Atmosphere data measurement system and method

Abstract

The invention discloses an atmosphere data measuring system and method. The system comprises a five-hole probe type airspeed tube, five-hole measuring points of the five-hole probe type airspeed tube are distributed in a cross shape, and a plurality of through measuring points are arranged on the side face of the five-hole probe type airspeed tube; the three-way differential pressure sensor is used for measuring a first pressure difference between an upper measuring point and a lower measuring point of the five-hole measuring point; measuring a second pressure difference between the left measuring point and the right measuring point of the five-hole measuring point; measuring a third pressure difference between the middle measuring point and the through measuring point of the five-hole measuring point; the one-way absolute pressure sensor is used for measuring the absolute pressure of the middle measuring point of the five-hole measuring points; the atmospheric temperature measuring module is used for measuring the atmospheric temperature; and the controller is used for resolving atmosphere data by adopting a data fusion algorithm based on the first pressure difference, the second pressure difference, the third pressure difference, the absolute pressure and the atmosphere temperature. According to the high-altitude low-speed atmosphere data calculation method, atmosphere data calculation with the air speed lower than 4 m / s and the height of 300,000 m can be achieved, and the measurement precision of the atmosphere data in the high-altitude low-speed environment is improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of atmospheric data measurement, and more specifically, relates to an atmospheric data measurement system and method. Background Art

[0002] The atmospheric data system is responsible for providing key atmospheric parameters required during flight, including but not limited to indicated airspeed, true airspeed, flight speed, pressure altitude, Mach number, total atmospheric temperature, atmospheric static temperature, etc. These parameters are the basis for the normal operation of the UAV flight control system, engine control system, navigation system and instrument display system, and are of great significance for ensuring flight safety and improving flight efficiency.

[0003] High-altitude, low-speed UAVs are characterized by light weight, slow speed, and relatively weak wind resistance. These characteristics make UAVs susceptible to external factors such as wind speed during flight, resulting in a large difference between ground speed and air speed. Therefore, for high-altitude, low-speed UAVs, real-time and accurate measurement of atmospheric data parameters is particularly important.

[0004] Traditional atmospheric data computers have problems such as insufficient measurement range and poor measurement accuracy when measuring atmospheric data in high-altitude and low-speed environments.

[0005] The information disclosed in the background technology section of the present invention is only intended to deepen the understanding of the general background technology of the present invention, and should not be regarded as acknowledging or suggesting in any form that the information constitutes the prior art already known to those skilled in the art. Summary of the invention

[0006] The purpose of the present invention is to propose an atmospheric data measurement system and method, so as to solve the problems of insufficient measurement range and poor measurement accuracy of conventional atmospheric data computers for measuring atmospheric data in high-altitude and low-speed environments, and to improve the measurement accuracy of atmospheric data in high-altitude and low-speed environments.

[0007] To achieve the above object, the present invention proposes an atmospheric data measurement system and method.

[0008] According to a first aspect of the present invention, an atmospheric data measurement system is provided, comprising:

[0009] A five-hole probe pitot tube, wherein the five-hole measuring points of the five-hole probe pitot tube are distributed in a cross shape, and a plurality of through measuring points are arranged on the side of the five-hole probe pitot tube;

[0010] A three-way differential pressure sensor is used to measure the first pressure difference between the upper measuring point and the lower measuring point of the five-hole measuring point; to measure the second pressure difference between the left measuring point and the right measuring point of the five-hole measuring point; and to measure the third pressure difference between the middle measuring point of the five-hole measuring point and the through measuring point;

[0011] An absolute pressure sensor is used to measure the absolute pressure of the middle measuring point of the five hole measuring points;

[0012] Atmospheric temperature measurement module, used to measure atmospheric temperature;

[0013] a controller, electrically connected to the three differential pressure sensors, the one absolute pressure sensor and the atmospheric temperature measurement module, and configured to calculate atmospheric data using a data fusion algorithm based on the first pressure difference, the second pressure difference, the third pressure difference, the absolute pressure and the atmospheric temperature;

[0014] A secondary power supply is used to provide power to the air data measurement system.

[0015] Optionally, the atmospheric data includes:

[0016] Angle of attack, sideslip angle, atmospheric altitude, airspeed and static atmospheric temperature.

