing operations, significantly improving snow removal efficiency and removal rate, and can meet various different operating conditions.

Thermal protection systems for aerospace vehicles, such as hypersonic vehicles or space vehicles, are disclosed herein. In some embodiments, the disclosed thermal protection systems can be used to protect propellant tanks (e.g., composite propellant tanks) and vehicle primary structures (e.g., composite primary structures) from exceeding upper design temperature limits during vehicle ascent, reentry into Earth's atmosphere, and / or high velocity flight through an atmosphere. In some embodiments, a thermal protection system can include a framework of elongated composite members forming a plurality of cells. One or more layers of insulation material such as aerogel can be positioned in each of the cells. The cells can be covered by an external skin of the vehicle. In some embodiments, the framework is attached to a propellant tank and the insulation material is in contact with the external surfaced of the propellant tank.

This invention relates to the field of waste heat recovery technology and discloses a plate heat exchanger capable of waste heat recovery, comprising a first connecting plate, several connecting columns fixedly connected to the inner wall of the first connecting plate, a second connecting plate fixedly connected to the end of the connecting columns away from the first connecting plate, and several metal plates placed between the first connecting plate and the second connecting plate. Because the liquid flowing in from the hot water inlet has a relatively high velocity, the edge of the fluid will contact the spiral plate. The fluid at the edge will be guided by the spiral plate, causing the outer layer of liquid to flow along the outer wall of the spiral plate. This will cause the outer fluid to start rotating. When the liquid flows out from the hot water inlet, the fluid near the inner wall of the hot water inlet will flow out in a diffused manner, allowing the fluid at the edge to enter the nearest metal plate first. In this way, it is prevented that the fluid velocity is too high, and the liquid cannot enter the interior of each metal plate evenly, thereby resulting in low heat exchange efficiency.

A processing module may be centralized and coupled to multiple inputs from customers, and behave deterministically, e.g., programmed to depend on state, inputs and outputs. The rapid speed of automated trading systems implementing such a centralized, deterministic module, where all users can access a central limit order object, can quickly result in an object state that does not reflect a true consensus or desirable state. Accordingly the resulting problem is a problem arising in computer systems due in part to the high speeds of computer systems. The solutions disclosed herein are, in one embodiment, implemented as automatic responses and actions by a computing system.

Systems and methods for non-invasive ventilation are provided. The systems may include a gas source that provides breathing gases to a patient through one or more of a primary flow path (PFP) and a flushing flow path (FFP). The system may include a control assembly configured to open and restrict gas flow through the PFP. When the PFP is open, a significant portion of the gas flows through the PFP while the remaining gas flows through the FFP. When the PFP is restricted, a significant portion of the gas flows through the FFP. Increased flow through the FFP may have a high velocity (especially relative to the flow through the PFP). Gas delivered through the FFP may be used to flush dead space. One or both flow paths may contribute to inspiratory positive airway pressure (IPAP), expiratory positive airway pressure (EPAP), and / or positive end expiratory pressure (PEEP).

The utility model discloses an interface cleaning high-speed fluid jet device which comprises a gun barrel and a telescopic pipe, the gun barrel is provided with a connector arranged at the tail end of the gun barrel, a holding handle a arranged on the side face of the gun barrel and a clamping ring arranged on the side face of the gun barrel, and the connector is connected with an external high-pressure air pump. The telescopic pipe is slidably nested at one end of the gun barrel and provided with a holding handle b arranged on the side face of the telescopic pipe, a sliding frame slidably arranged in the holding handle b and a spring arranged at the top end of the sliding frame, the spring is located between the sliding frame and the holding handle b, and the sliding frame is connected with the clamping ring in a clamped mode. The telescopic pipe slides along the front end of the gun barrel to change the spraying range of the device. The gun barrel and the telescopic pipe are arranged, the telescopic pipe can slide forwards along the front end of the gun barrel, meanwhile, the sliding frame is pushed by the spring to move, the sliding frame is connected with the gun barrel in a clamped mode, and therefore the position of the telescopic pipe is fixed, and the spraying angle of the device is increased.

