CN115683042A - Multi-channel probe measurement system and parameter measurement method applied to aircraft - Google Patents

Abstract

The application provides a multichannel probe measurement system and parameter measurement method for aircraft relates to aircraft flow field and detects technical field, the system includes: the device comprises a porous probe, a pitot tube and/or a measuring host, wherein the measuring host comprises a plurality of detection channels, and the detection channels comprise an angle detection channel and a speed detection channel; the multi-hole 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; the measurement host is used for obtaining the operating parameters of the aircraft according to the data collected by the porous probe and the data collected by the pitot tube. A plurality of measured data of same position can be gathered for the data bulk of gathering is more, improves the detection precision of measuring the host computer, also can gather a plurality of measured data of different positions, can measure the data of different positions simultaneously, improves the detection efficiency of measuring the host computer.

Description

Multi-channel probe measurement system and parameter measurement method applied to aircraft

Technical Field

The application relates to the technical field of aircraft flow field detection, in particular to an eight-channel probe measurement system and a parameter measurement method applied to an aircraft.

Background

The collection of the flow field data of the aircraft has important significance for the safe flight of the aircraft. In the prior art, a porous probe is mostly used for measuring the angle information, the incoming flow speed and other operation parameters of the aircraft.

However, in practical application of the aircraft, the detection channels of the adopted detection devices are limited, so that the data volume acquired by the detection devices is limited, and the detection result has errors. In some wind tunnel test scenes, the existing detection equipment can increase the test cost due to limited acquired detection data.

In this situation, it is necessary to provide a system capable of improving the accuracy and efficiency of the detection result of the air flow in the flow field of the aircraft.

Disclosure of Invention

In view of the above, an object of the present invention is to provide a multi-channel probe measurement system and a parameter measurement method applied to an aircraft, which can specifically solve the existing problems.

In view of the above, in a first aspect, the present application provides 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 angle detection channels and/or speed detection channels; the multi-hole 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; the measurement host is used for obtaining the operating parameters of the aircraft according to the data collected by the porous probe and the data collected by the pitot tube.

Optionally, the system includes 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 in one-to-one correspondence with the angle detection channels, and each hole of the multi-hole probe is in one-to-one correspondence with one angle detection channel through one pressure guide pipe.

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

Optionally, the multi-hole probe is a five-hole probe, and the measurement host has eight measurement channels, where 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 which is used for reading the current atmospheric pressure.

Optionally, the sensors of the measurement host corresponding to each detection channel include 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 respectively correspond to the five angle detection channels one to one, and the sixth differential pressure sensor and the seventh differential pressure sensor respectively correspond to the two speed detection channels one to one; and 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 probe received by the first differential pressure sensor, the fifth differential pressure sensor and the fifth differential pressure sensor, and obtaining the airflow speed of the environment where the aircraft is located according to the pressure data of the pitot tube 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 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, 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 communication module, the communication chip is connected with the processor and the serial communication module, and the serial 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, and comprises a storage management chip, a storage card and a transmission interface, wherein 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 comprises a casing having electromagnetic shielding and temperature control functions.

In a second aspect, the present application provides a parameter measurement method applied to the multi-channel probe measurement system applied to the aircraft of any one of the first aspect, the method including: acquiring pressure data acquired by the porous probe and the pitot tube, and acquiring a calibration coefficient of the aircraft, wherein the calibration coefficient is obtained according to a pressure value and a calibration formula of the aircraft under preset operating parameters; and performing reverse interpolation calculation according to the calibration coefficient and the pressure data to obtain operation parameters of the aircraft, wherein the operation parameters comprise at least one of a pitch angle, a yaw angle, total pressure and dynamic pressure of the aircraft.

