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

Abstract

This application provides a multi-channel probe measurement system and parameter measurement method applied to aircraft, which relates to the technical field of aircraft flow field detection. The system includes: a porous probe, a pitot tube and/or a measurement host, and the measurement host includes A plurality of detection channels, the plurality of detection channels include an angle detection channel and 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 The measurement host; the measurement host is used to obtain the operating parameters of the aircraft according to the data collected by the porous probe and the data collected by the pitot tube. Multiple measurement data at the same location can be collected, so that the amount of data collected can be increased, and the detection accuracy of the measurement host can be improved. Multiple measurement data at different locations can also be collected, and data at different locations can be measured at the same time, improving Measure the detection efficiency of the host.

Description

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

technical field

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

Background technique

The collection of flow field data of the aircraft is of great significance to the safe flight of the aircraft. In the prior art, most of the measurement of operating parameters such as angle information and incoming flow velocity of the aircraft are measured by porous probes.

However, in the actual application of the aircraft, the detection channels of the detection equipment used are limited, which leads to the limited amount of data collected, resulting in errors in the detection results. To obtain more data, it is necessary to set up multiple detection devices, which will increase The overall weight of the aircraft and increased power consumption. And in some wind tunnel test scenarios, the existing testing equipment will increase the test cost due to the limited testing data obtained.

In this case, it is necessary to propose a system capable of improving the detection result accuracy and detection efficiency of the flow field airflow of the aircraft.

Contents of the invention

In view of this, the purpose of this application is to propose a multi-channel probe measurement system and parameter measurement method applied to aircraft, which can specifically solve existing problems.

Based on the above purpose, in the first aspect, the present application proposes a multi-channel probe measurement system applied to an aircraft, the system includes: a porous probe, a pitot tube and a measurement host, and the measurement host includes a plurality of detection channels, The multiple detection channels include 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 a host computer; the measurement host computer is used to obtain 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 porous probe, and the number of multiple angle detection channels of the measurement host is obtained according to the number of the at least one porous probe and the number of holes in each of the porous probes; wherein , the porous probe is connected to the measurement host through a connection assembly, the connection assembly has a pressure guide tube corresponding to each angle detection channel, and each hole of the porous probe is connected to a pressure guide tube through a pressure guide tube. An angle detection channel is connected in one-to-one correspondence.

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 used to convert the collected Pressure data from the porous probe is digitally communicated to the processor.

Optionally, the porous probe is a five-hole probe, and 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; The five holes of the five-hole probe are respectively connected to the five angle detection channels; the pitot tube includes a total pressure hole and a static pressure hole, and the total pressure hole and the static pressure hole are respectively connected to the two speed detection channels. channel; the atmospheric pressure detection channel is provided with an absolute pressure sensor, and the absolute pressure sensor is used to read 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, and a sixth differential pressure sensor. pressure sensor, the seventh differential pressure sensor and the absolute pressure sensor, the first to fifth differential pressure sensors correspond to the five angle detection channels respectively, the sixth differential pressure sensor and the seventh differential pressure sensor The sensors are in one-to-one correspondence with the two speed detection channels; the processor of the measurement host is used to obtain the angle parameters of the aircraft according to the pressure data of the five-hole probe received by the first to fifth differential pressure sensors , and according to the pressure data of the Pitot tube received by the sixth differential pressure sensor and the seventh differential pressure sensor, the airflow velocity of the environment where the aircraft is located is obtained.

Optionally, the measurement host further includes: a temperature acquisition circuit, a power supply circuit, a communication circuit and a storage circuit, and the temperature acquisition circuit, a power supply circuit, a communication circuit and a storage circuit are respectively connected to the processor; the housing A connection socket is provided, and the temperature acquisition circuit, power supply circuit, communication circuit and storage circuit are connected to external devices through the connection socket; the temperature acquisition circuit includes a temperature sensor and a temperature acquisition chip, and the temperature sensor is connected to the temperature acquisition circuit. chip, the temperature acquisition chip is connected to the processor, and the temperature acquisition circuit is used to collect the current atmospheric temperature; the communication circuit includes a communication chip and a serial communication module, and the communication chip is connected to the processor and the serial communication module , the serial port communication module is used to connect to the host computer and perform data transmission with the host computer; the storage circuit is used to store the data required by the processor during data processing, and the storage circuit includes a storage management chip , a memory card and a transmission interface, the transmission interface and the memory card are connected to the storage management chip, the storage management chip is connected to the processor, and the storage management chip is used to process the data in the memory card and The processor manages the data required during data processing.

