CN219551488U - Multi-channel probe measurement system applied to aircraft - Google Patents

Abstract

The utility model provides a multichannel probe measurement system applied to an aircraft, and relates to the technical field of aircraft flow field detection, wherein the system comprises: a porous probe, a pitot tube, and/or a measurement host, the measurement host comprising a plurality of detection channels, the plurality of detection channels comprising an angle detection channel and a velocity detection channel; the porous probe is connected to the measurement host through the angle detection channel; the pitot tube is connected to the measurement host through the speed detection channel; and the measurement host is used for obtaining the operation parameters of the aircraft according to the data acquired by the porous probe and the data acquired by the pitot tube. The method can collect a plurality of measurement data at the same position, so that the collected data volume is more, the detection precision of the measurement host is improved, a plurality of measurement data at different positions can be collected, the data at different positions can be measured at the same time, and the detection efficiency of the measurement host is improved.

Description

Multi-channel probe measurement system applied to aircraft

Technical Field

The utility model relates to the technical field of flow field detection of aircrafts, in particular to an eight-channel probe measurement system applied to an aircraft.

Background

The acquisition of the flow field data of the aircraft has great significance for the safe flight of the aircraft. In the prior art, most of the measurement of the angle information, incoming flow speed and other operation parameters of the aircraft are measured by using a porous probe.

However, in the practical application of the aircraft, the detection channels of the adopted detection devices are limited, so that the collected data volume is limited, errors exist in the detection result, and if more data volume is required to be obtained, a plurality of detection devices are required to be arranged, so that the overall weight of the aircraft is increased, and the power consumption is increased. In some wind tunnel test scenes, the existing detection equipment also increases test cost due to limited acquired detection data.

Under such circumstances, it is necessary to provide a system capable of improving the accuracy and efficiency of detection of flow field airflow of an aircraft.

Disclosure of Invention

In view of the above, the present utility model aims to provide a multi-channel probe measurement system for an aircraft, which can specifically solve the existing problems.

Based on the above object, the present utility model proposes a multi-channel probe measurement system for use in an aircraft, said system comprising: the device comprises a porous probe, a pitot tube and a measurement host, wherein the measurement host comprises a plurality of detection channels, and the plurality of detection channels comprise an angle detection channel and/or a speed detection channel; the porous probe is connected to the measurement host through the angle detection channel; the pitot tube is connected to the measurement host through the speed detection channel; and the measurement host is used for obtaining the operation parameters of the aircraft according to the data acquired by the porous probe and the data acquired by the pitot tube.

Optionally, the system comprises at least one multi-hole probe, and the number of the plurality of angle detection channels of the measurement host is obtained according to the number of the at least one multi-hole probe and the number of holes of each multi-hole probe; the multi-hole probe is connected to the measuring host through a connecting component, the connecting component is provided with pressure guide pipes corresponding to each angle detection channel one by one, and each hole of the multi-hole probe is connected with each angle detection channel one by one through a pressure guide pipe.

Optionally, the measurement host includes a housing, a processor disposed in the housing, and a sensor corresponding to each detection channel, where the sensor is connected to the processor, and the sensor is configured to transmit the collected pressure data of the porous probe to the processor in a digital communication manner.

Optionally, the multi-hole probe is a five-hole probe, the measurement host has eight measurement channels, and the eight measurement channels include five angle detection channels, two speed detection channels and one atmospheric pressure detection channel; five holes of the five-hole probe are respectively connected with the five angle detection channels; the pitot tube comprises a total pressure hole and a static pressure hole, and the total pressure hole and the static pressure hole are respectively connected with the two speed detection channels; the atmospheric pressure detection channel is provided with an absolute pressure sensor, and the absolute pressure sensor is used for reading the current atmospheric pressure.

Optionally, the sensor of each detection channel corresponding to the measurement host includes a first differential pressure sensor, a second differential pressure sensor, a third differential pressure sensor, a fourth differential pressure sensor, a fifth differential pressure sensor, a sixth differential pressure sensor, a seventh differential pressure sensor and the absolute pressure sensor, where the first to fifth differential pressure sensors are respectively in one-to-one correspondence with the five angle detection channels, and the sixth differential pressure sensor and the seventh differential pressure sensor are respectively in one-to-one correspondence with the two speed detection channels; the processor of the measurement host is used for obtaining the angle parameter of the aircraft according to the pressure data of the five-hole probes received by the first to fifth differential pressure sensors, and obtaining the air flow speed of the environment where the aircraft is located according to the pressure data of the pitot tubes received by the sixth differential pressure sensor and the seventh differential pressure sensor.

