227results about "Fluid speed measurement using pressure difference" patented technology

The invention provides a method for testing flow-induced noise of a pipeline. The method comprises the following steps: S1, determining measurement positions at an upstream flow channel and a downstream flow channel of a measured element, carrying out normalization processing on measured signals, and calculating the pressure power spectrum density of the inner wall surface of a pipe; s2, calculating a wall surface pressure fluctuation time domain cross correlation coefficient, and analyzing correlation characteristics between wall surface pressure pulsation; s3, spectrum intrinsic orthogonal decomposition is carried out on the pressure pulsation field, and space-time decoupling is achieved through time domain-frequency domain conversion; s4, extracting a dominant flow-induced noise mode, constructing an empirical frequency-wave number spectrum, and decomposing fluctuating energy distribution into contributions of different frequency and wave number combinations; s5, analyzing the decoupled flow-induced noise characteristic result, and identifying the amplitude-frequency characteristic of the flow-induced noise; according to the invention, real-time measurement of pressure pulsation in the pipeline can be realized, decoupling analysis of flow field pulsation and sound pressure pulsation can be carried out on the measured signal, and characteristics and a generation mechanism of pipeline flow-induced noise can be identified.

Various implementations include a low-drag smart tether system for measuring fluid speed and direction. The system includes a sleeve, a pressure sensor, and a tether. The sleeve has a longitudinal axis and an airfoil shaped cross-section as viewed in a plane perpendicular to the longitudinal axis. The sleeve has a leading edge. The sleeve defines a tether opening extending parallel to the longitudinal axis. The pressure sensor is disposed along a surface of the sleeve. The pressure sensor is configured to measure the pressure exerted on the pressure sensor by air moving over the surface of the sleeve. The tether extends through the tether opening defined by the sleeve. The tether has a tether longitudinal axis. The tether opening is positioned such that fluid flowing around the sleeve causes the sleeve to rotate about the tether longitudinal axis.

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.

A method is disclosed herein. The method includes receiving, by a processor, an ejection command for ejecting an ejection seat from an aircraft; determining, by the processor, an equivalent airspeed and an equivalent altitude of the ejection seat; and, responsive to the airspeed and the altitude indicating a second mode of operation: sending, by the processor, a command to deploy a drogue parachute; determining, by the processor, a variable drogue severance delay; and responsive to the variable drogue severance delay expiring, sending, by the processor, a command to sever the drogue parachute and deploy a main parachute.

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.

A system includes a body, a sensor, a pressurized fluid source, and a blockage detection module. The body defines a cavity 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 and a valve disposed along a conduit fluidly connecting the pressurized fluid source to the cavity. The blockage detection module includes a processor and memory encoded with instructions of a blockage detection method.

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 invention relates to the technical field of pipeline flow velocity measurement, and provides a non-contact pipeline fluid flow velocity measurement method based on a neural network model, and the method comprises the steps: collecting signal data sets at different pipeline flow velocities through a piezoelectric film sensor; performing two-dimensional Fourier transform on the signal data set, and converting the signal into a two-dimensional energy spectrogram of a frequency-wavenumber domain; the two-dimensional energy spectrogram predicts the flow velocity of the fluid through a two-dimensional neural network model. The collected signals are subjected to two-dimensional Fourier transform and converted into the two-dimensional energy spectrogram of the frequency-wavenumber domain, the signal processing capacity is effectively improved, more accurate and meaningful input data are provided for the two-dimensional neural network model, the two-dimensional neural network model is adopted for flow velocity prediction, the two-dimensional energy spectrogram serves as input, and the flow velocity prediction accuracy is improved. And features are automatically extracted and the flow velocity is predicted through a deep learning technology. According to the method, a traditional signal algorithm for processing the workpiece problem in the complex turbulence environment through the flow speed is overcome, and the measurement precision and robustness are improved.

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 invention provides a method for measuring the air volume in the cross section of an air duct of a non-uniform wind field, which comprises the following steps of: counting the rotation of a speed measuring fan by using electric signals of at least one speed measuring fan with the same specification uniformly distributed in the cross section of the air duct of the non-uniform wind field and a corresponding rotating speed measuring unit; a rotating speed value is obtained through processing by a monitoring analysis unit and is converted into a circumferential wind speed; according to the circumferential linear speed, the outer diameter of the speed measuring fan and a flow calibration coefficient, the air volume in the sensed plane area is calculated; meanwhile, the air volumes in the plane areas sensed by the other speed measuring fans are calculated according to the steps, and then the weighted average value of the air volumes is calculated, namely the air volume of the cross section of the whole air duct; torque is generated through the wind speed of an average fan blade surface and a plane, the average wind speed of a fan blade and a cross section is generated after weighted average is carried out through a rotating shaft, then weighted values of the torques and the average wind speed are calculated, and therefore the technical means similar to the overall data average wind speed is adopted for carrying out accurate wind quantity measurement on a non-uniform wind field air channel.