Optionally, the housing includes an outer shell with functions of electromagnetic shielding and temperature control.

In the second aspect, the present application proposes a parameter measurement method, which is applied to the multi-channel probe measurement system applied to aircraft according to any one of the first aspect, and the method includes: acquiring the multi-channel probe The pressure data collected by the needle and the pitot tube, and obtain the calibration coefficient of the aircraft, the calibration coefficient is obtained according to the pressure value and the calibration formula of the aircraft under the preset operating parameters; according to the calibration coefficient and the obtained Perform reverse interpolation calculation on the pressure data to obtain the operating parameters of the aircraft, the operating parameters include at least one of the aircraft's pitch angle, yaw angle, total pressure and dynamic pressure.

In general, the advantages of this application and the experience it brings to users lie in:

The application provides a multi-channel probe measurement system applied to aircraft, including a multi-hole probe, a pitot tube, and a measurement host. The measurement host includes multiple detection channels, and the multiple detection channels include angle detection channels and speed detection channels; the multi-hole probe Connect 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 to obtain the operating parameters of the aircraft according to the data collected by the porous probe and the data collected by the pitot tube . Multiple measurement data at the same location can be collected, so that the amount of data collected can be increased, and the detection accuracy of the measurement host can be improved. Multiple measurement data at different locations can also be collected, and data at different locations can be measured at the same time, improving Measure the detection efficiency of the host.

Description of drawings

In the drawings, unless otherwise specified, the same reference numerals designate the same or similar parts or elements throughout the several drawings. The drawings are not necessarily drawn to scale. It should be understood that these drawings only depict some embodiments disclosed according to the application, and should not be regarded as limiting the scope of the application.

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

Fig. 2 shows another system architecture diagram of the multi-channel probe measurement system applied to aircraft of the present application;

Fig. 3 shows a partial structural schematic 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 shows a schematic diagram of the hardware structure of a measurement host;

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

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

FIG. 8 shows a schematic diagram of the actual application of the multi-channel probe measurement system of this embodiment on an aircraft.

Detailed ways

The application will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain related inventions, not to limit the invention. It should also be noted that, for the convenience of description, only the parts related to the related invention are shown in the drawings.

It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and embodiments.

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

With reference to Fig. 1, the multi-channel probe measurement system applied to the aircraft provided by the present embodiment includes: a porous probe, a pitot tube 102 and a measurement host 103, the measurement host 103 includes a plurality of detection channels, and the plurality of detection channels includes an angle detection channel And\or 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. Wherein, the measurement host 103 is used to obtain the operating parameters 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 multiple detection channels in this embodiment include angle detection channels and/or speed detection channels, that is, the multiple detection channels in this embodiment may only include angle detection channels, so as to detect only the angle of the aircraft according to actual needs The data can also contain only the speed detection channel to detect only the airflow speed of the environment in which the aircraft is located according to actual needs, and can also include both angle detection channels and speed detection channels to detect the flight angle of the aircraft and the environment in which the aircraft is located according to actual needs air velocity. In this embodiment, for the convenience of description, the multiple detection channels include an angle detection channel and a speed detection channel in the following.

Specifically, the angle detection channel is used to receive the pressure data collected by the porous probe. After the pressure data is received by the sensor at the measuring host 103, the processor processes the pressure data to obtain the angle parameters of the aircraft. The angle parameters include pitch angle and yaw angle. The speed detection channel is used to receive the pressure data collected by the pitot tube 102. After the pressure data is received by the sensor at the measurement host 103, the processor processes the pressure data to obtain the airflow velocity of the environment where the aircraft is located.

