99results 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.

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 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.

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 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 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.

[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.

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 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.

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).

The utility model discloses a denitration system wind speed uniform distribution measuring device, which comprises a plurality of multi-position differential pressure detecting devices arranged above a denitration catalyst layer and below an ammonia spraying rectification grid, a plurality of measuring holes are formed in the side surface of the denitration system at equal intervals, and the measuring holes are communicated with the denitration catalyst layer. The multi-position differential pressure detection devices are installed in the corresponding measuring holes, each multi-position differential pressure detection device comprises a steel pipe and a plurality of pitot tubes, the pitot tubes are fixedly installed in the steel pipe, and the detection ends of the pitot tubes are installed in the measuring holes. According to the utility model, when wind speed measurement needs to be carried out in a denitration part, the steel pipe is pushed into the measuring hole, precise control of the pitot tubes is realized, differential pressure of corresponding positions can be measured through the pitot tubes, and the plurality of pitot tubes are arranged in the steel pipe, so that wind speeds of multiple points of a detection section can be acquired at the same time; the consistency of wind speed collection at the same time is kept, and the detection precision is improved.

This invention proposes a method for testing flow-induced noise in pipelines, comprising the following steps: Step S1: Determine the measurement positions at the upstream and downstream flow channels of the component under test, normalize the measured signals, and calculate the pressure power spectral density of the pipe wall; Step S2: Calculate the time-domain cross-correlation coefficient of the wall pressure fluctuations and analyze the correlation characteristics between the wall pressure pulsations; Step S3: Perform spectral eigenorthogonal decomposition on the pressure pulsation field and achieve spatiotemporal decoupling through time-domain-frequency-domain conversion; Step S4: Extract the dominant flow-induced noise modes, construct an empirical frequency-wavenumber spectrum, and decompose the energy distribution of the fluctuations into contributions from different frequency and wavenumber combinations; Step S5: Analyze the decoupled flow-induced noise characteristic results and identify the amplitude-frequency characteristics of the flow-induced noise; This invention can realize real-time measurement of pressure pulsations in pipelines, achieve decoupling analysis of flow field pulsations and sound pressure pulsations in the measured signals, and identify the characteristics and generation mechanism of pipeline flow-induced noise.

A system for monitoring a vehicle-borne probe includes a first edge device in communication with the probe and configured to sense data related to a characteristic of a heating element of the probe, a coordinator in communication with the first edge device and configured to receive a first data output from the first edge device and to incorporate the first data output into a data package, a cloud infrastructure in communication with the coordinator via a data gateway and configured to analyze the data package to estimate a remaining useful life and predict a failure of the probe, and a ground station in communication with the cloud infrastructure and configured to refine remaining useful life estimation and failure prediction techniques of the system.

A system includes a body, a sensor (50), a pressurized fluid source (46), and a blockage detection module (32). The body defines a cavity (44) open to an ambient environment at a port. The sensor communicates with the cavity to produce a signal representative of a fluid pressure within the cavity. The blockage detection module includes a pressure regulator (36) and a valve (38) disposed along a conduit (34) fluidly connecting the pressurized fluid source to the cavity. The blockage detection module includes a processor (40) and memory (42) encoded with instructions of a blockage detection method.

The invention relates to an MEMS liquid flow velocity sensor based on differential pressure measurement and a preparation method thereof, the MEMS liquid flow velocity sensor based on differential pressure measurement comprises a base body which comprises a base body main body and a base body arm located at the top of the base body main body, and the side surface of the base body arm is provided with an opening; the flow channel is located in the base body, the first end of the flow channel is communicated with the opening, and the second end of the flow channel is provided with an MEMS pressure sensor. The MEMS liquid flow velocity sensor based on differential pressure measurement is small in overall size and can measure the flow velocity or flow in a small determined range.

According to the novel aircraft pitot tube provided by the invention, the installation mode between the pitot tube and the aircraft body is improved from the traditional equipotential electrical connection installation to the electrical insulation installation, and the lightning protection and static electricity removal device is additionally arranged between the pitot tube and the aircraft body, so that the pitot tube has the functions of lightning protection and static electricity discharge; in addition, the pitot tube is connected with the fuselage through the lightning protection and static electricity removal device, the negative influence on the pitot tube heating system caused by reduction of insulation performance of the pitot tube heating resistor can be reduced to a great extent, and therefore the reliability of the airplane pitot tube is improved.