[0017] Optionally, the angle of attack is calculated based on the first pressure difference, the sideslip angle is calculated based on the second pressure difference, the airspeed is calculated based on the third pressure difference, the atmospheric altitude is calculated based on the absolute pressure, and the atmospheric static temperature is calculated based on the atmospheric temperature.

[0018] Optionally, the atmospheric temperature measurement module includes:

[0019] Atmospheric temperature sensor, used to measure atmospheric temperature;

[0020] The temperature acquisition circuit is composed of a ΣΔ modulator and a digital filter, and is electrically connected to the atmospheric temperature sensor to acquire the analog signal of the atmospheric static temperature of the atmospheric temperature sensor, and convert the analog signal into a digital signal and send it to the controller.

[0021] Optionally, it also includes:

[0022] A temperature sensor, used to collect the temperature of the circuit board where the controller is located, and send the temperature to the controller;

[0023] A first heating circuit is provided, and the controller heats the controller through the first heating circuit based on the temperature.

[0024] Optionally, it also includes:

[0025] The second heating circuit is used to heat the five-hole probe type pitot tube.

[0026] Optionally, it also includes:

[0027] The communication circuit is respectively connected to the controller and the flight control computer for communication between the controller and the flight control computer.

[0028] Optionally, it also includes:

[0029] The communication circuit adopts Flexray plus RS422&RS485 dual-redundancy bus communication design.

[0030] Optionally, the data fusion algorithm includes:

[0031] Neural network algorithms.

[0032] According to a second aspect of the present invention, an atmospheric data measurement method is provided. Based on the atmospheric data measurement system according to any one of the first aspects, the method comprises:

[0033] The three-way differential pressure sensor is used to measure the first pressure difference between the upper measuring point and the lower measuring point of the five-hole measuring points of the five-hole probe pitot tube, the second pressure difference between the left measuring point and the right measuring point, and the third pressure difference between the middle measuring point and the through measuring point;

[0034] Measuring the absolute pressure of the middle measuring point of the five hole measuring points based on an absolute pressure sensor;

[0035] Measuring atmospheric temperature based on atmospheric temperature measurement module;

[0036] Atmospheric data is calculated using a data fusion algorithm based on the first pressure difference, the second pressure difference, the third pressure difference, the absolute pressure and the atmospheric temperature.

[0037] The beneficial effects of the present invention are as follows: the present invention arranges five differential pressure measuring points in a cross shape at the front end of a five-hole probe pitot tube, measures the first pressure difference between the upper measuring point and the lower measuring point of the five-hole measuring point by a three-way differential pressure sensor; measures the second pressure difference between the left measuring point and the right measuring point of the five-hole measuring point; measures the third pressure difference between the middle measuring point and the through measuring point of the five-hole measuring point, measures the absolute pressure of the middle measuring point of the five-hole measuring point by a one-way absolute pressure sensor, measures the atmospheric temperature by an atmospheric temperature measurement module, realizes the atmospheric information measurement in a high-altitude and low-speed environment that cannot be realized by traditional atmospheric data systems, adopts a data fusion algorithm to solve the atmospheric data to realize the atmospheric data solution at an airspeed lower than 4m / s and an altitude of 300,000 meters, can accurately and reliably solve the atmospheric data, and provide important basic data support for flight control, navigation, performance evaluation, etc. of aircraft.

[0038] The system of the present invention has other characteristics and advantages, which will be apparent from the drawings incorporated herein and the following detailed description, or will be described in detail in the drawings incorporated herein and the following detailed description, which together serve to explain the specific principles of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention in conjunction with the accompanying drawings, in which like reference numerals generally represent like components.

[0040] Figure 1 A schematic diagram of an air data measurement system according to Embodiment 1 of the present invention is shown.

[0041] Figure 2 A schematic diagram showing the distribution and connection of measurement points of a five-hole probe-type pitot tube according to the first embodiment of the present invention is shown. DETAILED DESCRIPTION

[0042] The present invention will be described in more detail below with reference to the accompanying drawings. Although preferred embodiments of the present invention are shown in the accompanying drawings, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to make the present invention more thorough and complete, and to fully convey the scope of the present invention to those skilled in the art.