The porous probe of the multi-channel probe measuring system of the present embodiment can comprise any one in three-hole probe, five-hole probe, seven-hole probe, or three-hole probe, five-hole probe, seven-hole probe Any two of the probes, or a combination of probes with different well numbers. Referring to Figure 1, the porous probes include porous probe 1, porous probe 2 and porous probe 3, a total of 3 porous probes, assuming that the 3 porous probes are three-hole probes, five-hole probes and seven-hole probes probe, the angle detection channels include 15 angle detection channels.

FIG. 2 shows another system architecture diagram of a multi-channel probe measurement system applied to an aircraft provided by this embodiment. Referring to FIG. 2 , the porous probe includes one porous probe. Assuming that the porous probe is a five-hole probe 101 , the angle detection channels include five angle detection channels.

In this embodiment, when multiple porous probes are connected to the measurement host 103, multiple measurement data at the same location can be collected, so that the amount of data collected is more, the detection accuracy of the measurement host 103 can be improved, and it is also possible to collect A plurality of measurement data in different positions can measure the data in different positions at the same time, so as to improve the detection efficiency of the measurement host 103 . That is, this embodiment can improve the accuracy and detection efficiency of the detection result of the flow field airflow of the aircraft by the measurement host 103 .

In this embodiment, the multi-channel probe measurement system includes at least one porous probe, that is, there can be one or more porous probes, and the number of multiple angle detection channels of the measurement host 103 is based on the number of at least one porous probe. and the number of holes for each multiwell probe.

In this embodiment, the number of multiple angle detection channels of the measurement host 103 is the sum of the number of holes of all porous probes, so that the pressure data collected by each hole of each porous probe can be transmitted to 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 a seven-hole probe and a three-hole probe, the measurement host 103 has ten angle detection channels. 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-mentioned calculations are angle detection channels, and the total number of channels of the measurement host 103 in this embodiment is the sum of the number of angle detection channels, speed detection channels and atmospheric pressure detection channels, wherein the atmospheric pressure detection channel setting There are absolute pressure sensors, which are used to read the current barometric pressure.

In this embodiment, in order to improve the applicability of the multi-channel probe measurement system, the porous 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 Measurement host 103 . Wherein, the connection assembly 202 has a pressure guide tube corresponding to each angle detection channel, and each hole of the multi-hole probe is connected to an angle detection channel in a one-to-one correspondence through a pressure guide tube, so that the pressure data of each hole can be independently transmitted to the sensors in the measurement host 103 .

In one example, the connection assembly 202 can be an integrated module (not shown) with multiple independent pressure guide tubes, for example, the pressure guide assembly is a piece with connectors at both ends, and the connectors are used to connect the multi-hole probe and The measuring host 103 and the connecting component 202 are integrated components with multiple hollow conduits passing through the above-mentioned connectors. On the one hand, the integration of the pressure guiding tube can be realized, and the durability of the pressure guiding tube can be increased. On the other hand, the pressure guiding tube can be reduced. volume of.

In one example, the connection assembly 202 can also be a connection assembly 202 composed of a plurality of independent pressure guiding tubes as shown in FIG. 1 or FIG. Measurement host 103 .

In another example, the connection component 202 can 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 set in the integrated connection component 202 , the signal transmission line connects the measurement host 103 to the device provided at the location of the porous probe, so as to improve the integration of the connection component 202 and reduce the overall volume of the multi-channel probe measurement system of this embodiment.

In this embodiment, the measuring component can use a rubber pressure guiding tube, so that the pressure guiding tube has better flexibility, avoiding the situation that the porous probe or pitot tube 102 and the measuring host 103 can only be in a fixed position due to rigid connection , increasing the optional placement of the porous probe and pitot tube 102 , and facilitating the installation and disassembly between the porous probe and pitot tube 102 and the measurement host 103 .

FIG. 3 shows a partial structural diagram of a measuring 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 used to convert the collected pressure data of the porous probe into The digital communication is transmitted to the processor 104 . For example, the sensor transmits the collected pressure data of the porous probe to the processor 104 via an Inter-Integrated Circuit (IIC) or a Serial Peripheral Interface (SPI) communication.

As shown in FIG. 3 , the sensors include sensor 1 , sensor 2 , sensor 3 , sensor 4 . . . sensor N, and the N sensors are all connected to the processor 104 .