Generally, the advantages of the present application and the experience brought to the user are:

the application provides a multi-channel probe measuring system applied to an aircraft, which comprises a multi-hole probe, a pitot tube and a measuring host, wherein the measuring host comprises a plurality of detecting channels, and the plurality of detecting channels comprise an angle detecting channel and a speed detecting channel; the multi-hole probe is connected to the measurement host through the angle detection channel; the pitot tube is connected to a measurement host through the speed detection channel; and the measurement host is used for obtaining the operating parameters of the aircraft according to the data acquired by the porous probe and the data acquired by the pitot tube. A plurality of measured data of same position can be gathered for the data bulk of gathering is more, improves the detection precision of measuring the host computer, also can gather a plurality of measured data of different positions, can measure the data of different positions simultaneously, improves the detection efficiency of measuring the host computer.

Drawings

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

FIG. 1 shows a system architecture diagram of the multi-channel probe measurement system of the present application as applied to an aircraft;

FIG. 2 illustrates another system architecture diagram of the multi-channel probe measurement system of the present application as applied to an aircraft;

fig. 3 shows a schematic partial structural diagram of a measurement host according to an embodiment of the present application;

FIG. 4 shows a schematic structural diagram of an eight channel probe measurement system according to an embodiment of the present application;

FIG. 5 is a schematic diagram of a hardware configuration of a measurement host;

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

FIG. 7 is a flow chart illustrating steps of a parameter measurement method according to an embodiment of the present application;

fig. 8 shows a practical application diagram of the multi-channel probe measurement system of the embodiment in an aircraft.

Detailed Description

The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and not restrictive of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.

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

Fig. 1 shows a system architecture diagram of the multi-channel probe measurement system of the present application as applied to an aircraft.

Referring to fig. 1, the multi-channel probe measurement system applied to an aircraft provided in the present embodiment includes: the multi-hole probe comprises a multi-hole probe, a pitot tube 102 and a measurement host machine 103, wherein the measurement host machine 103 comprises a plurality of detection channels, the plurality of detection channels comprise an angle detection channel and/or a speed detection channel, the multi-hole probe is connected to the measurement host machine 103 through the angle detection channel, and the pitot tube 102 is connected to the measurement host machine 103 through the speed detection channel. The measurement host machine 103 is used for obtaining the operating parameters of the aircraft according to the data collected by the multi-hole probe and the data collected by the pitot tube 102.

It should be noted that the plurality of detection channels of this embodiment include an angle detection channel and/or a speed detection channel, that is, the plurality of detection channels of this embodiment may include only the angle detection channel to detect only angle data of the aircraft according to actual needs, may also include only the speed detection channel to detect only airflow speed of the environment where the aircraft is located according to actual needs, and may also include both the angle detection channel and the speed detection channel to detect the flight angle of the aircraft and the airflow speed of the environment where the aircraft is located according to actual needs. For convenience of description, the following description will refer 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 multi-hole probe, and after the pressure data is received by a sensor at the measuring host machine 103, the processor processes the pressure data 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 collected by the pitot tube 102, and after the pressure data is received by a sensor at the measuring host machine 103, the processor processes the pressure data to obtain the airflow speed of the environment where the aircraft is located.

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

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 assuming that the multi-well probe is a five-well probe 101, the angle detection channel includes 5 angle detection channels.

In this embodiment, when a plurality of porous probes are connected to the measurement host machine 103, a plurality of measurement data at the same position can be collected, so that the collected data amount is more, the detection accuracy of the measurement host machine 103 is improved, a plurality of measurement data at different positions can also be collected, the data at different positions can be measured simultaneously, and the detection efficiency of the measurement host machine 103 is improved. That is, the present embodiment can improve the accuracy and 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-well probe, i.e. the multi-well probe may be one or multiple, and the number of the multiple angle detection channels of the measurement host 103 is obtained according to the number of the at least one multi-well probe and the number of wells of each multi-well probe.