Optionally, the measurement host further includes: the temperature acquisition circuit, the power supply circuit, the communication circuit and the storage circuit are respectively connected to the processor; the shell is provided with a connecting socket, and the temperature acquisition circuit, the power supply circuit, the communication circuit and the storage circuit are connected with external equipment through the connecting socket; the temperature acquisition circuit comprises a temperature sensor and a temperature acquisition chip, wherein the temperature sensor is connected with the temperature acquisition chip, the temperature acquisition chip is connected with the processor, and the temperature acquisition circuit is used for acquiring the current atmospheric temperature; the communication circuit comprises a communication chip and a serial port communication module, the communication chip is connected with the processor and the serial port communication module, and the serial port communication module is used for connecting an upper computer and carrying out data transmission with the upper computer; the storage circuit is used for storing data required by the processor in a data processing process, the storage circuit comprises a storage management chip, a storage card and a transmission interface, the transmission interface and the storage card are connected with the storage management chip, the storage management chip is connected with the processor, and the storage management chip is used for managing the data in the storage card and the data required by the processor in the data processing process.

Optionally, the housing includes a housing having electromagnetic shielding and temperature control functions.

Overall, the advantages of the utility model and the experience brought to the user are:

the utility model provides a multichannel probe measurement system applied to an aircraft, which comprises a porous probe, a pitot tube and a measurement host, wherein the measurement host comprises a plurality of detection channels, and the plurality of detection channels comprise an angle detection channel and a speed detection channel; the porous probe is connected to the measurement host through an angle detection channel; the pitot tube is connected to the measuring host computer through the speed detection channel; the measuring host is used for obtaining the operation parameters of the aircraft according to the data collected by the porous probe and the data collected by the pitot tube. The method can collect a plurality of measurement data at the same position, so that the collected data volume is more, the detection precision of the measurement host is improved, a plurality of measurement data at different positions can be collected, the data at different positions can be measured at the same time, and the detection efficiency of the measurement host is improved.

Drawings

In the drawings, the same reference numerals refer to the same or similar parts or elements throughout the several views unless otherwise specified. The figures are not necessarily drawn to scale. It is appreciated that these drawings depict only some embodiments according to the disclosure and are not therefore to be considered limiting of its scope.

FIG. 1 shows a system architecture diagram of a multichannel probe measurement system of the utility model applied to an aircraft;

FIG. 2 shows another system architecture diagram of the multi-channel probe measurement system of the present utility model applied to an aircraft;

FIG. 3 is a schematic diagram of a portion of a measurement host according to an embodiment of the utility model;

FIG. 4 shows a schematic diagram of an eight-channel probe measurement system according to an embodiment of the utility model;

FIG. 5 shows a hardware architecture diagram of a measurement host;

FIG. 6 shows a schematic diagram of a multi-channel probe measurement system according to an embodiment of the utility model;

fig. 7 shows a schematic diagram of the practical application of the multi-channel probe measurement system of the present embodiment on an aircraft.

Detailed Description

The utility model is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the utility model and are not limiting of the utility model. It should be noted that, for convenience of description, only the portions related to the present utility model are shown in the drawings.

It should be noted that, without conflict, the embodiments of the present utility model and features of the embodiments may be combined with each other. The utility model will be described in detail below with reference to the drawings in connection with embodiments.

Fig. 1 shows a system architecture diagram of a multichannel probe measurement system for an aircraft according to the utility model.

Referring to fig. 1, a multi-channel probe measurement system for an aircraft according to the present embodiment includes: the probe comprises a porous probe, a pitot tube 102 and a measurement host 103, wherein the measurement host 103 comprises a plurality of detection channels, the plurality of detection channels comprise an angle detection channel and/or a speed detection channel, the porous probe is connected to the measurement host 103 through the angle detection channel, and the pitot tube 102 is connected to the measurement host 103 through the speed detection channel. The measurement host 103 is configured to obtain an operation parameter of the aircraft according to the data collected by the porous probe and the data collected by the pitot tube 102.

It should be noted that, the plurality of detection channels in this embodiment include an angle detection channel and/or a speed detection channel, that is, the plurality of detection channels in this embodiment may include only the angle detection channel to detect only angle data of the aircraft according to actual requirements, may include only the speed detection channel to detect only airflow speed of an environment where the aircraft is located according to actual requirements, and may include both the angle detection channel and the speed detection channel to detect a flight angle of the aircraft and airflow speed of the environment where the aircraft is located according to actual requirements. For convenience of explanation, the following description will be given with respect to a plurality of detection channels including an angle detection channel and a speed detection channel.

Specifically, the angle detection channel is used for receiving pressure data acquired by the porous probe, and after the pressure data is received by a sensor at the measurement host 103, the pressure data is processed by the processor to obtain angle parameters of the aircraft, wherein the angle parameters comprise a pitch angle and a yaw angle. The speed detection channel is used for receiving pressure data acquired by the pitot tube 102, and after the pressure data is received by a sensor at the measurement host 103, the processor processes the pressure data to obtain the air flow speed of the environment where the aircraft is located.

