169results about "Fluid speed measurement using pressure difference" patented technology

The invention provides a device and method for measuring the flow velocity and flow of gas in a pipeline, and particularly relates to the technical field of measuring instruments, and the device comprises a flow field optimization assembly, a flow velocity sensing assembly and a signal processing assembly. The flow field optimization assembly comprises a plurality of air duct partition plates and straight pipe sections, and the gas conveying pipeline is divided into a plurality of independent divided air ducts; the flow velocity sensing assembly comprises a rectification assembly and a pressure sensing assembly, the rectification assembly comprises a pore plate and / or a grid, and the pressure sensing assembly comprises a plurality of uniformly distributed pressure sensing elements; the signal processing assembly comprises a differential pressure sensing transmitter, a static pressure sensing transmitter, a temperature sensing transmitter, an atmospheric pressure sensing transmitter and a data processing module. The pressure sensing element detects differential pressure signals, the differential pressure sensing transmitter converts the signals, the data processing module calculates the average flow velocity and flow of gas based on the signals and measurement data, and the measurement precision and accuracy are improved.

The invention discloses a thirteen-hole probe and a fluid velocity vector measurement method and system, and the method comprises the steps: carrying out the partitioning of the thirteen-hole probe according to the physical position of each pressure hole in the surface of a spherical probe; adjusting the angle attitude of the thirteen-hole probe, obtaining multiple groups of calibration data under a known flow field, and calculating an angle coefficient characteristic curve graph of each subarea by using the calibration data; performing dimensionless processing on the pore pressure data of each pressure pore in the known flow field to obtain a dimensionless pressure coefficient for fitting, and establishing a general calculation model; and collecting actually measured pore pressure data of the thirteen-hole probe in the flow field to be measured, positioning the subarea to which the actually measured pore pressure data belongs, and calling the angle characteristic curve of the corresponding subarea in the general calculation model to calculate the flow field parameters of the flow field to be measured. A plurality of pressure holes are formed in the spherical probe and used for receiving airflow in multiple directions, the defect that only airflow in the axis direction of the probe can be received in the prior art is overcome, and large-angle bias flow measurement is achieved.

An improved version of pitot test adapters to allow a user to clamp a pitot in an adapter, seal a drain inlet, properly couple a ram and static inlets with independent, simple and efficient steps by moving clamping screws and a separate clamper. The possibility to individually move, align, screw, position, clamp, seal and / or adjust the various components allows for a more efficient and an easier mounting of an adapter onto a pitot tube mounting. The apparatus allows to correctly and more efficiently perform the various testing and calibration of a pitot and associated system of an aircraft.

The invention provides a mixed flow velocity and flow measuring device and method, and particularly relates to the technical field of measuring instruments, and the device comprises a gas mixing assembly, a flow field optimization assembly, a flow velocity sensing assembly and a signal processing assembly. The gas mixing assembly comprises a differential channel mixer and a mixing cavity, and gas premixing is achieved. The flow field optimization assembly comprises a plurality of air duct partition plates and straight pipe sections, and the mixed gas conveying pipeline is divided into a plurality of independent divided air ducts; the flow velocity sensing assembly comprises a rectification assembly and a pressure sensing assembly, the rectification assembly comprises a pore plate and / or a grid, and the pressure sensing assembly comprises a plurality of uniformly distributed pressure sensing elements; the signal processing assembly comprises a differential pressure sensing transmitter, a static pressure sensing transmitter, a temperature sensing transmitter, an atmospheric pressure sensing transmitter and a data processing module. The pressure sensing element detects differential pressure signals, the differential pressure sensing transmitter converts the signals, the data processing module calculates the average flow velocity and flow of the mixed gas based on the signals and measurement data, and the measurement precision and accuracy are improved.

An air data indicating and calibrating arrangement and method for a vertical take-off and landing aircraft, in particular a helicopter, for providing information on an air speed of the vertical take-off and landing aircraft and for providing information on an altitude of the vertical take-off and landing aircraft are described. The vertical take-off and landing aircraft includes a pitot tube device for determining a stagnation air pressure at a position of the pitot tube device and a static port device for determining a static air pressure at a position of the static port device. The air data indicating arrangement includes an air speed and altitude determination module to determine in real-time the air speed and the altitude of the vertical take-off and landing aircraft from flight data by using a regressor obtained by training an artificial neural network with training data.