[0043] An atmospheric data measurement system according to the present invention comprises:

[0044] Five-hole probe pitot tube, the five-hole measuring points of the five-hole probe pitot tube are distributed in a cross shape, and multiple through-measuring points are set on the side of the five-hole probe pitot tube;

[0045] The three-way differential pressure sensor is used to measure the first pressure difference between the upper and lower measuring points of the five-hole measuring points; the second pressure difference between the left and right measuring points of the five-hole measuring points; and the third pressure difference between the middle measuring point and the through measuring point of the five-hole measuring points;

[0046] One absolute pressure sensor is used to measure the absolute pressure of the middle measuring point of the five-hole measuring points;

[0047] Atmospheric temperature measurement module, used to measure atmospheric temperature;

[0048] A controller, electrically connected to three differential pressure sensors, one absolute pressure sensor and an atmospheric temperature measurement module, for calculating atmospheric data using a data fusion algorithm based on the first pressure difference, the second pressure difference, the third pressure difference, the absolute pressure and the atmospheric temperature;

[0049] Secondary power supply, used to provide power to the air data measurement system.

[0050] Specifically, the present invention arranges five-hole differential pressure measuring points in a cross shape at the front end of the five-hole probe pitot tube. When the five-hole probe pitot tube is working, its five holes respectively sense different pressures, the central hole usually senses the total pressure of the airflow, and the four surrounding holes sense the static pressure of the airflow and the pressure components related to the airflow direction; by measuring these pressures, using the Bernoulli equation and other related principles, the speed of the airflow, the angle of attack and the sideslip angle of the aircraft and other parameters can be calculated; the first pressure difference between the upper measuring point and the lower measuring point of the five-hole measuring point is measured by a three-way differential pressure sensor, the second pressure difference between the left measuring point and the right measuring point of the five-hole measuring point is measured, and the third pressure difference between the middle measuring point and the through measuring point of the five-hole measuring point is measured; the three-way differential pressure sensor is a sensor that can simultaneously measure the pressure difference between three different positions or channels. It works based on the principle of pressure difference and electrical signal conversion. Generally speaking, when the pressure difference acts on the sensitive element of the sensor, it will cause physical changes in the sensitive element, such as strain, capacitance change or piezoelectric effect. These physical changes will be converted into electrical signals, and the size of the electrical signal is in a certain proportional relationship with the pressure difference. The absolute pressure of the middle point of the five-hole measuring points is measured by an absolute pressure sensor, and the atmospheric temperature is measured by the atmospheric temperature measurement module. The atmospheric data is solved by the data fusion algorithm to achieve the atmospheric data solution of airspeed below 4m / s and altitude of 300,000 meters, and the atmospheric information measurement in the high-altitude and low-speed environment that the traditional atmospheric data system cannot achieve is realized; the data fusion algorithm is to comprehensively process the data from multiple sensors to obtain more accurate and reliable information. In the atmospheric data solution, when it is necessary to deal with special cases such as airspeed below 4m / s and altitude of 300,000 meters, data fusion can use the complementary characteristics of different sensors to improve the solution accuracy, and provide important basic data support for the flight control, navigation, performance evaluation, etc. of the aircraft. On the aircraft, the secondary power supply provides stable power for avionics equipment (such as communication equipment, navigation systems, radar systems, etc.). For example, the 28V DC generated by the generator driven by the aircraft engine is converted into DC power of various voltage levels (such as ±5V, ±12V, ±15V, etc.) and AC power (such as 115V / 400Hz) to meet the power supply requirements of different electronic equipment. The secondary power supply adopts an airtight high-density power module, which can effectively reduce weight and adapt to high-altitude and low-pressure environments.

[0051] In one example, the atmospheric data includes:

[0052] Angle of attack, sideslip angle, atmospheric altitude, airspeed and static atmospheric temperature.

[0053] In one example, the angle of attack is resolved based on the first pressure difference, the sideslip angle is resolved based on the second pressure difference, the airspeed is resolved based on the third pressure difference, the atmospheric altitude is resolved based on the absolute pressure, and the atmospheric static temperature is resolved based on the atmospheric temperature.