The multi-hole probe of the multi-channel probe measurement system of the present embodiment may include any one of a three-hole probe, a five-hole probe, a seven-hole probe, or any two of a three-hole probe, a five-hole probe, a seven-hole probe, or a combination of a plurality of probes with different hole numbers. Referring to fig. 1, the multi-well probe includes a total of 3 multi-well probes of multi-well probe 1, multi-well probe 2, and multi-well probe 3, and the angle detection channel includes 15 angle detection channels assuming that the 3 multi-well probes are a three-well probe, a five-well probe, and a seven-well probe, respectively.

Fig. 2 shows another system architecture diagram of the multi-channel probe measurement system applied to an aircraft provided by the present embodiment. Referring to fig. 2, the multi-well probe includes one multi-well probe, and the angle detection channel includes 5 angle detection channels assuming that the multi-well probe is a five-well probe 101.

In this embodiment, when multiple porous probes are connected to the measurement host 103, multiple measurement data at the same position can be collected, so that the collected data volume is more, the detection accuracy of the measurement host 103 is improved, multiple measurement data at different positions can be also collected, and the data at different positions can be measured at the same time, so that the detection efficiency of the measurement host 103 is improved. Namely, the embodiment can improve the accuracy and the detection efficiency of the detection result of the measurement host 103 on the flow field airflow of the aircraft.

In this embodiment, the multi-channel probe measurement system includes at least one multi-hole probe, i.e. the number of multi-hole probes may be one or more, and the number of the plurality of angle detection channels of the measurement host 103 is obtained according to the number of at least one multi-hole probe and the number of holes of each multi-hole probe.

In this embodiment, the number of the plurality of angle detection channels of the measurement host 103 is the sum of the hole numbers of all the multi-hole probes, so that the pressure data collected by each hole of each multi-hole probe can be transmitted to the measurement host 103.

For example, if the multi-channel probe measurement system includes one seven-hole probe, the number of angle detection channels of the measurement host 103 is seven. For example, if the multi-channel probe measurement system includes one seven-hole probe and one three-hole probe, the number of angle detection channels of the measurement host 103 is ten. For another example, if the multi-channel probe measurement system includes two seven-hole probes and one three-hole probe, the number of angle detection channels of the measurement host 103 is seventeen.

It should be noted that, the above calculation is an angle detection channel, and the total channel number of the measurement host 103 of the present embodiment is the sum of the number of angle detection channels, the speed detection channel, and the atmospheric pressure detection channel, where the atmospheric pressure detection channel is provided with an absolute pressure sensor, and the absolute pressure sensor is used for reading the current atmospheric pressure.

In this embodiment, in order to improve the applicability of the multi-channel probe measurement system, the multi-channel probe is connected to the measurement host 103 through the connection assembly 202, and the connection assembly 202 is used to transmit the pressure data collected by each hole of the multi-channel probe to the measurement host 103. The connection assembly 202 has a pressure pipe corresponding to each angle detection channel, and each hole of the multi-hole probe is connected to each angle detection channel through a pressure pipe, so that pressure data of each hole can be independently transmitted to the sensor in the measurement host 103.

In one example, the connection assembly 202 may be an integrated module (not shown in the figure) with a plurality of independent impulse pipes, for example, the impulse pipe assembly is an integrated assembly with connectors at two ends, the connectors are used for connecting the porous probe and the measurement host 103, and a plurality of hollow conduits penetrating through the connectors are arranged in the middle of the connection assembly 202, so that on one hand, the integration of the impulse pipes can be realized, the durability of the impulse pipes can be improved, and on the other hand, the volume of the impulse pipes can be reduced.

In one example, the connection assembly 202 may also be a connection assembly 202 formed by a plurality of independent impulse pipes, as shown in fig. 1 or fig. 2, whose two ends are respectively connected to the multi-hole probe and the measurement host 103.

In another example, the connection assembly 202 may be used to transmit electrical signals while transmitting the pressure data collected by each well of the multi-well probe to the measurement host 103, for example, a signal transmission line is disposed in the integrated connection assembly 202, where the signal transmission line connects the measurement host 103 and a device disposed at the location of the multi-well probe, so as to increase the integration level of the connection assembly 202 and reduce the overall volume of the multi-channel probe measurement system of the present embodiment.

In this embodiment, the measurement component may use a rubber pressure guiding tube, so that the pressure guiding tube has better flexibility, so that the situation that the porous probe or the pitot tube 102 and the measurement host 103 can only be at a fixed position due to rigid connection is avoided, the placement options of the porous probe and the pitot tube 102 are increased, and the installation and the disassembly between the porous probe and the pitot tube 102 and the measurement host 103 are facilitated.

Fig. 3 shows a partial schematic diagram of a measurement host 103. In this embodiment, the measurement host 103 includes a housing, a processor disposed in the housing, and a sensor corresponding to each detection channel, where the sensor is connected to the processor 104, and the sensor is configured to transmit the collected pressure data of the porous probe to the processor 104 in a digital communication manner. For example, the sensor communicates the collected pressure data of the porous probe to the processor 104 via an integrated circuit bus (Inter-Integrated Circuit, IIC) or serial peripheral interface (Serial Peripheral Interface, SPI) communication.