The present disclosure relates to an airflow sensor unit for an aerial vehicle, the airflow sensor unit. The airflow sensor unit comprises a housing, with a plurality of openings defined in the housing. Each opening faces in a different direction to the other openings. The airflow sensor unit further comprises a plurality of conduits, wherein each conduit is in fluid communication with a corresponding opening. The airflow sensor unit further comprises a plurality of sensor arrangements, wherein each sensor arrangement is configured to measure a pressure within one or more of the conduits.

The invention discloses a cross-medium aircraft, an airspeed tube drainage method of the cross-medium aircraft and a product of the airspeed tube drainage method, and is applied to the technical field of aircrafts. The cross-medium aircraft comprises an airspeed tube and an airspeed tube drainage system, and the airspeed tube drainage system comprises a detection module used for detecting the relative humidity in a first tube or the water pressure in the first tube in the airspeed tube when the operation working condition of the cross-medium aircraft is the water surface working condition or the air working condition; and the drainage module is used for conveying gas into the airspeed tube to discharge accumulated water in the airspeed tube under the condition that the relative humidity in the first tube is greater than or equal to a first preset relative humidity threshold value or the water pressure in the first tube is greater than or equal to a first preset water pressure threshold value. According to the method, gas can be conveyed into the airspeed tube through the drainage module, accumulated water is discharged through the gas, it is ensured that measurement of fluid pressure by the airspeed tube is not interfered by the accumulated water, and the problem that fluid pressure measurement of a cross-medium aircraft is inaccurate due to the accumulated water in the airspeed tube is effectively solved.

The present disclosure relates to methods, apparatuses, devices, and program products for measuring speed. The method comprises acquiring, from a pressure sensor of an electronic device, first pressure information of the electronic device at a first moment when the electronic device is in a stationary state. The method further comprises acquiring, from the pressure sensor, second pressure information of the electronic device at a second moment when the electronic device is in a moving state. The method further comprises acquiring, from an acceleration sensor of the electronic device, acceleration information of the electronic device. In addition, the method comprises determining, based on the first pressure information, the second pressure information, and the acceleration information, an absolute speed of the electronic device at the second moment. By means of the method disclosed herein, the absolute speed of the electronic device can be accurately measured based on the pressure sensor and the acceleration sensor of the electronic device, thereby making the speed measurement more accurate and simple.

An aircraft pressure measurement device includes a pressure sensor (16), a pressure measurement path (14), a valve (18), and a fluid port (22). The pressure measurement path extends between an aircraft skin (12) and the pressure sensor, and the valve is positioned within the pressure measurement path between the aircraft skin and the pressure sensor. The valve is configured to regulate airflow through the pressure measurement path, and the fluid port is configured to allow a pressurized fluid into the pressure measurement path to clear the pressure measurement path of debris.

TITLE Method for monitoring the operation of a plurality of aeronautical measurement probes, and associated monitoring system and aeronautical measurement architecture. The present invention relates to a method for monitoring the operation of a plurality of aeronautical measurement probes, each probe comprising heating means, the method comprising the following steps: - acquisition (110) of a plurality of consumption data, each consumption data characterizing the electrical consumption of the heating means of one of the aeronautical measurement probes; - determination (120) of at least one similarity relationship between at least two consumption data; - comparison (130) of the similarity relationship(s) with a threshold; - detection (140) of an operating anomaly based on the result of the comparison(s). Figure for the abstract: Figure 3

An AGL (above ground level) altitude module may determine an AGL value for the aircraft. An air data MSL (mean sea level) module may determine an air data MSL value for the aircraft based on an air data measurement. A blending module may generate a synthesized operational altitude value for the aircraft based on the AGL value and the air data MSL value. At least one of may be executed: transmitting the synthesized operational altitude value for display to a user of the aircraft; or partially or fully controlling operation of the aircraft according to the synthesized operational altitude value.

A jet aircraft having an airflow modification device in its engine duct, the airflow modification device comprising an inlet, an outlet, and a flow path extending from the inlet to the outlet, wherein the device is positioned to receive an incoming airflow and is configured to at least partially modify the airflow within the flow path to improve the ordering of the incoming airflow, the airflow modification device further comprising at least one pitot sensor located at the inlet and integrated with the device, and a pressure line having a first end and a second end, the first end being connected to the pitot sensor and the second end being connected to a transducer, wherein the pressure line is completely enclosed within the device.