[0054] Specifically, when the angle of attack of the aircraft changes, the angle of the airflow relative to the five-hole probe pitot tube will also change. The pressure difference felt by the upper and lower points is related to the size of the angle of attack. Within the small angle of attack range, as the angle of attack increases, the pressure at the upper point will gradually increase, the pressure at the lower point will gradually decrease, and the pressure difference between them will also increase accordingly. The pressure difference is converted into an electrical signal by a three-way differential pressure sensor, and then after calibration and calculation, the size of the angle of attack can be obtained. This measurement method is based on the principle of aerodynamics. The airflow will produce specific changes in the pressure distribution on the upper and lower surfaces of the pitot tube at different angles of attack, and this change can be captured by the differential pressure sensor. For the left and right points, when the aircraft has a sideslip, the airflow blows from the side, which will cause a difference in pressure on the left and right sides. The three-way differential pressure sensor measures the pressure difference between the left and right points and converts it into an electrical signal. In the absence of sideslip, the pressure on the left and right sides is basically equal, and the pressure difference is zero; when sideslip occurs, the pressure difference will increase with the increase of the sideslip angle. Through prior calibration and appropriate calculation algorithms, the size of the sideslip angle can be determined based on this pressure difference. Similarly, this is also based on the change in the pressure distribution on the left and right sides of the pitot tube in aerodynamics when the airflow is sliding. The three-way differential pressure sensor receives pressure signals from the middle point of the cross and multiple penetration points on the side of the pitot tube. The middle point measures the total pressure, which is the pressure when the airflow is completely stagnant, while the penetration point measures the static pressure. According to the Bernoulli equation (When the height remains unchanged, h is a constant and can be ignored), dynamic pressure Where ρ is the air density and v is the airspeed. When the air density is known, the airspeed can be calculated by measuring the differential pressure between the total pressure and the static pressure. Since air density is related to factors such as altitude and temperature, it is usually necessary to combine other atmospheric parameters (such as atmospheric pressure measured by an absolute pressure sensor to estimate altitude, temperature measured by a temperature sensor, etc.) to accurately calculate the air density and obtain a more accurate airspeed. The absolute pressure sensor receives a pressure signal from the intermediate measuring point, and this static pressure signal is closely related to the atmospheric altitude. According to the standard atmospheric model, atmospheric pressure decreases with increasing altitude, and the relationship roughly conforms to a certain mathematical model (such as the international standard atmospheric model). By measuring the static pressure and combining the pressure-altitude relationship formula in the standard atmospheric model, the atmospheric altitude of the aircraft can be calculated.

[0055] In one example, the atmospheric temperature measurement module includes:

[0056] Atmospheric temperature sensor, used to measure atmospheric temperature;

[0057] The temperature acquisition circuit is composed of a ΣΔ modulator and a digital filter, and is electrically connected to the atmospheric temperature sensor to acquire the analog signal of the atmospheric static temperature of the atmospheric temperature sensor, and convert the analog signal into a digital signal and send it to the controller.

[0058] Specifically, the ΣΔ (Sigma-Delta) circuit is an oversampling analog-to-digital conversion technology that oversamples the analog signal at a high frequency and then uses digital filtering technology to convert the oversampled signal into a high-precision digital output. When solving the atmospheric static temperature, the basic idea is to first amplify and condition the weak analog signal related to the atmospheric static temperature output by the temperature sensor, then perform analog-to-digital conversion through the ΣΔ circuit, and finally use the digital signal processing algorithm to solve the atmospheric static temperature from the converted digital signal. The ΣΔ modulator is the core part of the ΣΔ circuit. It consists of an integrator, a comparator, and a feedback DAC (digital-to-analog converter). The integrator integrates the input analog signal, and the comparator compares the integration result with a reference level to generate a single-bit digital output (0 or 1). The feedback DAC generates an analog feedback signal based on the digital output, which is subtracted from the input signal and sent to the integrator again to form a closed-loop system. The digital filter is used in the ΣΔ circuit to filter the high-frequency single-bit digital stream output by the ΣΔ modulator. It can be a low-pass filter that filters out high-frequency quantization noise, while decimating and averaging the digital signal to convert the oversampled signal into a low-frequency, high-precision digital signal. For example, by using a finite impulse response (FIR) digital filter, by selecting appropriate filter coefficients, effective suppression of quantization noise can be achieved, and according to the filter cutoff frequency and decimation rate, the frequency of the output digital signal can be adjusted to a range suitable for subsequent processing. After obtaining the digital signal converted by the ΣΔ circuit, it is necessary to solve the atmospheric static temperature according to the characteristics of the temperature sensor. For platinum resistance temperature sensors, according to their resistance-temperature characteristic formula R T =R 0 (1+αT)(where R T is the resistance value at temperature T, R 0 is the resistance value at the reference temperature, α is the temperature coefficient), as well as the conversion relationship between the signal conditioning circuit and the ΣΔ circuit, the relationship between temperature and digital signal can be derived.