It can be seen that the sensor of this embodiment is a digital sensor, adopts digital communication, and its data acquisition rate can reach up to 400Hz. Under this data update rate, 50 data sliding average 50Hz data output can be provided for the back-end algorithm. This enables the processor 104 to calculate the resulting data faster. At the same time, the sensor adopts digital communication instead of analog signal output, which is beneficial to reduce the interference of environmental factors on the air pressure data. The impact of measurement data makes the application scenarios and environments more adaptable, and can better meet the harsh environmental requirements of aircraft.

Fig. 4 shows a schematic structural diagram of an eight-channel probe measurement system. In this embodiment, when the porous 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; the five holes of the five-hole probe are respectively connected to five angle detection channels for measuring the angle parameters of the aircraft, and the angle parameters include the pitch angle and yaw angle of the aircraft. Pitot tube 102 includes a total pressure hole and a static pressure hole, the total pressure hole and the static pressure hole are respectively connected to two velocity detection channels for measuring the airflow velocity of the environment where the aircraft is located. The atmospheric pressure detection channel is provided with an absolute pressure sensor, which is used to read the current atmospheric pressure.

Among them, the five-hole probe is a multi-hole probe device that measures data according to the differential pressure method, and it is widely used in the test scene of the aerodynamic flow field, especially in the test of the aerospace flow field. The center of the probe front end of the five-hole probe and the symmetrical positions up, down, left, and right are respectively provided with pressure measuring holes. The five-hole probe can generate different pressures on the five pressure measuring holes through the airflow to determine the fluid characteristics, and calculate the total pressure of the flow field, Static pressure, velocity and direction of airflow.

The Pitot tube 102 is a tubular device that measures the total pressure and static pressure of the airflow to determine the airflow velocity. The pressure can be measured through the Pitot tube 102, and then the velocity of the airflow can be directly calculated by applying Bernoulli's theorem, which has good velocity measurement accuracy.

Considering that although the five-hole probe can measure the velocity component of the aircraft, due to its own structure and the complexity of calibration before use, this embodiment uses the pitot tube 102 to measure the airflow velocity of the environment where the aircraft is located. The five-hole probe is used for Measure the pitch angle and yaw angle of the aircraft, thereby reducing the complicated calibration and verification work when measuring the air velocity through the five-hole probe, reducing the measurement complexity, and greatly improving the measurement accuracy and measurement speed of the aircraft's operating parameters.

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 The fifth differential pressure sensor 1035, the sixth differential pressure sensor 1036, the seventh differential pressure sensor 1037 and the absolute pressure sensor 1038, the first to fifth differential pressure sensors correspond to the five angle detection channels respectively, and the sixth differential pressure sensor 1036 and the seventh differential pressure sensor 1037 correspond to the two speed detection channels respectively; the processor 104 of the measurement host 103 is used to obtain the pressure data of the five-hole probe 101 received by the first to fifth differential pressure sensors to obtain the aircraft's The angle parameter and the pressure data of the pitot tube 102 received by the sixth differential pressure sensor 1036 and the seventh differential pressure sensor 1037 are used to obtain the airflow velocity of the environment where the aircraft is located.

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

4, the first differential pressure sensor 1031, the second differential pressure sensor 1032, the third differential pressure sensor 1033, the fourth differential pressure sensor 1034, the fifth differential pressure sensor 1035, the sixth differential pressure sensor 1036, the seventh differential pressure sensor The sensor 1037 and the absolute pressure sensor 1038 are respectively connected to the processor 104 through independent transmission channels, and each channel has its unique corresponding communication address.

In this embodiment, the measurement host 103 also includes: a temperature acquisition circuit 105, a power supply circuit 106, a communication circuit 107 and a storage circuit 108, and 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 connecting socket 502 through which 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.

Wherein, the temperature acquisition circuit 105 includes a temperature sensor 1051 and a temperature acquisition chip 1052, the temperature sensor 1051 is connected to the temperature acquisition chip 1052, the temperature acquisition chip 1052 is connected to the processor 104, and the temperature acquisition circuit 105 is used to acquire the current atmospheric temperature . The processor 104 can obtain the current ambient temperature of the aircraft according to the temperature data collected by the temperature sensor 1051, and calculate the atmospheric density, and can calculate the current five-hole probe according to the preset calibration data of the pitot tube 102 and the Bernoulli equation. The velocity of the needle flow.