This invention discloses a jet microchannel heat sink, comprising a shell, which is divided into a lower microchannel layer and an upper jet generating layer by a layered plate. Several pairs of first ribs are spaced apart in each microchannel to enhance the disturbance of the fluid on the wall and near the jet orifice. A pair of second ribs is also provided between adjacent first ribs to disturb the fluid between adjacent jet orifices, resulting in a higher fluid velocity near the second ribs and helping to reduce the temperature in the middle region between adjacent jet orifices. The jet generating layer also includes several jet dispersing ribs to disturb the fluid flowing in through the jet inlet, solving the problem of uneven jet distribution. Furthermore, the structure of this invention can incorporate crossflow, and by improving the jet orifice diameter distribution, the fluid in the latter half of the microchannel still has a high velocity after the crossflow mixes with the jet, carrying away more heat and making the temperature distribution of the microchannel more uniform.

A method of providing channel state information (CSI) reference signal (RS) configuration is proposed to support high velocity in new radio (NR) systems. A CSI-RS resource can be configured with a bursty period in which the same CSI-RS resource is repeatedly transmitted over time. Any two repetitions of the CSI-RS resource are not overlapped in time. For periodic and semi-persistent CSI-RS, the repetitions of CSI-RS in the bursty period can be signalled by radio resource control (RRC) signaling. For aperiodic CSI-RS, the CSI-RS repetitions in the bursty period can be indicated by the triggering downlink control information (DCI). UE can acquire Doppler-domain information based on the CSI-RS repetition to facilitate high velocity scenarios in 5G NR systems.

Systems and methods are disclosed for Channel Quality Indicator (CQI) reporting. In one embodiment, a method performed by a User Equipment (UE) comprises receiving, from a network node, first signaling that indicates a precoding matrix duration in time domain and receiving, from the network node, second signaling that indicates a number of precoder matrix durations wherein each precoder matrix duration is associated with a precoder matrix. The method further comprises receiving, from the network node, third signaling that indicates one or more CQI resolutions in time domain for one or more CQIs. The method further comprises reporting, to the network node, Precoding Matric Indicator (PMI) for the number of precoder matrix durations and reporting, to the network node, one or more CQIs according to the indicated one or more CQI resolutions in time domain. In this manner, feedback of CQI is enabled for, e.g., high-velocity UEs.

The method for designing an autopilot controller for flying objectives (FOs) that adapts to velocity, altitude, and overload consists of two parts: part I focuses on determining the initial controller, and part II focuses on determining the adaptive controller. This method eliminates transfer function zeros, prevents continuous integration, and limits the control signal to ensure the operational conditions of the control loops. The use of a unified control structure allows for a consistent design and tuning process across all three control channels, thereby generalizing the control problem. The solution ensures strong adaptability across a wide range of flight scenarios for FOs, particularly those operating at high velocities, with high overload, and continuously changing altitudes.

The present invention is for removing carbon from the induction system of an internal combustion engine. The device uses a restriction to accelerate the chemical fluid while air is bled into a high velocity chemical stream. This provides a means to break up the chemical into very small chemical droplets that can be suspended in the airflow moving into the engine. Thus, carrying the droplets of chemical to the carbon deposits within the induction system and combustion chambers. This atomizer works to produce a chemical fog into the running engine so the induction system and combustion chambers can be properly cleaned.

The invention relates to a method for preparing a thermal barrier coating interface three-dimensional texture with the assistance of a mask plate, and the method comprises the following steps: depositing a texture layer on the surface of a bonding layer by adopting a metal mask plate auxiliary spraying technology: placing a metal mask plate, and then carrying out plasma spraying or high velocity oxy-fuel spraying on the surface of the bonding layer to obtain the thermal barrier coating interface three-dimensional texture with the assistance of the metal mask plate; and a texture layer is prepared on the surface of the bonding layer through spraying, and after the metal mask plate is removed, the three-dimensional texture of the needed structure is obtained. Compared with the prior art, in the spraying process of the bonding layer, a layer of metal mask plate is added on the surface of the bonding layer, rapid and simple three-dimensional texture construction is achieved in a continuous spraying mode, and therefore the stability of the coating is improved, and the service life of the coating is prolonged.

