297results 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 utility model discloses a foldable pitot tube device, which relates to the technical field of unmanned aerial vehicles, and comprises a pitot tube, an extension tube and a folding mechanism connected in sequence; wherein the folding mechanism comprises a first connecting seat, a second connecting seat and a connecting sleeve; a first drag reduction rectifying part is formed on the side of the first connecting seat facing the pitot tube, and a second drag reduction rectifying part is formed on the side of the connecting sleeve away from the pitot tube; an elastic rubber ring is arranged on the side of the first drag reduction rectifying part away from the pitot tube; in the folded state of the foldable pitot tube device, the connecting sleeve is separated from the first connecting seat; in the unfolded state of the foldable pitot tube device, one end of the connecting sleeve abuts against the elastic rubber ring, and the first drag reduction rectifying part, the elastic rubber ring, the connecting sleeve and the second drag reduction rectifying part form a streamlined structure. The utility model can effectively reduce the airflow impact on the folding mechanism, and effectively reduce the risk of loose connection of the folding mechanism.

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 aircraft airflow sensor includes one or more pitot inlets, ports, and / or static ports and a calibration data memory physically storing calibration data with the aircraft airflow sensor probe. The aircraft airflow sensor moreover includes where the calibration data is configured to be implemented in an air data computer (ADC).

Disclosed an airflow sensor and an airflow sensor packaging structure. The airflow sensor comprises a base, a vibrating electrode, and a fixed electrode in a stacked arrangement, wherein the base has a back cavity passing through in its thickness direction. it is intended that the fixed electrode of the air flow sensor is provided with a vent hole and the perimeter edge of the vibration sensitive area of the vibration electrode is provided with a pressure equalizing hole. In the thickness direction of the substrate, the pressure equalizing hole The projection overlaps with the projection of the vent hole, and the pressure equalizing hole, the vent hole and the gap layer channel jointly form an air release channel, which is conducive to the smooth diffusion of oil smoke entering the air flow sensor along the air release channel.

The present disclosure provides a composite sensor for detecting fluid parameters in a pipeline, including a shell with a streamlined outer surface, a fiber Bragg grating temperature sensor disposed in the shell, a fiber Bragg grating temperature and pressure sensor disposed on the shell, a fiber Bragg grating pressure pulsation sensor, a first fiber Bragg grating flow rate sensor, and a second fiber Bragg grating flow rate sensor. The fiber Bragg grating temperature sensor is used to detect the temperature of the liquid; the fiber Bragg grating temperature and pressure sensor is used to detect the temperature and pressure of the liquid; the fiber Bragg grating pressure pulsation sensor is used to detect the pressure fluctuation of the liquid; and the combination of the first fiber Bragg grating flow rate sensor and the second fiber Bragg grating flow rate sensor is used to detect the flow rate of the liquid. The above-mentioned composite sensor of the present disclosure integrates multiple sensors in a bionic fish-shaped structure and can form a wavelength division multiplexing array structure, so that the measurement points of the pressure, temperature and pressure pulsation of the hydraulic system are concise and reliable, and the risk of too many leakage points is also reduced.

The invention discloses an airspeed tube with deicing and drainage functions. The airspeed tube is composed of main parts such as a fusiform drainage opening, a waterproof deicing plate, an adapter flange, a protective sleeve and a mounting seat. The front end of the airspeed tube adopts a pointed-cone-shaped streamline design, so that airflow fluctuation and turbulence can be reduced, and the flight energy consumption is reduced. And the gas diversion trenches are arranged around, so that water drops or ice crystals can be prevented from adhering, and the measurement precision is improved. The total pressure port is located at the foremost end of the fusiform drainage port and can make contact with stable airflow, and measurement reliability is guaranteed; the static pressure openings are formed in the radial side edge of the fusiform drainage opening, and redundant design is provided for the multiple static pressure openings. And the waterproof deicing plate is provided with a deicing heating wire and a miniature water outlet and is used for heating, deicing and draining water. The total pressure pipeline and the static pressure pipeline filter melt water through a waterproof breathable film, and the melt water is prevented from entering the rear-end pressure pipeline. The heating wire and the deicing heating wire wound outside the total pressure conduit and the static pressure conduit form a series loop to improve the cooling efficiency. The design of the total pressure pagoda joint and the static pressure pagoda joint with different lengths at the tail saves the structural space and is convenient to install and maintain. While light-weight and small-size development is met, the functions of low-power-consumption intelligent deicing and drainage after deicing are achieved at the same time.