The application discloses a kind of subsonic aircraft airspeed measurement method and system, it is related to aerospace field, the method comprises: obtaining the dynamic pressure voltage value of aircraft external gas measured by silicon piezoresistive pressure difference sensor and the temperature value of silicon piezoresistive pressure difference sensor measured by temperature sensor under different standard temperature points different standard dynamic pressure pressure value;Characteristic coefficient value of each subset is calculated;According to the characteristic coefficient value of subset and the dynamic pressure voltage value and temperature value in subset, the uncorrected dynamic pressure corresponding to each subset is calculated;Uncorrected dynamic pressure is corrected and calibrated, and the calibrated dynamic pressure corresponding to each subset is obtained;Set range dynamic pressure is calculated, and set range dynamic pressure is obtained by total pressure value minus static pressure value;Target dynamic pressure is calculated according to calibrated dynamic pressure and set range dynamic pressure;According to target dynamic pressure, the airspeed corresponding to each target dynamic pressure is determined, and the high-precision measurement of subsonic aircraft airspeed is realized.

The application provides a multi-parameter wind-sand monitoring device and method for a sand collector, relates to the technical field of wind-sand observation and environmental monitoring, and the device synchronously measures wind speed data at different heights through a wind speed gradient measurement module, measures the real-time orientation of the sand collector through a wind direction measurement module to obtain wind direction data, detects sand particle impact through a wind-sand event sensing module and outputs an impact electric signal, and finally, according to the impact electric signal, the starting and ending of a wind-sand event are monitored through an intelligent control module, the starting time, the ending time and the duration of the event are recorded, and the wind-sand monitoring result of the wind-sand event is determined based on the wind speed data and the wind direction data obtained in the wind-sand event period, and the wind-sand monitoring result includes the starting time, the ending time, the duration, the dominant wind direction and the average wind speed at each height in the wind-sand event period. The application can automatically and accurately monitor the whole process of wind-sand movement and provide comprehensive and reliable data support for wind-sand research.

In an embodiment, a system on a chip (SOC) includes a component that remains powered when the remainder of the SOC is powered off. The component may include a sensor capture unit to capture data from various device sensors, and may filter the captured sensor data. Responsive to the filtering, the component may wake up the remainder of the SOC to permit the processing. The component may store programmable configuration data, matching the state at the time the SOC was most recently powered down, for the other components of the SOC, in order to reprogram them after wakeup. In some embodiments, the component may be configured to wake up the memory controller within the SOC and the path to the memory controller, in order to write the data to memory. The remainder of the SOC may remain powered down.

In one embodiment, a probe includes a first facet associated with a first pressure port operable to measure a first wind pressure, a second facet associated with a second pressure port operable to measure a second wind pressure, and a third facet associated with a third pressure port operable to measure a third wind pressure. The second facet is adjacent to the first facet and the third facet adjacent to the second facet. The probe further includes a fourth facet adjacent to the third facet and a fifth facet adjacent to the fourth facet and to the first facet. The first facet, the second facet, the third facet, the fourth facet, and the fifth facet are located between a first end portion and a second end portion of the probe.

The invention relates to the technical field of unmanned aerial vehicle parts, in particular to an unmanned aerial vehicle waterproof airspeed tube convenient to disassemble and assemble, which comprises an air inlet piece, a pressure separation piece, an air inlet pipe and an airspeed tube. The air inlet pipe and the airspeed tube are both mounted in the pressure separation piece and are not directly communicated with each other; the air inlet piece is connected with the pressure separation piece, and external air enters the airspeed tube through the air inlet pipe to be measured. An air inlet cavity and a water baffle are arranged in the air inlet piece, and primary drainage is achieved through a first drainage assembly; the pressure separation part comprises a horizontal pressure transmission part and an inclined height difference flow guide part and is provided with a second drainage assembly, and the second drainage assembly comprises a water collection cavity and a second drainage port and is installed between the air inlet pipe and the airspeed pipe to achieve air-water separation and secondary drainage. The airspeed tube air inlet hole is higher than the air inlet tube exhaust hole, and accumulated water is further prevented from flowing backwards. The device is reasonable in structure, has good waterproof and drainage capacity, can improve the airspeed measurement precision, and is suitable for various unmanned aerial vehicle platforms with fixed wings, vertical take-off and landing and the like.