In this embodiment, the number of the plurality of angle detection channels of the measurement host 103 is the sum of the number of the holes 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 a 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 performed by using the angle detection channels, and the total number of channels 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-hole probe is connected to the measurement host 103 through the connection component 202, and the connection component 202 is used for transmitting the pressure data collected by each hole of the multi-hole probe to the measurement host 103. The connection component 202 has a pressure pipe corresponding to each angle detection channel, and each hole of the multi-hole probe is connected to an angle detection channel through a pressure pipe, so that the pressure data of each hole can be independently transmitted to the sensor in the measurement host 103.

In one example, the connection component 202 may be an integrated module (not shown) having a plurality of independent pressure pipes, for example, the pressure pipe component is an integrated component having connectors at two ends for connecting the multi-hole probe and the measurement host 103, and the middle of the connection component 202 has a plurality of hollow conduits penetrating through the connectors, so that on one hand, the integration of the pressure pipes can be realized, the durability of the pressure pipes can be increased, and on the other hand, the volume of the pressure pipes can be reduced.

In an example, the connection assembly 202 may also be a connection assembly 202 composed of a plurality of independent pressure guiding pipes as shown in fig. 1 or fig. 2, and the two ends of the plurality of independent pressure guiding pipes are respectively connected with the porous probe and the measurement host 103.

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

In this embodiment, the measurement component may adopt a rubber pressure pipe, so that the pressure pipe has better flexibility, the situation that the porous probe or the pitot tube 102 and the measurement host 103 can only be in a fixed position due to rigid connection is avoided, the position placement selectivity of the porous probe and the pitot tube 102 is 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 schematic diagram of a partial structure 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, the sensor is connected to the processor 104, and the sensor is configured to transmit the acquired pressure data of the multi-well probe to the processor 104 in a digital communication manner. For example, the sensor may transmit the acquired pressure data of the multi-well probe to the processor 104 in a digital communication manner through an Inter-Integrated Circuit (IIC) or Serial Peripheral Interface (SPI) communication manner.

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

Therefore, the sensor of the embodiment is a digital sensor, and adopts a digital communication mode, the data acquisition rate can reach 400Hz at most, and under the data update rate, 50Hz data output with a moving average of 50 data can be provided for a back-end algorithm, so that the processor 104 can calculate the result data more quickly. 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 interference resistance, small size and low power consumption, can reduce the influence of the precision drift of the analog-digital sampling of the sensor circuit on the measured data, and has stronger application scene and environmental adaptability, thereby better meeting the harsh environmental requirements of the 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, 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 five angle detection channels and used for measuring angle parameters of the aircraft, and the angle parameters comprise a pitch angle and a yaw angle of the aircraft. The pitot tube 102 includes a total pressure port and a static pressure port, which are respectively connected to the two speed detection channels for measuring the air flow velocity of the environment in which the aircraft is located. The atmospheric pressure detection channel is provided with an absolute pressure sensor which is used for reading the current atmospheric pressure.

The five-hole probe is a multi-hole probe device for measuring data according to a pressure difference method, and is widely applied to test scenes of aerodynamic flow fields, particularly aerospace flow field tests. Pressure measuring holes are respectively arranged at the center, the upper part and the lower part and the left and right symmetrical positions of the front end of the probe of the five-hole probe, the five-hole probe can generate different pressures on the five pressure measuring holes through airflow to determine the fluid characteristics, and the total pressure and the static pressure of a flow field and the flow rate and the flow direction of the airflow are calculated.

The pitot tube 102 is a tubular device for measuring the total pressure and the static pressure of the airflow to determine the speed of the airflow, the pressure can be measured by the pitot tube 102, and the speed of the airflow can be directly calculated by applying Bernoulli's theorem, so that the accuracy of speed measurement is good.

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

Specifically, as shown in fig. 4, the sensors corresponding to each detection channel of the measurement master 103 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 correspond to five angle detection channels one to one, and the sixth differential pressure sensor 1036 and the seventh differential pressure sensor 1037 respectively correspond to two speed detection channels one to 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 an airflow speed of an 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 fast start and flexible program setting. The processor 104 is used for processing the data collected by the first to 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 each connected to the processor 104 via a respective independent transmission channel, each channel 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 respectively connected to the processor 104. 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 an external device, such as a power supply, through the connection socket 502.