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 to connect with the host computer and perform data transmission with the host computer.

In one example, the communication chip 1071 and the serial communication module 1072 use the RS485 protocol for transmission, and can choose the request response mode or the direct sending mode, and developers can set the corresponding transmission mode according to actual application requirements.

In this embodiment, the storage circuit 108 is used to store the data required by the processor 104 during data processing, the storage circuit includes a storage management chip 1081, a memory card 1083 and a transmission interface 1082, the transmission interface 504 and the The memory card is connected to the storage management chip, and the storage management chip is connected to the processor 104. The storage management chip 1081 is used to manage the data in the memory card 1083 and the data required by the processor 104 during data processing. The transmission interface 504 may be a USB interface, which is used to connect to other devices of the aircraft, so as to write and export data of the storage management chip 1081 .

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

In this embodiment, the power supply circuit is used to supply power to the measurement host 103, and the power supply circuit includes a power supply voltage stabilizer. The working voltage range of the measuring host 103 in this embodiment is 4.5-45V.

In one example, the power regulator can use the LM2596 regulator. The LM2596 regulator uses a step-down power management monolithic integrated circuit, which can output a driving current of 3A, and has good linearity and load regulation characteristics, ensuring The output performance is stable, which can reduce the measurement error caused by the voltage instability to the sensor.

Fig. 5 shows a schematic diagram of the hardware structure of a measurement host 103. With reference to Fig. 5, the measurement host 103 has a housing 501, the above-mentioned processor 104, sensor, temperature acquisition circuit 105, power supply circuit 106, communication circuit 107 and storage circuit 108 set in the housing.

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

Wherein, the casing 501 is provided with a measurement interface 505 , and the measurement interface 505 is used to connect with the connection component 202 to realize the connection between the connection component 202 and the measurement host 103 . Wherein, the number of measurement interfaces 505 is consistent with the number of detection channels of the measurement body.

The casing 501 of this embodiment includes an outer shell with functions of electromagnetic shielding and temperature control. For example, the casing of the measurement host 103 in this embodiment is an all-metal aluminum alloy casing, which can realize an electromagnetic shielding function and effectively prevent electromagnetic interference.

For example, multiple cooling slots can be set on the shell, or opening and closing parts can be set on the cooling slot to realize the switching function of the cooling slot. When the temperature is higher than the preset value, the opening and closing parts can be opened to realize measurement through the cooling slot The air convection between the inside and outside of the host 103, when the temperature is lower than the preset value, the opening and closing parts are closed to reduce the air convection between the inside and outside of the measurement host 103. Alternatively, a temperature control material is provided on the inner wall of the casing to achieve the purpose of temperature control.

In addition, with reference to Fig. 5, the measurement host 103 of the present embodiment also includes a power supply switch 503, a work indicator light 109, the power supply switch is used to realize the power supply control of the measurement host 103, and the work indicator light 109 is used to display the working state of the measurement host 103, For example, when the measuring host 103 is in the working state, the working indicator light 109 is in the green light state, and when the measuring host 103 is in the standby state, the working indicator light 109 is in the red light state.

Based on the workflow of the processor 104, the workflow of the system of the multi-channel probe measurement system applied to the aircraft provided by this embodiment will be described below:

Processor 104 obtains the pitch angle and yaw angle of the aircraft according to the received pressure data collected by the first to fifth differential pressure sensors, and the processor 104 obtains the aircraft's pitch angle and yaw angle according to the received pressure data collected by the sixth differential pressure sensor and the seventh differential pressure sensor. The obtained pressure data obtains the airflow velocity of the environment where the aircraft is located, and the processor 104 obtains the atmospheric pressure of the environment and the altitude of the aircraft based on the received pressure data collected by the absolute pressure sensor, and the processor 104 can also obtain the airflow velocity collected by the temperature sensor. The resulting temperature data yields the current atmospheric temperature.