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.

The invention relates to the technical field of smoke adjustment, in particular to a smoke flow and flow velocity comparison device capable of adjusting smoke in a translation mode and an adjusting method.The smoke flow and flow velocity comparison device comprises a smoke outlet plate arranged at the front end of a pipeline and an air outlet formed in the smoke outlet plate and further comprises a pitot tube, a driving mechanism, a shielding plate and an adjusting mechanism; the driving mechanism is installed at the pitot tube, the shielding plate is installed above the smoke outlet plate, the adjusting mechanism is located on one side of the shielding plate, the pitot tube detects and transmits the air volume to the driving mechanism, and the smoke discharging speed is monitored in real time through the pitot tube method. And different circulation paths are formed when the flue gas is initially discharged and excessive in discharge capacity through separate cavity transmission, so that the discharge capacity of the flue gas is reduced in a manner of prolonging the flow paths of the flue gas.

The present invention discloses a wind tunnel test system for measuring the surface wind speed of a stack, comprising: a stack model to be measured, which is used to obtain the surface wind speed based on a probe; and a wind flow field system, which is used to simulate natural wind and perform tests on the stack model to be measured based on the natural wind to obtain the surface wind speed of the stack model to be measured. The present invention also discloses a wind tunnel test method for measuring the surface wind speed of a stack, comprising: constructing a wind flow field system, blowing air on the stack model to be measured through the wind flow field system, and obtaining the wind speed data of each surface of the stack model to be measured; obtaining a plurality of wind speed ratios based on the wind speed data of each surface of the stack model to be measured; performing weighted averaging on the area of each surface based on the plurality of wind speed ratios to obtain a comprehensive wind speed ratio; obtaining a wind speed influence coefficient based on the comprehensive wind speed ratio, and calculating the surface wind speed of the stack based on the wind speed influence coefficient.

The invention provides an intelligent interactive blowing type wind measurement method for meteorological science research. The intelligent interactive blowing type wind measurement method for meteorological science research comprises the following steps: a, detecting the pressure difference change in real time through a pressure difference sensor when airflow passes through; b, performing temperature and humidity compensation based on a temperature and humidity compensation module, and measuring environment temperature and humidity by using temperature and humidity sensors; c, eliminating the interference of intermittent airflow by adopting a breathing pulse algorithm; d, carrying out shaping treatment on the airflow through a three-stage airflow shaping system; and e, calculating the wind speed of the airflow through a self-adaptive pressure difference detection module. According to the intelligent interactive blowing type wind measurement method for meteorological science research, firstly, the temperature and humidity of the environment are monitored in real time by introducing a temperature and humidity compensation module and the self-adaptive pressure difference detection module, and temperature and humidity coupling compensation is carried out by adopting a compensation algorithm; and it is ensured that the measured wind speed values under various environmental conditions are more accurate.

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 present invention relates to a sailing boat comprising an aerodynamic profile and a system for determining the characteristics of the incident air flow on its leading edge. In order to be able to precisely determine the position of the stagnation point at different regions along the leading edge of the aerodynamic profile, a system comprises: rows (S1 to S5) of pressure sensors (16) distributed on either side of the leading edge (14) and virtually forming a pattern (M1 to M5) spaced apart from each other in the form of a simple broken line; and a computer (20) connected to the pressure sensors (16). The computer (20) determines the corresponding stagnation point position along each of the patterns (M1 to M5), the stagnation point position being defined by the abscissa of the curve (a1 to a5) and by the height (z1 to z5) evaluated based on the corresponding height data from the pressure sensors (16) in the corresponding rows (S1 to S5), for which the pressure P*, interpolated based on the pressure measurements provided by the pressure sensors (16) in the corresponding rows (S1 to S5), is at a maximum.

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.

Disclosed is a system (100) for determining a pressure distribution, comprising a sensor assembly comprising a sensor configured to provide pressure data; a control module configured to receive position data indicating a spatial characteristic of the sensor assembly and to determine a pressure distribution based on the position data and the pressure data Also disclosed is a method for determining the pressure distribution comprising providing pressure data, receiving position data indicating a spatial characteristic of a sensor assembly, and determining a pressure distribution based on the position data and the pressure data.

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