The application relates to a waterless photovoltaic cleaning unmanned aerial vehicle based on a dust accumulation mechanics model, and belongs to photovoltaic panel cleaning. The speed-increasing flow-increasing duct drives the high-speed downward airflow generated by a brushless motor and a propeller to be plasticized to generate high-speed airflow. The outlet airflow velocity is effectively increased based on the flow-increasing speed-increasing duct, the dust accumulation mechanics model and the removal condition of adhered particles. The high-speed airflow after speed increase has high velocity and cleaning effect, and can effectively remove the dust and dirt on the surface of a photovoltaic panel. On the other hand, the application adopts an edge straight line detection image processing technology to position a cleaning area in view of the unmanned aerial vehicle vision and path planning problem. In addition, four groups of notches are designed at the bottom side of the speed-increasing flow-increasing duct to ensure the stability of the unmanned aerial vehicle in high-load operation. The carbon plate connecting assembly of the application uses high-strength and light-weight carbon fiber material, which can not only bear large stress, but also reduce the overall weight, improve the flight efficiency and endurance.

This utility model discloses a dust suppression and collection device and an electrostatic precipitator. The dust suppression and collection device includes a dust suppression plate, which is disposed on the side of the anode plate of the electrostatic precipitator near the dust flow outlet. The end of the dust suppression plate extends between two adjacent anode plates and is arc-shaped, extending towards the channel between the anode plates. Based on the configuration of the dust suppression plate, dust flow near the anode plate surface, upon reaching the dust suppression plate, will form a local backflow counterflow, expanding the low-velocity area on the surface and guiding the high-velocity area to the center of the channel. On the one hand, the capture time of charged dust particles is effectively increased, while the cathode wire in the center of the channel is less prone to dust accumulation under high velocity, thus simultaneously improving discharge stability. In practical applications, the plate-shaped dust suppression plate design also avoids the defect of increased load on the anode plate due to dust accumulation in through-holes.

An air handler assembly provides an air handler that resides completely on a drain pan, and comprises multiple panels. At least two panels join at the edges to form an enclosed chamber with central region. Two of the opposing panels are apertured to enable passage of air. Multiple coils carrying cooling fluid are disposed in a parallel relationship, and on the inner side, of the coil panels. A blower forces high velocity air through one or more opposing coil panels, and across the coils to cool the air. From the coils, cooled air flows to central region of air handler. A fan at the top of the air handler draws the cooled air from an outlet opening that forms in a top panel for dispersing through a duct or plenum.

The utility model relates to a high-temperature high-speed airflow contact type temperature measurement high-temperature probe, which is characterized in that a first detection galvanic couple is exposed when being close to one end of an opening of a protective shell, so that the first detection galvanic couple is in contact with an external environment, and the temperature of the external environment is further detected; the first detection galvanic couple and the second detection galvanic couple are separated from each other, and meanwhile, the second detection galvanic couple is exposed when being close to one end of the opening of the protective shell, so that the second detection galvanic couple is in contact with the external environment and is further used for detecting the temperature of the external environment, and a certain distance exists between the detection position of the first detection galvanic couple and the detection position of the second detection galvanic couple. Therefore, the detection result of the first detection galvanic couple and the detection result of the second detection galvanic couple form a data gradient difference, so that extreme data can be conveniently removed, and the accuracy of the detection result is improved.

A sensor assembly mounted on a body panel of a vehicle comprises a sensor housing defining a chamber therein and a sensor housed inside the chamber and facing a vehicle-forward direction. The sensor assembly further comprises a garnish supported on the body panel and coupled to the sensor housing, such that the chamber is formed between the garnish and the sensor housing. The garnish comprises a first region configured to receive high velocity air from the exterior of the vehicle and a ramp region inclined to the first region and extending from a portion of the first region towards a vehicle-rearward direction away from the sensor. The ramp region is configured to receive a first portion of the high velocity air from the first region, such that the ramp region guides the first portion of the high velocity air towards the vehicle-rearward direction away from and over the sensor.