The temperature acquisition circuit 105 comprises a temperature sensor 1051 and a temperature acquisition chip 1052, wherein 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 may obtain the ambient temperature of the current aircraft according to the temperature data acquired by the temperature sensor 1051, calculate the atmospheric density, and calculate the incoming flow velocity of the current 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 transmission, and may select a request response mode or a direct transmission mode, and developers 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, and 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 data in the memory card 1083 and data required by the processor 104 during data processing. Transport interface 504 may be a USB interface for connecting to other devices of the aircraft to enable writing and exporting of data by memory management chip 1081.

For example, when the processor 104 calculates the pressure value according to the pressure data, calibration values and verification coefficients 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 the present embodiment may be a TF card.

In this embodiment, the power supply circuit is configured to supply power to the measurement host 103, and the power supply circuit includes a power regulator, where one end of the power regulator is connected to the measurement host 103, and the other end of the power regulator is connected to the 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 to 45V.

In one example, the power regulator may be an LM2596 regulator, and the LM2596 regulator may be a buck power management monolithic integrated circuit, and may output a 3A driving current, and have good linearity and load regulation characteristics, so as to ensure stable output performance, and reduce a measurement error caused by unstable voltage to the sensor.

Fig. 5 shows a hardware structure diagram of a measurement host 103, and 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 the present embodiment are all electrically connected to the connection socket 502.

The housing 501 is provided with a measurement interface 505, and the measurement interface 505 is used for connecting with the connection assembly 202 and is used for connecting the connection assembly 202 with the measurement host 103. Wherein the number of the measurement interfaces 505 is the same as the number of the 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 achieve the electromagnetic shielding function and effectively prevent electromagnetic interference.

For example, a plurality of heat dissipation grooves may be formed in the housing, or opening and closing members may be disposed on the heat dissipation grooves to realize an opening and closing function of the heat dissipation grooves, when the temperature is higher than a preset value, the opening and closing members are opened to realize air convection between the inside and the outside of the measurement host 103 through the heat dissipation grooves, and when the temperature is lower than the preset value, the opening and closing members are closed to reduce air convection between the inside and the outside of the measurement host 103. Or, the inner wall of the shell is provided with a temperature control material to achieve the purpose of temperature control.

In addition, referring to fig. 5, the measurement host 103 of this 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 the 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 workflow of the system of the multi-channel probe measurement system applied to an aircraft provided in the present embodiment is explained below based on the workflow of the processor 104:

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

Therefore, the advantages of the measurement accuracy of the five-hole probe, the pitot tube 102 and each sensor 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 of this 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 as shown in fig. 6, referring to fig. 6, a plurality of porous probes are provided, and may include a porous probe a and a porous probe b.

The multi-channel probe measuring system applied to the aircraft comprises a multi-hole probe, a pitot tube 102 and a measuring host machine 103, wherein the measuring host machine 103 comprises a plurality of detection channels, and the plurality of detection channels comprise an angle detection channel and a speed detection channel; the multi-hole probe is connected to the measurement host machine 103 through an angle detection channel; the pitot tube 102 is connected to a measurement host machine 103 through the speed detection channel; the measurement host machine 103 is used for obtaining the operation parameters of the aircraft according to the data collected by the multi-hole probe and the data collected by the pitot tube 102. A plurality of measurement data of same position can be gathered for the data bulk of gathering is more, improves the detection precision of measuring host computer 103, also can gather a plurality of measurement data of different positions, can measure the data of different positions simultaneously, improves the detection efficiency of measuring host computer 103.

The present embodiment further provides a parameter measurement method, referring to fig. 7, which is applied to the multi-channel probe measurement system applied to the aircraft provided in the present embodiment, such as the system shown in fig. 4 or fig. 6, and the method includes the following steps S701-S702:

s701, acquiring pressure data acquired by the porous probe and the pitot tube 102, and acquiring a calibration coefficient of the aircraft.