As shown in fig. 3, the sensors include sensor 1, sensor 2, sensor 3, sensor 4.

Therefore, the sensor in this embodiment is a digital sensor, and the data acquisition rate of the sensor can reach 400Hz at maximum by adopting a digital communication mode, and the sensor can provide 50Hz data output of 50 data moving averages for the back-end algorithm at the data update rate, so that the processor 104 can calculate the result data faster. Meanwhile, the sensor adopts a digital communication mode instead of analog signal output, is favorable for reducing the interference of environmental factors on air pressure data, has the advantages of anti-interference, small volume and low power consumption, can reduce the influence of accuracy drift of analog-digital sampling of a sensor circuit on measurement data, has stronger application scene and environmental adaptability, and can more meet the harsh environmental requirements of an aircraft.

Fig. 4 shows a schematic structural diagram of an eight-channel probe measurement system. In this embodiment, when the multi-hole probe of the multi-channel probe measurement system is a five-hole probe, the measurement host 103 has eight measurement channels including five angle detection channels, two speed detection channels, and one atmospheric pressure detection channel; five holes of the five-hole probe are respectively connected with five angle detection channels and are used for measuring angle parameters of the aircraft, wherein the angle parameters comprise pitch angle and yaw angle of the aircraft. The pitot tube 102 includes a total pressure orifice and a static pressure orifice, which are respectively connected to two velocity sensing channels for measuring the airflow velocity of the environment in which the aircraft is located. The atmospheric pressure detection channel is provided with an absolute pressure sensor, and the absolute pressure sensor is used for reading the current atmospheric pressure.

The five-hole probe is a multi-hole probe device for measuring data according to a differential pressure method, and has wide application in the test scene of an aerodynamic flow field, in particular to the test of an aerospace flow field. The center of the front end of the five-hole probe and the positions which are vertically and bilaterally symmetrical are respectively provided with pressure measuring holes, the five-hole probe can generate different pressures for the five pressure measuring holes through air flow to determine the fluid characteristics, and the total pressure and the static pressure of a flow field and the flow speed and the flow direction of the air flow are calculated.

The pitot tube 102 is a tubular device for measuring the total pressure and the static pressure of the air flow to determine the speed of the air flow, and the pressure can be measured through the pitot tube 102, and the speed of the air flow can be directly calculated by applying the Bernoulli theorem, so that the speed measuring precision is good.

Considering that the five-hole probe can measure the velocity component of the aircraft, the pitot tube 102 is adopted to measure the air flow velocity of the environment where the aircraft is located in the embodiment due to the complexity of the self structure and the calibration before use, and the five-hole probe is used for measuring the pitch angle and the yaw angle of the aircraft, so that the complex calibration check work when the air flow velocity is measured through the five-hole probe is reduced, the measurement complexity is reduced, and the measurement precision and the measurement speed of the operation parameters of the aircraft can be greatly improved.

Specifically, as shown in fig. 4, the sensors of the measurement host 103 corresponding to each detection channel include a first differential pressure sensor 1031, a second differential pressure sensor 1032, a third differential pressure sensor 1033, a fourth differential pressure sensor 1034, a fifth differential pressure sensor 1035, a sixth differential pressure sensor 1036, a seventh differential pressure sensor 1037, and an absolute pressure sensor 1038, the first to fifth differential pressure sensors respectively corresponding to five angle detection channels one by one, and the sixth differential pressure sensor 1036 and the seventh differential pressure sensor 1037 respectively corresponding to two speed detection channels one by one; the processor 104 of the measurement host 103 is configured to obtain an angle parameter of the aircraft according to the pressure data of the five-hole probe 101 received by the first to fifth differential pressure sensors, and obtain the air flow velocity of the environment in which the aircraft is located according to the pressure data of the pitot tube 102 received by the sixth differential pressure sensor 1036 and the seventh differential pressure sensor 1037.

In one example, the processor 104 employs an ATmega128 single-chip microcomputer, which has the functions of quick start and flexible program setting. The processor 104 is configured to process data collected by the first through seventh differential pressure sensors and the absolute pressure sensor.

Referring to fig. 4, a first differential pressure sensor 1031, a second differential pressure sensor 1032, a third differential pressure sensor 1033, a fourth differential pressure sensor 1034, a fifth differential pressure sensor 1035, a sixth differential pressure sensor 1036, a seventh differential pressure sensor 1037, and an absolute pressure sensor 1038 are respectively coupled to the processor 104 via separate transmission channels, each having its unique corresponding communication address.