Systems and methods for indication of Non-Zero Coefficients (NZCs) in a codebook for User Equipments (UEs) are disclosed. In one embodiment, a method performed by a UE comprises generating Channel State Information (CSI) comprising NZCs of a set of linear combining coefficients, wherein the set of linear combining coefficients are associated with a number, L, of selected Discrete Fourier Transform (DFT) basis vectors in spatial domain (SD), a number, M, of selected DFT basis vectors in frequency domain (FD), and MvDD selected DFT basis vectors in Doppler Domain (DD). The CSI further comprises, for each reported layer, a set of MvDD NZC bitmaps that indicates positions of the NZCs, wherein the set of MvDD NZC bitmaps comprises a separate bitmap for each selected DFT basis vector in DD in the set of MvDD selected DFT basis vectors in DD. The method further comprises reporting the CSI to a network node.

The invention discloses a high-speed plasma spraying gun and method for ceramic materials. The high-speed plasma spraying gun comprises a shell, a control panel, an accelerated spraying unit, a stirring and feeding unit and a clamping nozzle. The control panel is fixed to the shell and used for controlling work of the plasma spraying gun. The accelerated spraying unit is fixed in the shell and comprises a spraying acceleration pipeline, and a cathode block, a plurality of acceleration magnet rings, an anode block and a condensation pipeline which are sequentially arranged on the spraying acceleration pipeline; the spraying acceleration pipeline comprises a feeding end and a discharging end, the feeding end is communicated with the stirring and feeding unit through a feeding pipeline, and the discharging end is communicated with the clamping nozzle; the cathode block and the anode block both partially extend into the spraying acceleration pipeline; the multiple acceleration magnet rings and the condensation pipeline are arranged on the spraying acceleration pipeline in a sleeving mode. The stirring and feeding unit is fixed in the shell and used for stirring and smashing raw materials and conveying the raw materials to the accelerated spraying unit. And the clamping nozzle is fixed on the outer wall surface of the shell. The device is more compact and uniform in spraying and more convenient to use.

Systems and methods of Channel State Information (CSI) reporting with Type II codebook for high velocity are provided. In some embodiments, a method includes determining when to apply Doppler domain compression and when to avoid Doppler domain compression when feeding back a CSI report; determining a signaled number of CSI instances, for which the network node requests the User Equipment (UE) to compute CSI; and based on the number of CSI instances, determining whether to apply CSI compression in the Doppler domain or not. Some solutions proposed allow the possibility for the network and the UE to support cases with Doppler domain compression and without Doppler domain compression under a single CSI reporting framework. Based on the signaling received from the network, the solutions allow the UE to determine when to feedback selected Doppler domain bases and when to avoid Doppler domain bases selection in the Type II CSI report.

A method for repairing damage at a damage site on the surface of a nickel- or cobalt-based alloy. The method includes: machining at the damage site; and applying a high entropy alloy (HEA) repair material to the damage site via high velocity oxy-fuel (HVOF) spray, high velocity air-fuel (HVAF) spray, or cold spray.

The invention relates to the technical field of surface strengthening, in particular to a composite protective layer, a preparation method of the composite protective layer and a water turbine flow passage component. The composite protective layer sequentially comprises a nickel-based anti-cavitation laser cladding layer, a nickel-based anti-cavitation laser cladding layer, a nickel-based anti-cavitation laser cladding layer, a nickel-based anti-cavitation laser cladding layer, a nickel-based anti-cavitation laser cladding layer, a nickel-based anti-cavitation laser cladding layer and a nickel-based anti-cavitation laser cladding layer, the nickel-based anti-cavitation-erosion laser cladding layer is used for providing anti-cavitation-erosion performance and is made of a nickel-based alloy material containing chromium, molybdenum and titanium elements; the high velocity oxy-fuel WC silt-wear-resistant coating is arranged on the surface of the nickel-based cavitation-erosion-resistant laser cladding layer, and the high velocity oxy-fuel WC silt-wear-resistant coating is used for providing silt-wear-resistant performance; and a metallurgical bonding transition area is formed between the nickel-based cavitation-erosion-resistant laser cladding layer and the high velocity oxy-fuel sprayed WC silt-wear-resistant coating, so that the overall stability of the composite protective layer is improved. The problems of low bonding strength or easy cracking and the like existing in a single protection technology are solved by constructing a system combining cavitation erosion resistance of the bottom layer and wear resistance of the surface layer.

