59 results about "High velocity" patented technology

The system and method for decelerating space objects moving at high velocities are provided. The system comprises at least one closed volume containing a combination of gas, liquid, solid particles, or a mixture thereof. The volume can be transported to the targeted location using a range of means, including a chemical gun, light gas gun, electromagnetic coil gun, superconducting quench gun, a rocket, or a combination thereof. The volume is strategically positioned on the trajectory of the moving object. Upon penetrating the walls of the volume, the object passes through it, experiencing deceleration.

Systems and methods for using a liquid jet apparatus for dental treatments are disclosed. In one implementation, the liquid jet apparatus may include a handpiece configured to deliver a high velocity liquid jet to a desired location in the mouth of a patient. The handpiece may include a positioning member having a channel through or along which the jet can propagate. The positioning member may have a distal end portion configured to be at least partially disposed in a pulp cavity, canal space, or opening in the tooth under treatment. During operation, the jet may impact an impingement surface of the distal end portion of the positioning member and be deflected as a spray through one or more openings in the distal end portion. The liquid jet apparatus may be used for root canal treatments.

A three-dimensional (3D) metal object manufacturing apparatus is configured to eject melted metal drops from an ejector head at different velocities to form different portions of metal object layers with different measurable values of a same physical property. The different velocities are achieved by operating the ejector head with two different electrical voltages. The greater voltage that achieves the higher velocity is about 25% greater than the voltage used to achieve the lesser velocity. By operating the ejector head with the two different voltages different portions of the object can be formed with different physical property characteristics.

The invention discloses a method for repairing a blade damping table through combination of argon arc welding and supersonic spraying, and belongs to the technical field of aviation part repairing. The method comprises the following steps: firstly, repairing cracks of the damping table through argon arc welding, and ensuring the welding quality through nondestructive testing and stress relief heat treatment; then, the welding repair area is ground down; spraying a high-cobalt-molybdenum-chromium wear-resistant coating with specific components on the end surface by adopting a high velocity oxy-fuel spraying technology; and finally, the design size is recovered through accurate grinding. The coating prepared through high velocity oxy-fuel spraying has the outstanding advantages of high density, high hardness and high bonding strength, the crack defect is thoroughly eliminated, the size is recovered, the abrasion resistance and corrosion resistance of the blade damping table are remarkably improved, the service life of the blade is prolonged, economic benefits are remarkable, and the application prospect is wide. And the method is suitable for remanufacturing high-value precision parts such as aero-engines.

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.

The invention discloses a high velocity oxy-fuel spraying method for a titanium alloy irregular arc surface. The high velocity oxy-fuel spraying method comprises the following steps that S1, the titanium alloy with the irregular arc surface is pretreated; s2, shielding the non-spraying surface of the irregular arc surface titanium alloy pretreated in the S1; s3, carrying out sand blasting treatment on the to-be-sprayed surface of the irregular arc surface titanium alloy subjected to shielding treatment in S2; and S4, the spraying face of the irregular arc face titanium alloy subjected to sand blasting treatment in the S3 is preheated through supersonic flame, spraying is conducted on the spraying face, when the variable cross section of the irregular arc face titanium alloy is met, the distance between a spraying gun and the spraying face is adjusted to be 5-20 mm, meanwhile, the angle of the spraying gun is adjusted to be 70-90 degrees, overall spraying is conducted for 15-20 times, and the final thickness of a coating is 40-80 microns. By means of the method, the uniformity and compactness of the flame spraying coating of the irregular arc surface of the titanium alloy can be guaranteed, and the coating with the wear resistance superior to the function of a chromium plating layer can be obtained.

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.

Methods and apparatuses join multiple members with a high velocity induced metallurgical bond. An example method includes accelerating a projectile to a threshold velocity toward members in stacked relation to one another and striking a first member of the members at or above a threshold velocity with the projectile to form a joint that couples the members to one another. The threshold velocity is sufficient to induce a metallurgical bond in the joint.

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.

The invention discloses a technological method for repairing a hydraulic cylinder of a blowout preventer, and relates to the technical field of oil well blowout preventer repairing. According to the process, corrosives on the inner wall are removed through pulse type high-pressure water jet and ultrasonic cleaning, a stress atlas is subjected to rotary sand blasting coarsening and laser surveying and mapping, a stress concentration area and a main body area of a hydraulic cylinder are preheated section by section based on the atlas, and a tungsten carbide-based coating is deposited by adopting a high velocity oxy-fuel spraying combined pulse powder feeding technology. A pressure stress layer is formed through subarea temperature control gradient cooling, sealing surface grinding and ultrasonic impact strengthening; and finally, eddy current flaw detection, thickness measurement and high-temperature and high-pressure cyclic fatigue testing are performed. The process solves the problems that a traditional repairing coating is low in bonding strength and high in porosity, the corrosion resistance and the fatigue resistance of the repairing layer are improved through stress regulation and control, and the process is suitable for hydraulic cylinder repairing under the high-pressure corrosion working condition.