In this embodiment, the measurement host 103 further includes: the temperature acquisition circuit 105, the power supply circuit 106, the communication circuit 107, and the storage circuit 108 are connected to the processor 104, respectively, and the temperature acquisition circuit 105, the power supply circuit 106, the communication circuit 107, and the storage circuit 108 are connected to the processor. Referring to fig. 5, the housing 501 is provided with a connection socket 502, and the temperature acquisition circuit 105, the power supply circuit 106, the communication circuit 107, and the storage circuit 108 are connected to external devices such as a power supply through the connection socket 502.

The temperature acquisition circuit 105 includes a temperature sensor 1051 and a temperature acquisition chip 1052, the temperature sensor 1051 is connected with the temperature acquisition chip 1052, the temperature acquisition chip 1052 is connected with the processor 104, and the temperature acquisition circuit 105 is used for acquiring the current atmospheric temperature. The processor 104 can obtain the current environment temperature of the aircraft according to the temperature data acquired by the temperature sensor 1051, calculate the air density, and calculate the current incoming flow speed of the five-hole probe according to the preset calibration data of the pitot tube 102 and the bernoulli equation.

In this embodiment, the communication circuit 107 includes a communication chip 1071 and a serial communication module 1072, the communication chip 1071 is connected to the processor 104 and the serial communication module 1072, and the serial communication module 1072 is used for connecting to an upper computer and performing data transmission with the upper computer.

In one example, the communication chip 1071 and the serial communication module 1072 adopt RS485 protocol for transmission, and may select a request response mode or a direct transmission mode, and a developer may set a corresponding transmission mode according to actual application requirements.

In this embodiment, the storage circuit 108 is configured to store data required by the processor 104 during data processing, where the storage circuit includes a storage management chip 1081, a memory card 1083, and a transmission interface 1082, the transmission interface 504 and the memory card are connected to the storage management chip, the storage management chip is connected to the processor 104, and the storage management chip 1081 is configured to manage the data in the memory card 1083 and the data required by the processor 104 during data processing. The transport interface 504 may be a USB interface for interfacing with other devices of the aircraft to enable writing and exporting of data to and from the storage management chip 1081.

For example, when the processor 104 calculates the pressure value from the pressure data, the calibration value and the calibration coefficient of each hole pressure data of the five-hole probe stored in the memory card 1083 in advance are retrieved, or after the processor 104 obtains the pressure value, the obtained pressure value is stored in the memory card 1083, and the memory card of this embodiment may be a TF card.

In this embodiment, the power supply circuit is configured to supply power to the measurement host 103, where the power supply circuit includes a power regulator, one end of the power regulator is connected to the measurement host 103, and the other end of the power regulator is connected to a power supply, and is configured to convert the power supply into a working voltage of the measurement host 103, and the working voltage range of the measurement host 103 in this embodiment is 4.5-45V.

In one example, the power supply voltage stabilizer may be an LM2596 voltage stabilizer, and the LM2596 voltage stabilizer uses a buck power management monolithic integrated circuit, which can output 3A driving current, and meanwhile has good linearity and load regulation characteristics, ensures stable output performance, and can reduce measurement errors caused by voltage instability to the sensor.

Fig. 5 shows a schematic hardware structure of the measurement host 103, referring to fig. 5, the measurement host 103 has a housing 501, and the processor 104, the sensor, the temperature acquisition circuit 105, the power supply circuit 106, the communication circuit 107, and the storage circuit 108 are disposed in the housing.

The connection socket 502 may be an 8-core integrated socket as shown in fig. 5, and the temperature acquisition circuit 105, the power circuit 106, and the communication circuit 107 of this embodiment are all electrically connected to the connection socket 502.

Wherein the housing 501 is provided with a measurement interface 505, the measurement interface 505 is for connection with the connection assembly 202 for enabling connection of the connection assembly 202 with the measurement host 103. Wherein the number of measurement interfaces 505 corresponds to the number of detection channels of the measurement body.

The housing 501 of the present embodiment includes a case having electromagnetic shielding and temperature control functions. For example, the housing of the measurement host 103 in this embodiment is an all-metal aluminum alloy housing, which can realize electromagnetic shielding function and effectively prevent electromagnetic interference.

For example, a plurality of heat dissipation grooves may be provided on the housing, or an opening and closing member may be provided on the heat dissipation grooves to realize a switching function for the heat dissipation grooves, and when the temperature is higher than a preset value, the opening and closing member is opened, and when the temperature is lower than the preset value, the air convection between the inside and the outside of the measurement host 103 is realized through the heat dissipation grooves, and when the temperature is lower than the preset value, the opening and closing member is closed, so that the air convection between the inside and the outside of the measurement host 103 is reduced. Or, a temperature control material is arranged on the inner wall of the shell so as to achieve the purpose of temperature control.