In this embodiment, the pressure data collected by the multi-hole probe and the pitot tube 102 is the data collected by the sensor connected to the multi-hole probe and the pitot tube 102 and the measurement host 103.

In this embodiment, the calibration coefficient of the aircraft is obtained according to the pressure value of the aircraft under the preset operating parameter and a calibration formula. The preset operation parameters are parameters obtained through experiments in a wind tunnel, for example, a blowing test is performed in a standard wind tunnel, corresponding experiment data are obtained, pressure values of different pressure sensing holes of the probe at a specific flow speed and the sizes of a deflection angle and a pitch angle are obtained, and the pressure values, the deflection angle and the pitch angle are brought into a calibration formula to obtain a calibration coefficient.

And S702, 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 operating parameter includes at least one of a pitch angle, a yaw angle, a total pressure, and a dynamic pressure of the aircraft.

Taking the multi-hole probe connected to the measurement host 103 as an example, the five-hole probe includes an upper hole, a lower hole, a middle hole, a left hole and a right hole, and the calibration formula may be:

pitch coefficient = (lower hole pressure value-upper hole pressure value)/(middle hole pressure value-average of surrounding 4 hole pressures)

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

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

Dynamic pressure coefficient = (total pressure-static pressure)/(middle hole pressure-average surrounding 4 holes pressure)

The pressure values of the upper hole, the lower hole, the middle hole, the left hole and the right hole are pressure values of all holes of the five-hole probe obtained through experiments in the wind tunnel. The total and static pressure values are the pressure values experienced by the two orifices of the pitot tube 102.

After calibration, a pitch angle, a yaw angle, a total pressure coefficient and a dynamic pressure coefficient corresponding to each group of pitch coefficient and yaw coefficient can be obtained. When the calibrated porous probe is applied to a flight scene of an aircraft, the pitch angle, the yaw angle, the total pressure value and the dynamic pressure value of the current aircraft can be obtained by acquiring data acquired by a sensor connected with the measurement host 103, the porous probe and the pitot tube 102, namely an actual measurement value of the aircraft, and performing reverse interpolation calculation on the actual measurement value. The method has good detection effect, and the measuring system of the embodiment has multiple channels, can obtain multiple measured values, and can reduce measurement errors.

Fig. 8 shows a practical application of the multi-channel probe measurement system of this embodiment in an aircraft, wherein the multi-channel probe measurement system of this embodiment is disposed inside an aircraft 800, and a target position can be measured by increasing the length of a pressure guiding pipe, and the target position can be a nose and two wings of the aircraft, for example, as shown in fig. 8, the multi-channel probe measurement system includes 3 multi-hole probes, and the three multi-hole probes are respectively disposed on the nose, the left wing and the right wing of the aircraft, so as to obtain pressure data of the nose, the left wing and the right wing, and further monitor an operation parameter of the aircraft, and ensure smooth operation of the aircraft.

The processor 104 in this embodiment may also be an integrated circuit chip having signal processing capabilities. In implementation, the steps of the above method may be performed by integrated logic circuits of hardware in a processor or instructions in the form of software. The Processor 104 may be a general-purpose Processor, and includes a Central Processing Unit (CPU), a Network Processor (NP), and the like; but may also be a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), an off-the-shelf programmable gate array (FPGA) or other programmable logic device, discrete gate or transistor logic, discrete hardware components. The various methods, steps, and logic blocks disclosed in the embodiments of the present application 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 application may be directly implemented by a hardware decoding processor, or implemented by a combination of hardware and software modules in the decoding processor. The software modules may be located in ram, flash, rom, prom, or eprom, registers, etc. as is well known in the art. The storage medium is positioned in the memory, and the processor reads the information in the memory and completes the processing of the pressure data collected by the sensor 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 machine, or other apparatus. Various general purpose systems may also be used with the teachings herein. The required structure for constructing such a system will be apparent from the description above. Moreover, this application is not intended to refer to any particular programming language. It will be appreciated that a variety of programming languages may be used to implement the teachings of the present application as described herein, and any descriptions of specific languages are provided above to disclose the best modes of the present application.