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.

Techniques are provided for receiving PUSCH and PUCCH transmitted by a high speed transmitter. The techniques include calculating a phase difference of OFDM symbols of the PUCCH from OFDM symbols of a first DM-RS and OFDM symbols of a second DM-RS of the PUCCH, correlating the OFDM symbols of the first DM-RS and second DM-RS. Determine a doppler shift and report it to L2. Compensate channel estimates and data symbols with the doppler shift. Equalize and demodulate the PUCCH. Perform a first level of phase correction on the PUSCH by correcting the phase on output samples of an IDFT from the doppler shift received from L2. Measure a phase deviation on the output of the first level of phase correction, accumulate the measured phase deviation and the doppler shift received from L2, to derive an accumulated phase correction, and report the accumulated phase correction to L2. Demodulate the PUSCH.

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).

Methods and apparatuses join multiple members with a high velocity induced metallurgical bond. An example method includes accelerating a projectile to a threshold velocity toward members in stacked relation to one another and striking a first member of the members at or above a threshold velocity with the projectile to form a joint that couples the members to one another. The threshold velocity is sufficient to induce a metallurgical bond in the joint.

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.

Disclosed is an ultrasound imaging approach employing a transmission scheme, termed "StaBle", to increase the Nyquist limit, through dealiasing, of conventional sequential angle, ultrafast (high-frame-rate) ultrasound imaging (e.g., plane-wave Doppler imaging or diverging wave imaging). The dealiased multi-angle Doppler estimates facilitate accurate least-squares estimates of flow magnitude and direction for vector Doppler imaging (VDI). "StaBle" combines the Nyquist velocity limit extension of staggered, multiple pulse repetition frequencies (PRFs) with a double transmission scheme. With 3 transmit angles and 2 PRFs, for example, the disclosed "StaBle" technique can achieve a 6-12 times higher velocity limit compared to sequential-angle VDI. The robustness of "StaBle" can be observed in derived measures from the VDI results, such as vorticity, kinetic energy, and energy loss obtained from the resolved vector field, which show consistent beat-to-beat variation.

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.

The present invention relates to a spurious shear horizontal mode frequency control with the addition of a high velocity layer in a lithium niobate filter. In particular, to an electronic device comprising a first surface acoustic wave (SAW) resonator and a second SAW resonator, each SAW resonator having interleaved interdigital transducer (IDT) electrodes, the first SAW resonator and the second SAW resonator being formed on a same piezoelectric substrate, the first SAW resonator having IDT electrodes with a different interdigitated pitch than the IDT electrodes of the second SAW resonator; a layer of dielectric material disposed on the IDT electrodes of the first SAW resonator and the second SAW resonator; a high velocity layer disposed within the layer of dielectric material configured on the IDT electrodes of the first SAW resonator, the second SAW resonator not having a high velocity layer disposed within the layer of dielectric material configured on the IDT electrodes.

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).

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.

The invention provides a test method for evaluating the reliability of an EBPVD (electron beam physical vapor deposition) coating of a turbine blade of a gas turbine, which is characterized by comprising the following steps: acquiring a test blade, and coating the surface of the test blade with an EBPVD thermal barrier coating to be tested; the test blade is fixed through the supporting tool; spraying a flame flow containing particles to the surface of the test blade by using a supersonic flame gun, and simulating the working conditions of gas scouring and particle erosion; the failure form of the thermal barrier coating is observed, and testing times are recorded; and judging the reliability of the thermal barrier coating according to the failure form and the test count. According to the testing method, high-temperature and high-speed fuel gas is obtained, and the fuel gas is washed by particles and is closer to a real fuel gas incoming flow state. The high velocity oxy-fuel spray gun sprays emery to impact the blade coating area, the technological process is simpler and more efficient, the testing period is short, and the judgment standard of reliability evaluation is simple and direct.

The invention discloses a wind power generation system. The wind power generation system optimizes wind energy utilization and achieves overload protection through a multi-stage structure. A horn-shaped wind gathering part is arranged at the front end of the system and used for primarily compressing entering airflow, and primary gain airflow with the high flow speed is formed. Afterwards, the airflow enters the Laval nozzle structure and is secondarily compressed through the convergence section, the higher flow speed is achieved at the throat portion, secondary gain airflow is formed, a wind power generation device located at the throat portion is driven, and the power generation efficiency is remarkably improved. The system is provided with a wind speed sensor at the air inlet and is linked with the control device. When the wind speed is too high or the generated power exceeds the limit, the control device drives the mechanical iris mechanism to adjust the through-flow area of the inlet of the Laval nozzle and control the flow of the entering airflow, so that the power generation device is ensured to always work in a safe range, and overload is effectively prevented. The system integrates wind energy gain and active protection, and has the characteristics of efficient power generation and stable operation.