In addition, referring to fig. 5, the measurement host 103 of the present embodiment further includes a power supply switch 503 and an operation indicator lamp 109, where the power supply switch is used to implement power supply control of the measurement host 103, and the operation indicator lamp 109 is used to display an operation state of the measurement host 103, for example, when the measurement host 103 is in an operation state, the operation indicator lamp 109 is in a green light state, and when the measurement host 103 is in a standby state, the operation indicator lamp 109 is in a red light state.

The following describes the workflow of the system for the multi-channel probe measurement system for an aircraft according to the present embodiment based on the workflow of the processor 104:

the processor 104 obtains the pitch angle and the yaw angle of the aircraft according to the received pressure data acquired by the first to fifth differential pressure sensors, the processor 104 obtains the air flow speed of the environment where the aircraft is located according to the received pressure data acquired by the sixth differential pressure sensor and the seventh differential pressure sensor, the processor 104 obtains the ambient atmospheric pressure and the altitude where the aircraft is located according to the received pressure data acquired by the absolute pressure sensor, and the processor 104 can also obtain the current atmospheric temperature according to the temperature data acquired by the temperature sensor.

Therefore, the measurement accuracy advantages of the five-hole probe, the pitot tube 102 and the sensors can be furthest exerted, the functions of processing the detection data on line and outputting the flight parameters of the aircraft are realized, and the possibility is provided for meeting the requirements of various aircrafts.

Fig. 4 is a schematic structural diagram of the eight-channel probe measurement system according to the present embodiment, and when the number of channels of the measurement host 103 is changed, the schematic structural diagram of the multi-channel probe measurement system is shown in fig. 6, and referring to fig. 6, the multi-channel probe has a plurality of multi-channel probes, which may include a multi-channel probe a and a multi-channel probe b.

The multi-channel probe measurement system applied to the aircraft provided by the embodiment comprises a multi-hole probe, a pitot tube 102 and a measurement host 103, wherein the measurement host 103 comprises a plurality of detection channels, and the plurality of detection channels comprise an angle detection channel and a speed detection channel; the porous probe is connected to the measurement host 103 through an angle detection channel; pitot tube 102 is connected to measurement host 103 through the speed detection channel; the measurement host 103 is used for obtaining the operation parameters of the aircraft according to the data collected by the porous probe and the data collected by the pitot tube 102. Multiple measurement data at the same position can be acquired, so that the acquired data volume is more, the detection precision of the measurement host 103 is improved, multiple measurement data at different positions can be acquired, the data at different positions can be measured at the same time, and the detection efficiency of the measurement host 103 is improved.

The processor of this embodiment obtains the operation parameters of the aircraft according to the data collected by the porous probe and the data collected by the pitot tube, which may be: and acquiring pressure data acquired by the porous probe and the pitot tube, acquiring a calibration coefficient of the aircraft, and performing reverse interpolation calculation according to the calibration coefficient and the pressure data to obtain the operation parameters of the aircraft.

In this embodiment, the calibration coefficient of the aircraft is obtained according to the pressure value and the calibration formula of the aircraft under the preset operation parameters. The preset operation parameters are parameters obtained by performing experiments in a wind tunnel, for example, performing a blowing experiment in a standard wind tunnel to obtain corresponding experimental data, obtaining pressure values, deflection angles and pitch angles of different pressure sensing holes of the probe under a specific flow rate, and taking the pressure values, the deflection angles and the pitch angles into a calibration formula to obtain a calibration coefficient.

In this embodiment, the operating parameters include at least one of pitch angle, yaw angle, total pressure, and dynamic pressure of the aircraft. Taking the example that the porous probe connected with the measurement host 103 is a five-hole probe, the five-hole probe includes an upper hole, a lower hole, a middle hole, zuo Kong and a right hole, and the calibration formula can be:

pitch coefficient= (lower pore pressure value-upper pore pressure value)/(middle pore pressure value-average surrounding 4 pore pressure value)

Yaw coefficient= (right hole pressure value-left hole pressure value)/(middle hole pressure value-surrounding 4 hole pressure average value)

Total pressure coefficient= (total pressure value-mesopore pressure value)/(mesopore pressure value-average value of surrounding 4-pore pressure)

Dynamic pressure coefficient= (total pressure value-static pressure value)/(mesopore pressure value-average value of surrounding 4-pore pressure)

The pressure values of the upper hole, the lower hole, the middle hole, the Zuo Kong and the right hole are the pressure values of each hole of the five-hole probe obtained by experiments in the wind tunnel. The total and static pressure values are the pressure values to which the two holes of the pitot tube are subjected.

After calibration, pitch angle, yaw angle, total pressure coefficient and dynamic pressure coefficient corresponding to each group of pitch coefficient and yaw coefficient can be obtained. When the calibrated porous probe is applied to the flight scene of the aircraft, the pitch angle, yaw angle, total pressure value and dynamic pressure value of the current aircraft can be obtained by acquiring data acquired by the measuring host 103 and sensors connected with the porous probe and the pitot tube, namely, the measured value of the aircraft, and performing reverse interpolation calculation through the measured value. The measuring system has good detection effect, has multiple channels, can obtain multiple measured values, and can reduce measurement errors.