To remove the dead volume in the sensor assembly of a mass flow controller.SOLUTION: A sensor assembly 16 of a mass flow controller includes: a first reservoir 22 coupled to a first pressure transducer 18 and communicating with a sampling flow path 64; a second reservoir 24 coupled to a second pressure transducer 20, communicating with the first reservoir 22 via a flow-through path 26, and further communicating with another sampling flow path 66; and a restrictor 68 disposed in the flow-through path 26 so as to face the first and second pressure transducers 18 and 20.SELECTED DRAWING: Figure 2A

[Object] To detect airspeed and an airflow direction with respect to an airframe of a motorized aircraft with high accuracy without increasing the cost and weight and rapidly control attitudes of an electric propulsion system and the airframe in accordance with fluctuations of the airspeed and airflow direction.[Solving Means] An electric propulsion system control device includes: a first airspeed measurement unit that is mounted on an airframe of an aircraft and includes a first propulsion system parameter detector that detects a propulsion system parameter, the propulsion system parameter being a parameter of an electric propulsion system, the electric propulsion system being driven by an electric motor and rotating about a rotation axis as a center, and a first airspeed calculator that calculates first airspeed on a basis of the propulsion system parameter, the first airspeed being airspeed with respect to a first direction that is a direction of the rotation axis; a second airspeed measurement unit that is mounted on the airframe and measures second airspeed, the second airspeed being airspeed with respect to a second direction different from the first direction; and an airflow calculator that calculates airspeed and airflow direction with respect to the airframe on a basis of the first direction and the first airspeed and the second direction and the second airspeed.

The application relates to the technical field of fluid pressure detection, in particular to a flow rate detection system and a flue gas flow rate detection method. In the flow rate detection system, a wind-blocking side plate of a pitot tube is enclosed and installed on a wind-blocking bottom plate, and a wind-collecting cavity is formed by the wind-blocking side plate and the wind-blocking bottom plate; a total pressure detection hole is arranged on the wind-blocking side plate, and a first air outlet and a second air outlet are symmetrically arranged on the two sides of the total pressure detection hole; the region of the wind-blocking side plate where the first air outlet and the second air outlet are located is gradually contracted in the direction towards the first air outlet, the second air outlet and the total pressure detection hole, thereby forming a contracted structure; one end of a total pressure transmission pipe is communicated with the total pressure detection hole, and the other end is communicated with a high-pressure end of a differential pressure sensor; a static pressure transmission pipe is arranged on the side of the wind-blocking bottom plate away from the wind-blocking side plate, a static pressure detection hole is arranged on the end of the static pressure transmission pipe close to the wind-blocking bottom plate, and the other end is communicated with a low-pressure end of the differential pressure sensor. The pitot tube realizes physical anti-blocking, and can normally work in a flue with low flow rate and a large amount of particulate matters.

An airspeed instrument that employs one or more circulation chambers to receive and circulate incoming airflow to separate moisture from the air that can be then expelled via a drainage port. The exemplary airspeed instrument apparatus can be implemented as a small instrument appropriately sized for small UASs and aircraft. The separation chamber has an angled bottom surface that leads to a sampling port positioned at the top of the chamber, which prevents moisture from entering the sampling port into the measuring electronics. In some embodiments, the exemplary airspeed instrument apparatus is configured with an integrated static port sensor.

An airflow sensor unit 1 for an aerial vehicle (50, figure 2A) The airflow sensor unit comprises a housing 80, with a plurality of openings 30-35 defined in the housing. Each opening faces in a differ

This invention provides a substitute Pitot tube that ensures sufficient measurement accuracy when measuring wind speed and is less expensive than a standard Pitot tube. [Solution] The substitute Pitot tube 6 comprises a first pipe 11 with a first hole 11a, a second pipe 12 with a second hole 12a adjacent to the first hole 11a, and a measuring instrument 13 for measuring the pressure difference between the inside of the first pipe 11 and the inside of the second pipe 12. The hole axis 11aa of the second hole 12a is inclined to the hole axis 12aa of the first hole 11a within a range of 90° to 180°. In this substitute Pitot tube 6, because the first hole 11a and the second hole 12a are adjacent, the measuring instrument 13 can determine a nearly accurate dynamic pressure as the pressure difference, thus ensuring sufficient measurement accuracy when measuring wind speed. Furthermore, since the first pipe 11 and the second pipe 12 are separate components, the processing of both pipes 11 and 12 is easier, making it cheaper than a traditional Pitot tube.

The invention relates to a method, an apparatus, a device and a program product for measuring speed. The method comprises the following steps: acquiring first pressure intensity information of the electronic equipment at a first moment when the electronic equipment is in a static state from a pressure intensity sensor of the electronic equipment; the method further comprises the step of obtaining second pressure intensity information of the electronic equipment at the second moment when the electronic equipment is in the motion state from the pressure intensity sensor. The method further includes acquiring acceleration information of the electronic device from an acceleration sensor of the electronic device. In addition, the method further comprises the step of determining the absolute speed of the electronic equipment at the second moment based on the first pressure intensity information, the second pressure intensity information and the acceleration information. Through the method disclosed by the invention, the absolute speed of the electronic equipment can be accurately measured based on the pressure sensor and the acceleration sensor of the electronic equipment, so that the speed measurement is more accurate and simpler.