A method of manufacturing a substrate includes, after depositing an exterior layer on a substrate and before polishing an exposed surface of the exterior layer of the substrate, hydrojet treating a selected portion of the exposed surface to remove material from the selected portion by directing a treatment liquid from a nozzle onto the selected portion at a sufficiently high velocity, thickness unevenness of the outer layer is reduced. Then, the outer layer of the treated substrate is subjected to chemical mechanical polishing to planarize and reduce the thickness of the outer layer.

A metal alloy and that includes an enhancement coating material. The metal alloy includes rhenium and one or more additives. The enhancement coating is at least partially applied to the metal alloy by a physical vapor deposition (PVD) process, a chemical vapor deposition (CVD) process, an atomic layer deposition (ALD) process, a plasma-enhanced chemical vapor deposition (PE-CVD) process, ion implantation, direct energy deposition (DED), and / or thermal spray techniques like plasma arc spraying, flame spraying, high velocity oxy fuel spraying (HVOF). The enhancement coating is formed of a) 35-95 wt. % zirconium and wherein said enhancement coating includes ZrN, ZrNC, ZrOC or a combination of ZrN and ZrO2, b) 20-85 wt. % titanium and one or more of carbon, nitrogen, oxygen, rhenium, and silicon, c) 40-85 wt. % chromium and one or more of carbon, nitrogen, oxygen, rhenium, and silicon, or d) at least 60 wt. % carbon.

This invention relates to the field of flame spraying, specifically to an alloy coating based on low-temperature supersonic flame spraying and its preparation method. This invention overcomes the problems of carbide decarburization and excessive residual tensile stress in traditional high-temperature spraying. It involves preparing rare-earth-modified Cr3C2-NiCr core-shell structured composite powder; fabricating an array of micro-pit textures on the blade substrate surface using nanosecond lasers; employing a low-temperature supersonic flame spraying process with nitrogen cooling flow to control flame temperature and suppress carbide decomposition while achieving high-speed particle deposition; and supplementing this with in-situ ultrasonic micro-forging and vacuum sealing heat treatment. The alloy coating of this invention can be used for turbine blade protection, extending the service life of the turbine unit through synergistic innovation in material modification, low-temperature processing, and stress control.

The utility model relates to combustion chamber cooling technical field, specifically disclose a kind of high-pressure combustion chamber cooling device for supersonic flame spraying, it include: base, the top of base is fixedly connected with water tank, the top of base is fixedly connected with support, the inside of support is fixedly connected with combustion chamber, the surface of combustion chamber is fixed and has sleeve ring, the inside of combustion chamber is equipped with inner chamber, the inside of combustion chamber is equipped with cooling cavity, the side of water tank top is fixed and is fixedly connected with water supply pump, the water outlet end of water supply pump is fixedly connected with water delivery pipe, the bottom end of water delivery pipe is fixedly connected with circulation pipe, the bottom end of circulation pipe is fixedly connected with return pipe;The utility model is through the collocation use of water tank, water supply pump, circulation pipe, cooling cavity, cold gas pipe, drive motor and fan blade, so that combustion chamber can be cooled to a certain extent when using, avoid the case that its inside heat deformation occurs due to internal temperature is too high, further guarantee the stability of combustion chamber.

Systems, methods, and devices for humidifying a breathing gas are presented. The system includes a base unit, a vapor transfer unit, a nasal cannula, and a liquid container. The base unit includes a blower. The vapor transfer unit is external to the base unit and includes a gas passage, a liquid passage, a gas outlet, and a membrane separating the gas passage and the liquid passage. The membrane permits transfer of vapor into the gas passage from liquid in the liquid passage. The nasal cannula is coupled to the gas outlet. The liquid container is configured to reversibly mate with the base unit.