In the description provided herein, numerous specific details are set forth. However, it is understood that embodiments of the application 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 foregoing description of exemplary embodiments of the application, various features of the application are sometimes grouped together in a single embodiment, figure, or description thereof for the purpose of streamlining the application and aiding in the understanding of one or more of the various inventive aspects. However, the disclosed method should not be construed to reflect the intent: this application is intended to cover such departures from the present disclosure as come within known or customary practice in the art to which this invention pertains. 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 application.

Those skilled in the art will appreciate that the modules in the devices in an embodiment may be adaptively changed and arranged in one or more devices different from the embodiment. 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. All of the features disclosed in this specification (including any accompanying claims, abstract and drawings), and all of the processes or elements of any method or apparatus so disclosed, may be combined in any combination, except combinations where at least some of such features and/or processes or elements 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 included in other embodiments, rather than other features, combinations of features of different embodiments are meant to be within the scope of the application and form different embodiments. For example, in the following claims, any of the claimed embodiments may be used in any combination.

The various component embodiments of the present application 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 a microprocessor or Digital Signal Processor (DSP) may be used in practice to implement some or all of the functions of some or all of the components in a virtual machine creation system according to embodiments of the present application. The present application may also be embodied as apparatus or system programs (e.g., computer programs and computer program products) for performing a portion or all of the methods described herein. Such programs implementing the present application may be stored on a computer readable medium or may be in the form of one or more signals. Such a signal may be downloaded from an internet website or provided on a carrier signal or in any other form.

It should be noted that the above-mentioned embodiments illustrate rather than limit the application, 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 application 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 systems, several of these systems may be embodied by one and the same item of hardware. The usage of the words first, second and third, etcetera do not indicate any ordering. These words may be interpreted as names.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any person skilled in the art can easily think of various changes or substitutions within the technical scope of the present application, and these should be covered by the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (8)

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 angle detection channels and/or speed detection channels;

the multi-hole 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 operating 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 in one-to-one correspondence with the angle detection channels, and each hole of the multi-hole probe is in one-to-one correspondence with one angle detection channel through one pressure guide pipe.

3. The multi-channel probe measurement system of claim 2, wherein the measurement host comprises a housing, a processor disposed within the housing, and a sensor corresponding to each detection channel, the sensor being connected to the processor, the sensor being configured to transmit the acquired pressure data of the multi-well probe to the processor in digital communication.

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 velocity 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 which is used for reading the current atmospheric pressure.

5. The multi-channel probe measurement system of claim 4, wherein the sensors of the measurement master corresponding to each detection channel include 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;

and 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 probe received by the first differential pressure sensor, the fifth differential pressure sensor and the fifth differential pressure sensor, and obtaining the airflow speed of the environment where the aircraft is located according to the pressure data of the pitot tube received by the sixth differential pressure sensor and the seventh differential pressure sensor.

6. The multi-channel probe measurement system according to claim 1 or 4, wherein the measurement host further comprises: the temperature acquisition circuit, the power 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, 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 communication module, the communication chip is connected with the processor and the serial communication module, and the serial 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, and comprises a storage management chip, a storage card and a transmission interface, wherein 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.

8. A parameter measurement method applied to the multichannel probe measurement system applied to the aircraft according to any one of claims 1 to 7, the method comprising:

acquiring pressure data acquired by the porous probe and the pitot tube, and acquiring a calibration coefficient of the aircraft, wherein the calibration coefficient is obtained according to a pressure value and a calibration formula of the aircraft under preset operating parameters;

and performing reverse interpolation calculation according to the calibration coefficient and the pressure data to obtain operation parameters of the aircraft, wherein the operation parameters comprise at least one of a pitch angle, a yaw angle, total pressure and dynamic pressure of the aircraft.

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