Fig. 7 shows a practical application of the multi-channel probe measurement system of the present embodiment on an aircraft, where the multi-channel probe measurement system of the present embodiment is disposed inside an aircraft 700, and can be used to measure a target position by increasing a length of a pressure pipe, where the target position may be a nose and two wings of the aircraft, for example, as shown in fig. 7, the multi-channel probe measurement system includes 3 multi-hole probes, and the three multi-hole probes are disposed on the nose, the left wing and the right wing of the aircraft respectively, so as to obtain pressure data of the nose, the left wing and the right wing, and further monitor operation parameters of the aircraft, so as to ensure smooth operation of the aircraft.

The processor 104 in this embodiment may also be an integrated circuit chip with signal processing capability. In implementation, the steps of the above method may be performed by integrated logic circuits of hardware in a processor or by instructions in the form of software. The processor 104 may be a general-purpose processor, including a central processing unit (Central Processing Unit, CPU for short), a network processor (Network Processor, NP for short), etc.; but may also be a Digital Signal Processor (DSP), application Specific Integrated Circuit (ASIC), an off-the-shelf programmable gate array (FPGA) or other programmable logic device, discrete gate or transistor logic device, discrete hardware components. The disclosed methods, steps, and logic blocks in the embodiments of the present utility model may be implemented or performed. A general purpose processor may be a microprocessor or the processor may be any conventional processor or the like. The steps of the method disclosed in connection with the embodiments of the present utility model may be embodied directly in the execution of a hardware decoding processor, or in the execution of a combination of hardware and software modules in a decoding processor. The software modules may be located in a random access memory, flash memory, read only memory, programmable read only memory, or electrically erasable programmable memory, registers, etc. as well known in the art. The storage medium is positioned in the memory, the processor reads the information in the memory, and the processing of the pressure data acquired by the sensor is completed by combining the hardware of the processor.

It should be noted that:

the algorithms and displays presented herein are not inherently related to any particular computer, virtual system, or other apparatus. Various general-purpose systems may also be used with the teachings herein. The required structure for a construction of such a system is apparent from the description above. In addition, the present utility model is not directed to any particular programming language. It will be appreciated that the teachings of the present utility model described herein may be implemented in a variety of programming languages, and the above description of specific languages is provided for disclosure of enablement and best mode of the present utility model.

In the description provided herein, numerous specific details are set forth. However, it is understood that embodiments of the utility model may be practiced without these specific details. In some instances, well-known methods, structures and techniques have not been shown in detail in order not to obscure an understanding of this description.

Similarly, it should be appreciated that in the above description of exemplary embodiments of the utility model, various features of the utility model are sometimes grouped together in a single embodiment, figure, or description thereof for the purpose of streamlining the disclosure and aiding in the understanding of one or more of the various inventive aspects. However, the disclosed method should not be construed as reflecting the intention that: i.e., the claimed utility model requires more features than are expressly recited in each claim. Rather, as the following claims reflect, inventive aspects lie in less than all features of a single foregoing disclosed embodiment. Thus, the claims following the detailed description are hereby expressly incorporated into this detailed description, with each claim standing on its own as a separate embodiment of this utility model.

Those skilled in the art will appreciate that the modules in the apparatus of the embodiments may be adaptively changed and disposed in one or more apparatuses different from the embodiments. The modules or units or components of the embodiments may be combined into one module or unit or component and, furthermore, they may be divided into a plurality of sub-modules or sub-units or sub-components. Any combination of all features disclosed in this specification (including any accompanying claims, abstract and drawings), and all of the processes or units of any method or apparatus so disclosed, may be used in combination, except insofar as at least some of such features and/or processes or units are mutually exclusive. Each feature disclosed in this specification (including any accompanying claims, abstract and drawings), may be replaced by alternative features serving the same, equivalent or similar purpose, unless expressly stated otherwise.

Furthermore, those skilled in the art will appreciate that while some embodiments described herein include some features but not others included in other embodiments, combinations of features of different embodiments are meant to be within the scope of the utility model and form different embodiments. For example, in the following claims, any of the claimed embodiments can be used in any combination.

Various component embodiments of the utility model may be implemented in hardware, or in software modules running on one or more processors, or in a combination thereof. Those skilled in the art will appreciate that some or all of the functions of some or all of the components in a virtual machine creation system according to embodiments of the utility model may be implemented in practice using a microprocessor or Digital Signal Processor (DSP). The present utility model can also be implemented as an apparatus or system program (e.g., a computer program and a computer program product) for performing a portion or all of the methods described herein. Such a program embodying the present utility model may be stored on a computer readable medium, or may have the form of one or more signals. Such signals may be downloaded from an internet website, provided on a carrier signal, or provided in any other form.