[0059] In one example, it also includes:

[0060] A temperature sensor is used to collect the temperature of the circuit board where the controller is located and send the temperature to the controller;

[0061] The controller heats the controller via the first heating circuit based on the temperature.

[0062] Specifically, by collecting the temperature of the circuit board and using the controller to control the first heating circuit to heat, the normal operation of the atmospheric data measurement system in a low temperature environment of -90°C is achieved.

[0063] In one example, it also includes:

[0064] The second heating circuit is used to heat the five-hole probe type pitot tube.

[0065] Specifically, heating the five-hole probe pitot tube is mainly to prevent it from freezing during flight and ensure accurate measurement of flight parameters such as airspeed. Whether heating is required is determined by the flight control system or a special heating control device based on the aircraft's flight speed, altitude, outside temperature and other parameters.

[0066] In one example, it also includes:

[0067] The communication circuit is respectively connected to the controller and the flight control computer for communication between the controller and the flight control computer.

[0068] In one example, it also includes:

[0069] The communication circuit adopts Flexray plus RS422&RS485 dual-redundancy bus communication design.

[0070] Specifically, FlexRay is a high-speed, deterministic communication protocol. It has a high data transmission rate and can meet application scenarios with high requirements for real-time performance and bandwidth. FlexRay uses TDMA to communicate, dividing the communication time into fixed time slots. In each time slot, a specific node can send or receive data. This mechanism makes communication deterministic, effectively avoids data conflicts, and can accurately arrange the communication sequence between different devices. RS422 is a serial communication interface standard for balanced transmission. It uses differential signal transmission to effectively suppress common-mode interference and improve anti-interference ability. RS485 is also a serial communication standard for differential signal transmission. It has been improved on the basis of RS422. RS485 has better anti-interference performance and longer transmission distance; RS422 & RS485 dual-redundancy bus communication can improve system reliability and fault tolerance. FlexRay is mainly used for high-speed, critical data transmission with extremely high real-time requirements, such as control commands and status feedback in control systems. The RS422 & RS485 dual-redundancy bus can be used to transmit some data with relatively low real-time requirements but high reliability requirements, such as equipment configuration information, monitoring data, etc. In this way, the advantages of the two communication methods can be fully utilized to build an efficient and reliable communication system.

[0071] In one example, the data fusion algorithm includes:

[0072] Neural network algorithms.

[0073] Specifically, data fusion algorithms include weighted averaging, Kalman filter fusion and neural network fusion. The present invention adopts a neural network fusion method, such as BP, MLP, CNN, RNN and other neural networks. First, a neural network model is constructed, with the data of each sensor as the input layer neuron, and the solution results of the atmospheric data (such as airspeed, altitude, temperature, etc.) as the output layer neuron, with several hidden layers in the middle; then, the neural network is trained through a large amount of training data to enable it to learn the complex nonlinear relationship between the sensor data and the atmospheric data.

[0074] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments, but is not intended to be limiting of the present invention. It should be noted that the embodiments and features in the embodiments of the present invention may be combined with each other without conflict.

[0075] Embodiment 1

[0076] like Figure 1 As shown, this embodiment provides an atmospheric data measurement system, including:

[0077] Five-hole probe pitot tube, such as Figure 2 As shown in the figure, the differential pressure measuring points at the front end of the five-hole probe pitot tube are distributed in a cross shape, where the upper and lower points in the cross are Pa+ and Pa-, which are output to the angle of attack differential pressure sensor for measuring the angle of attack, and the left and right points in the cross are P β + Dot and P β - point output to the sideslip angle differential pressure sensor for measuring the sideslip angle. The cross middle position Pt point and the five-hole probe pitot tube measuring surface multiple penetration points Ps point output to the airspeed differential pressure sensor for measuring airspeed. Ps point is also input to the absolute pressure sensor for measuring atmospheric altitude and other information.