The invention belongs to the technical field of gas emission amount detection, is particularly suitable for monitoring CO2 emission amount of a power plant and online detection of factory waste gas emission amount or emission amount of a certain component, and particularly relates to a device and a method for detecting the gas flow rate of a large-diameter pipe body based on a honeycomb structure. The device for detecting the gas flow rate of the large-diameter pipe body based on the honeycomb structure comprises a detection sub-unit, and a flow rate detection device is arranged on the detection sub-unit; and the detection sub-units are arranged in a honeycomb structure. According to the invention, the large aperture is divided into a plurality of honeycomb tube combinations, so that the problem of inaccurate wind speed measurement caused by the fringe effect of the large aperture can be effectively solved. The large-caliber wind speed can be accurately measured by adopting a honeycomb structure and a phase array measurement mode, the measurement accuracy guarantee value is within 2%, and the resistance drop loss is smaller than 5%. According to the measuring device, a honeycomb structure can be printed into an assembly through 3D printing, then the assembly is spliced and installed on site, and installation and maintenance are very convenient.

The invention provides a multi-parameter wind and sand monitoring device and method for a sand collector, and relates to the technical field of wind and sand observation and environmental monitoring, the device synchronously measures wind speed data at different heights through a wind speed gradient measurement module, and measures the real-time orientation of the sand collector through a wind direction measurement module to obtain wind direction data; detecting sand impact and outputting an impact electric signal through the wind and sand event sensing module; finally, through an intelligent control module, starting and ending of a wind and sand event are monitored according to the impact electric signals, the starting time and ending time of the event are recorded, and the duration is calculated; based on the wind speed data and the wind direction data acquired in the wind sand event time period, determining a wind sand monitoring result of the wind sand event, the wind sand monitoring result including event starting time, ending time, duration, prevailing wind direction and average wind speed of each height in the wind sand event time period. The whole sand movement process can be automatically and accurately monitored, and comprehensive and reliable data support is provided for sand research.

A hybrid heater system for an aircraft air data sensor includes a voltage source (46) and a first hybrid heater set (42). The first hybrid heater set includes a carbon nanotube (CNT) heater (28), a first positive temperature coefficient (PTC) heater disposed in parallel with the CNT heater (28) to form a parallel formation, and a second PTC heater disposed in series between the voltage source (46) and the parallel formation.

This invention relates to a fluid velocity and flow rate detection device, and pertains to the field of fluid detection technology. The device includes: a fixed small steel plate and an elastic sensing unit; both the fixed small steel plate and the elastic sensing unit are disposed inside the fluid pipe to be detected; wherein, the lower end of the fixed small steel plate is fixedly connected to the inner wall of the fluid pipe, and a fixing part is provided at its upper end; the elastic sensing unit includes at least two elastic steel plates, one end of each elastic steel plate converging and connecting to the fixing part, and the elastic steel plates are radially distributed with the fixing part as the center; a first sensor is assembled at the other end of each elastic steel plate. This invention has a wide range of applicable media, strong anti-interference ability, and stable detection.

A system (100) and a method (200) for localizing a railway vehicle (1) travelling on a railway line (10) which is powered by a catenary line (2) comprising a current-conducting wire (3) supported by a plurality of spaced apart catenary poles (4), wherein at least one sensor (110) is installed on-board of the railway vehicle (1) and is configured to provide to a control and processing unit (140), while the railway vehicle (1) is travelling along the railway line (10), first signals (S1) indicative of the actual value of a first parameter detected related to said current-conducting wire (3). The control and processing unit (140) is configured to calculate, based on the first signals (Si) received, a second parameter indicative of a catenary pole (4) possibly detected along the railway line (10). A plurality of devices (120) are installed on board of the railway vehicle (1) and are suitable to provide to the control and processing unit (140) second signals (S2) suitable for identifying the catenary pole (4) possibly detected; and wherein the control and processing unit (140) is further configured to univocally identify the catenary pole (4) possibly detected based on the second signals (S2) and to calculate the actual position of the railway vehicle (1) along the railway line (10) based on the univocally identified catenary pole (4).