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.

A flow velocity measuring tube, a main control module, a communication module and a lithium battery are all installed on a sinking frame, the sinking frame sinks into a riverbed and enables the flow velocity measuring tube to be in the water flow direction, and the flow velocity measuring tube is a reducer tube and comprises a first tube part and a second tube part; the pipe diameter of the first pipe part is larger than that of the second pipe part in the water flow direction, pressure sensors are arranged in the circumferential direction of the first pipe part and the circumferential direction of the second pipe part, the lithium battery provides electric energy for the pressure sensors, the main control module and the communication module, and the floating body floats on the water surface and is fixed to the sinking frame through a connecting rope. The communication module and the pressure sensor are connected with the main control module. Based on the Bernoulli principle, high-precision simultaneous measurement of the flow velocity and the water level of the river is realized by adopting a differential pressure measurement mode. The sensor is simple in design structure, clear in principle, free of interference and stable in data.

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 discloses an inhaler monitoring device with an integrated electronic module and an air inlet flow rate calculation method. The inhaler monitoring device comprises a shell and a base. A cavity space is formed between the shell and the base, a PCB is installed in the cavity space, an electronic module is arranged on the PCB and comprises a sensor system, and the shell is used for containing an inhaler and transmitting air pressure changes caused by the air inlet flow speed of the inhaler to the sensor system for measurement. The air pressure change caused by the air inlet flow speed of the inhaler can be conducted to the sensor system to be detected, so that parameters in airflow can be measured, the air pressure is detected, the air inlet flow speed of an air inlet of the inhaler is calculated, an inspiration flow curve is drawn at a client side, and accurate flow change data can be fed back in real time.

The invention relates to an air data indication and calibration device (1) and a method for a vertical take-off and landing aircraft, in particular a helicopter (50), for providing information of the airspeed of the vertical take-off and landing aircraft and for providing information of the height of the vertical take-off and landing aircraft. The vertical take-off and landing aircraft comprises pitot tube equipment (51) used for determining stagnation point air pressure at the position where the pitot tube equipment (51) is located; and the static pressure hole equipment (52) is used for determining the static pressure at the position of the static pressure hole equipment (52). The air data indicating device (1) comprises an airspeed and altitude determining module (2) used for determining the airspeed and altitude of the vertical take-off and landing aircraft in real time according to flight data by using a regression device (3) obtained by training an artificial neural network through training data.

The utility model discloses an on-line detection device for measuring wind speed and wind quantity in a pipeline, which comprises a shell, a balance straightener, a pressure tapping pipe network and a transmitting component, the balance straightener and the pressure tapping pipe network are arranged in the shell, the balance straightener is positioned on the front side of the inner cavity of the shell, the pressure tapping pipe network is positioned behind the balance straightener and positioned in the middle of the inner cavity of the shell, and the transmitting component is positioned in the middle of the inner cavity of the shell. The transmitting assembly is connected with the pressure tapping pipe network and located outside the shell. The balance straightener is used for adjusting, straightening and uniformizing disturbed air flow, the flow is adjusted to be balanced and steady in a short process, the balance straightener has the same effect as a straight pipe section with enough length, and the problem that a long straight pipe cannot be arranged due to insufficient space is solved; multi-point total pressure and static pressure measuring points are arranged at different positions on the flow velocity section, the accuracy and stability of wind speed and wind quantity measurement are improved, accurate and stable data are further obtained and serve as control signals of an automatic control system, and the stability and operability of the control system can be enhanced.

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.

A testing device, related method for using the testing device and a production device arranged based on a predicted ambient temperature determined using the testing device, the testing device including a circuitry of a first form factor that corresponds to a second form factor of the production device. Circuitry includes heat-generating electrical components to simulate thermal generation of the production device. The circuitry also includes sensors to measure at least one characteristic of airflow of the testing device and at least one temperature of the testing device. The sensors include a first sensor disposed upstream of the airflow, and a second sensor disposed downstream of the airflow. The circuitry also includes processing circuitry to receive sensor data from the sensors indicative the characteristics of airflow and the temperatures of the testing device, and to determine a predicted ambient temperature proximate to the production device based on the sensor data.

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.