The utility model discloses an obliquely-inserted short Venturi tube, and belongs to the technical field of Venturi tubes. The oblique insertion type short Venturi tube comprises a Venturi tube body, the Venturi tube body is provided with a sliding sleeve assembly, the two sides of the outer wall of the sliding sleeve assembly are connected with telescopic mechanisms respectively, the bottom ends of the two telescopic mechanisms are connected with a fixing plate, one side of the fixing plate is provided with a through hole, the sliding sleeve assembly comprises an outer ring, and the outer ring is provided with a through hole. The outer wall of the Venturi tube body is slidably connected with an outer ring, two sides of the outer wall of the outer ring are rotatably connected with shafts respectively, one sides of the two shafts are in threaded connection with screws respectively, the shafts are connected with the top end of the telescopic mechanism through the screws, and the Venturi tube body comprises a cylinder section, a contraction section, a throat, a diffusion section and an external connection section. One end of the cylinder section is communicated with the contraction section, the throat is communicated between the contraction section and the diffusion section, and one end of the diffusion section is communicated with the external connection section.

A method for validating aerodynamic measurements implemented by an architecture including N separate measurement paths each including Pm probes, including: acquisition of an elementary measurement from each probe; for each measurement path, determination of a resultant measurement from the probes belonging to this path, and comparison of the resultant measurements. When the resultant measurements are consistent, validation of the measurements. When a resultant measurement related to path k is inconsistent: selection of a measurement path i, determination of Pi+Pk consistence values, determination of an inconsistent value among all the consistence values, and invalidation of any elementary measurement from the probe corresponding to the inconsistent value.

The utility model discloses a micro differential pressure type airflow sensor, which comprises a support plate and a sensor shell, the support plate is arranged in the inner space of the sensor shell, a positioning assembly is arranged between the support plate and the sensor shell, the positioning assembly comprises four extension plates, and the extension plates are arranged on the support plate. The four extension plates are fixedly connected to the corners of the four side faces of the sensor shell correspondingly, the two extension plates on one side are attached to the inner wall of one side of the supporting plate, a supporting frame is fixedly connected to the interior of the supporting plate, a lead screw is rotatably connected to the interior of the supporting frame, and the exterior of the lead screw is in threaded connection with a clamping sleeve. The inner wall of the bottom of the supporting frame is fixedly connected with a guide rail, one end of the bottom of the clamping sleeve is slidably sleeved outside the guide rail, the sensor can be stably fixed at a to-be-detected position during use by arranging the positioning assembly, the sensor can also be quickly disassembled and taken down when maintenance is needed, the operation is convenient and quick, and the detection efficiency is improved. And the practicability of the device is improved.

The utility model relates to the technical field of flue gas collecting equipment, in particular to an integrated flue gas sampler which comprises a mounting base, a protective sleeve extending into a sampling hole is arranged on one side of the mounting base, a sampling pipe group is arranged in the protective sleeve, a positioning plate detachably connected with the mounting base is arranged at the end of the sampling pipe group, and a sampling pipe is arranged in the positioning plate. Through a detachable connection mode, the sampling pipe group can be rapidly mounted and dismounted, sampling pipe groups of different specifications can be selected according to different sampling requirements, the operation is simple and convenient, then connection positioning is performed through the protective sleeve and the to-be-measured main body, the structure is simple, and the assembly is efficient.

The utility model belongs to the technical field of wind speed detection, particularly relates to detection equipment for pipeline wind speed, and aims to solve the problems that a pitot tube wind speed transmitter is inconvenient to disassemble and assemble, time-consuming and labor-consuming to install, and inconvenient to disassemble and maintain when a fault occurs, the following scheme is provided: the detection equipment comprises a pitot tube wind speed transmitter and a probe rod installed on the pitot tube wind speed transmitter; an insertion hole is formed in the pipeline, and one end of the probe rod penetrates through the insertion hole and extends into the pipeline; the two positioning sleeves are fixedly mounted on the outer side of the pipeline, two positioning rods are fixedly mounted on the pitot tube wind speed transmitter, and the two positioning rods are clamped with the two positioning sleeves respectively; the two locking holes are formed in the two positioning rods; and the locking mechanism is arranged on the pipeline and used for being matched with the two locking holes to connect and fix the two positioning sleeves and the two positioning rods. According to the utility model, the pitot tube wind speed transmitter is convenient to disassemble and assemble, time and labor are saved during installation, and the pitot tube wind speed transmitter can be quickly disassembled and maintained during failure.