It can be seen that this embodiment can maximize the respective measurement accuracy advantages of the five-hole probe, pitot tube 102 and each sensor, realize the function of online processing of detection data and external output of aircraft flight parameters, and provide a comprehensive solution for meeting various aircraft requirements. possibility.

Above-mentioned Fig. 4 is the structure schematic diagram of the eight-channel probe measurement system of the present embodiment, and when the channel quantity of measuring main frame 103 changes, the structure diagram of multi-channel probe measurement system is as shown in Fig. 6, with reference to Fig. 6, multi-hole probe There are multiple needles, which may include porous probe A, porous probe B ... porous probe M, and the differential pressure sensor connected to the porous probe includes a first differential pressure sensor, a second differential pressure sensor, a third differential pressure sensor sensor, the fourth differential pressure sensor...the Nth differential pressure sensor, at this time, the measurement host 103 also includes a temperature acquisition circuit, a power supply circuit, a communication circuit, a storage circuit and a working indicator light.

A multi-channel probe measurement system applied to aircraft provided in this embodiment includes a porous probe, a pitot tube 102, and a measurement host 103. The measurement host 103 includes multiple detection channels, and the multiple detection channels include angle detection channels and speed detection. channel; the porous probe is connected to the measurement host 103 through the angle detection channel; the pitot tube 102 is connected to the measurement host 103 through the speed detection channel; the measurement host 103 is used for collecting data collected by the porous probe and the pitot tube 102 The obtained data are used to obtain the operating parameters of the aircraft. Multiple measurement data at the same location can be collected, so that the amount of collected data is larger, and the detection accuracy of the measurement host 103 can be improved. Multiple measurement data at different locations can also be collected, and data at different locations can be measured at the same time. The detection efficiency of the measurement host 103 is improved.

This embodiment also provides a parameter measurement method, referring to Fig. 7, the measurement method is applied to the multi-channel probe measurement system applied to the aircraft provided by this embodiment, such as the system shown in Fig. 4 or Fig. 6, the method includes The following steps S701-S702:

S701. Obtain the pressure data collected by the porous probe and the pitot tube 102, and obtain the calibration coefficient of the aircraft.

The pressure data collected by the porous probe and pitot tube 102 in this embodiment is the data collected by the sensor connected to the measurement host 103 and the porous probe and pitot tube 102 .

In this embodiment, the calibration coefficient of the aircraft is obtained according to the pressure value of the aircraft under preset operating parameters and the calibration formula. Among them, the preset operating parameters are parameters obtained through experiments in wind tunnels, such as blowing tests in standard wind tunnels to obtain corresponding experimental data, and to obtain the pressure values of different pressure-sensing holes of the probe at a specific flow rate As well as the size of the deflection angle and the pitch angle, and bring them into the calibration formula to obtain the calibration coefficient.

S702. Perform reverse interpolation calculation according to the calibration coefficient and the pressure data to obtain the operating parameters of the aircraft.

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 multi-hole probe connected to the measuring 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 can be:

Pitch coefficient = (pressure value of the lower hole - pressure value of the upper hole) / (pressure value of the middle hole - average pressure of the surrounding 4 holes)

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

Total pressure coefficient = (total pressure value - middle pore pressure value) / (medium pore pressure value - average pressure value of surrounding 4 holes)

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

Among them, the pressure values of the upper hole, the lower hole, the middle hole, the left hole and the right hole are the pressure values of each hole of the five-hole probe obtained from the experiment in the wind tunnel. The total pressure value and the static pressure value are the pressure values received by the two holes of the Pitot tube 102 .

After calibration, the pitch angle, yaw angle, total pressure coefficient and dynamic pressure coefficient corresponding to each set of pitch coefficients and yaw coefficients can be obtained. Then, when the calibrated porous probe is applied to the flight scene of the aircraft, the data collected by the sensor connected to the measurement host 103, the porous probe and the Pitot tube 102, that is, the actual measured value of the aircraft, is carried out through the actual measured value. By reverse interpolation calculation, the pitch angle, yaw angle, total pressure value and dynamic pressure value of the current aircraft can be obtained. It has a good detection effect, and the measurement system of this embodiment has multiple channels, can obtain multiple measurement values, and can reduce measurement errors.