It should be noted that the above-mentioned embodiments illustrate rather than limit the utility model, and that those skilled in the art will be able to design alternative embodiments without departing from the scope of the appended claims. In the claims, any reference signs placed between parentheses shall not be construed as limiting the claim. The word "comprising" does not exclude the presence of elements or steps not listed in a claim. The word "a" or "an" preceding an element does not exclude the presence of a plurality of such elements. The utility model may be implemented by means of hardware comprising several distinct elements, and by means of a suitably programmed computer. In the unit claims enumerating several means, several of these means may be embodied by one and the same item of hardware. The use of the words first, second, third, etc. do not denote any order. These words may be interpreted as names.

The foregoing is merely illustrative of the present utility model, and the present utility model is not limited thereto, and any person skilled in the art will readily recognize that various changes and substitutions are possible within the scope of the present utility model. Therefore, the protection scope of the present utility model shall be subject to the protection scope of the claims.

Claims (7)

1. A multi-channel probe measurement system for use in an aircraft, the system comprising: the device comprises a porous probe, a pitot tube and a measurement host, wherein the measurement host comprises a plurality of detection channels, and the plurality of detection channels comprise an angle detection channel and/or a speed detection channel;

the porous probe is connected to the measurement host through the angle detection channel;

the pitot tube is connected to the measurement host through the speed detection channel;

and the measurement host is used for obtaining the operation parameters of the aircraft according to the data acquired by the porous probe and the data acquired by the pitot tube.

2. The multi-channel probe measurement system of claim 1, wherein the system comprises at least one multi-well probe, and the number of the plurality of angle detection channels of the measurement host is obtained according to the number of the at least one multi-well probe and the number of wells of each multi-well probe;

the multi-hole probe is connected to the measuring host through a connecting component, the connecting component is provided with pressure guide pipes corresponding to each angle detection channel one by one, and each hole of the multi-hole probe is connected with each angle detection channel one by one through a pressure guide pipe.

3. The multi-channel probe measurement system of claim 2, wherein the measurement host includes a housing, a processor disposed within the housing, and a sensor corresponding to each detection channel, the sensor being coupled to the processor, the sensor being configured to digitally communicate the collected pressure data of the multi-channel probe to the processor.

4. The multi-channel probe measurement system of claim 3, wherein the multi-hole probe is a five-hole probe, the measurement host has eight measurement channels including five angle detection channels, two speed detection channels, and one atmospheric pressure detection channel;

five holes of the five-hole probe are respectively connected with the five angle detection channels;

the pitot tube comprises a total pressure hole and a static pressure hole, and the total pressure hole and the static pressure hole are respectively connected with the two speed detection channels;

the atmospheric pressure detection channel is provided with an absolute pressure sensor, and the absolute pressure sensor is used for reading the current atmospheric pressure.

5. The multi-channel probe measurement system of claim 4, wherein the sensor of the measurement host corresponding to each detection channel comprises a first differential pressure sensor, a second differential pressure sensor, a third differential pressure sensor, a fourth differential pressure sensor, a fifth differential pressure sensor, a sixth differential pressure sensor, a seventh differential pressure sensor, and the absolute pressure sensor,

the first to fifth differential pressure sensors are respectively in one-to-one correspondence with the five angle detection channels, and the sixth differential pressure sensor and the seventh differential pressure sensor are respectively in one-to-one correspondence with the two speed detection channels;

the processor of the measurement host is used for obtaining the angle parameter of the aircraft according to the pressure data of the five-hole probes received by the first to fifth differential pressure sensors, and obtaining the air flow speed of the environment where the aircraft is located according to the pressure data of the pitot tubes received by the sixth differential pressure sensor and the seventh differential pressure sensor.

6. The multi-channel probe measurement system of claim 4, wherein the measurement host further comprises: the temperature acquisition circuit, the power supply circuit, the communication circuit and the storage circuit are respectively connected to the processor; the shell is provided with a connecting socket, and the temperature acquisition circuit, the power supply circuit, the communication circuit and the storage circuit are connected with external equipment through the connecting socket;

the temperature acquisition circuit comprises a temperature sensor and a temperature acquisition chip, wherein the temperature sensor is connected with the temperature acquisition chip, the temperature acquisition chip is connected with the processor, and the temperature acquisition circuit is used for acquiring the current atmospheric temperature;

the communication circuit comprises a communication chip and a serial port communication module, the communication chip is connected with the processor and the serial port communication module, and the serial port communication module is used for connecting an upper computer and carrying out data transmission with the upper computer;

the storage circuit is used for storing data required by the processor in a data processing process, the storage circuit comprises a storage management chip, a storage card and a transmission interface, the transmission interface and the storage card are connected with the storage management chip, the storage management chip is connected with the processor, and the storage management chip is used for managing the data in the storage card and the data required by the processor in the data processing process.

7. The multi-channel probe measurement system of claim 3, wherein the housing comprises a housing having electromagnetic shielding and temperature control functions.