Fig. 8 shows the actual application of the multi-channel probe measurement system of this embodiment on an aircraft, wherein, the multi-channel probe measurement system of this embodiment is arranged inside the aircraft 800, and the length of the pressure guiding tube can be increased to To realize the measurement of the target position, the target position can be the nose and two wings of the aircraft. For example, as shown in Figure 8, the multi-channel probe measurement system includes 3 porous probes, and the three porous probes are respectively arranged on the nose, Left and right wings, so as to obtain the pressure data of the nose, left and right wings, and then monitor the operating parameters of the aircraft to ensure the smooth operation of the aircraft.

In this embodiment, the processor 104 may also be an integrated circuit chip, which has a signal processing capability. In the implementation process, each step of the above method can be completed by an integrated logic circuit of hardware in a processor or an instruction in the form of software. Above-mentioned processor 104 can be general-purpose processor, comprises central processing unit (Central Processing Unit, be called for short CPU), network processor (Network Processor, be called for short NP) etc.; Can also be digital signal processor (DSP), application-specific integrated circuit (ASIC), off-the-shelf programmable gate array (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components. Various methods, steps, and logic block diagrams disclosed in the embodiments of the present application may be implemented or executed. 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 module can be located in a mature storage medium in the field such as random access memory, flash memory, read-only memory, programmable read-only memory or electrically erasable programmable memory, register. The storage medium is located in the memory, and the processor reads the information in the memory, and combines with its hardware to complete the processing of the pressure data collected by the sensor.

It should be noted:

The algorithms and displays presented herein are not inherently related to any particular computer, virtual system, or other device. Various generic systems can also be used with the teachings based on this. The structure required to construct such a system is apparent from the above description. Furthermore, this application is not directed to any particular programming language. It should be understood that various programming languages can be used to implement the content of the application described here, and the description of specific languages above is to disclose the best implementation mode of the application.

In the description provided herein, numerous specific details are set forth. However, it is understood that the 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 the understanding of this description.

Similarly, it should be understood that in the above description of exemplary embodiments of the application, in order to streamline the application and to facilitate understanding of one or more of the various inventive aspects, various features of the application are sometimes grouped together in a single embodiment, figure, or its description. This method of disclosure, however, is not to be interpreted as reflecting an intention that the claimed application 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 this 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 can understand that the modules in the device in the embodiment can be adaptively changed and arranged in one or more devices different from the embodiment. Modules or units or components in the embodiments may be combined into one module or unit or component, and furthermore may be divided into a plurality of sub-modules or sub-units or sub-assemblies. All features disclosed in this specification (including accompanying claims, abstract and drawings) and any method or method so disclosed may be used in any combination, except that at least some of such features and/or processes or units are mutually exclusive. All processes or units of equipment are combined. Each feature disclosed in this specification (including accompanying claims, abstract and drawings) may be replaced by alternative features serving the same, equivalent or similar purpose, unless expressly stated otherwise.

In addition, those skilled in the art will understand that although some embodiments described herein include some features included in other embodiments but not others, combinations of features from different embodiments are meant to be within the scope of the present 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 realized in hardware, or in software modules running on one or more processors, or in a combination thereof. Those skilled in the art should understand that a microprocessor or a digital signal processor (DSP) may be used in practice to implement some or all functions of some or all components in the virtual machine creation system according to the embodiment of the present application. The present application can also be implemented as an apparatus or system program (eg, computer program and computer program product) for performing a part or all of the methods described herein. Such a program 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 site, or 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 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 can be implemented by means of hardware comprising several distinct elements, and by means of a suitably programmed computer. In a unit claim enumerating several systems, several of these systems can be embodied by one and the same item of hardware. The use of the words first, second, and third, etc. does not indicate any order. These words can be interpreted as names.

The above is only a specific embodiment of the application, but the scope of protection of the application is not limited thereto. Any person familiar with the technical field can easily think of its various changes or modifications within the technical scope disclosed in the application. Replacement, these should be covered within the protection scope of this application. Therefore, the protection scope of the present application should be determined by 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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