[0078] The three-way differential pressure sensor is used to measure the first pressure difference between Pa+ and Pa- of the five-hole measuring points; β + Dot and P β -The second pressure difference at point Pt; the third pressure difference between the five-hole measuring points Pt and Ps, the sensor range is -300Pa to 300Pa, with an accuracy of 0.5Pa.

[0079] One absolute pressure sensor, the sensor range is 20KPa-140KPa, the accuracy is 0.02%;

[0080] The atmospheric temperature sensor adopts a four-wire PT100 sensor and uses a ΣΔADC acquisition circuit without a constant current source to convert the analog signal of the atmospheric temperature collected by the atmospheric temperature sensor into a digital signal and send it to the main control ARM;

[0081] The main control ARM is electrically connected to three differential pressure sensors, one absolute pressure sensor and an atmospheric temperature measurement module, and is used to calculate atmospheric data using a data fusion algorithm based on the first pressure difference, the second pressure difference, the third pressure difference, the absolute pressure and the atmospheric temperature. The secondary power supply uses an airtight high-density power module, which can effectively reduce weight and adapt to high-altitude low-pressure environments.

[0082] Secondary power supply, used to provide power to the air data measurement system.

[0083] Atmospheric data includes:

[0084] Angle of attack, sideslip angle, atmospheric altitude, airspeed and static atmospheric temperature.

[0085] The angle of attack is calculated based on the first pressure difference, the sideslip angle is calculated based on the second pressure difference, the airspeed is calculated based on the third pressure difference, the atmospheric altitude is calculated based on the absolute pressure, and the atmospheric static temperature is calculated based on the atmospheric temperature.

[0086] The temperature sensor is used to collect the temperature of the circuit board where the main control ARM is located and send the temperature to the controller;

[0087] The controller heating circuit heats the main control ARM through the main control ARM heating circuit based on the temperature.

[0088] The Flexray communication circuit and the RS422&RS485 communication circuit are respectively connected to the main control ARM and the flight control computer for communication between the main control ARM and the flight control computer.

[0089] Fault detection circuit, used to detect system faults.

[0090] Pitot tube heating circuit, used to heat the pitot tube.

[0091] The data fusion algorithm adopts BP neural network algorithm.

[0092] Embodiment 2

[0093] This embodiment provides an atmospheric data measurement method, based on the atmospheric data measurement system described in Embodiment 1, including:

[0094] The first pressure difference between Pa+ and Pa- of the five-hole measuring points of the five-hole probe pitot tube is measured based on a three-way differential pressure sensor. β + Dot and P β - a second pressure difference at point Pt, and a third pressure difference between point Ps;

[0095] The absolute pressure of the Ps point of the five-hole measuring point is measured based on one absolute pressure sensor;

[0096] Measuring atmospheric temperature based on an atmospheric temperature sensor;

[0097] The atmospheric data is solved by using a data fusion algorithm based on the first pressure difference, the second pressure difference, the third pressure difference, the absolute pressure and the atmospheric temperature.

[0098] The embodiments of the present invention have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. An atmospheric data measurement system, characterized in that: include: A five-hole probe pitot tube, wherein the five-hole measuring points of the five-hole probe pitot tube are distributed in a cross shape, and a plurality of through measuring points are arranged on the side of the five-hole probe pitot tube; A three-way differential pressure sensor is used to measure the first pressure difference between the upper measuring point and the lower measuring point of the five-hole measuring point; to measure the second pressure difference between the left measuring point and the right measuring point of the five-hole measuring point; and to measure the third pressure difference between the middle measuring point of the five-hole measuring point and the through measuring point; An absolute pressure sensor is used to measure the absolute pressure of the middle measuring point of the five hole measuring points; Atmospheric temperature measurement module, used to measure atmospheric temperature; a controller, electrically connected to the three differential pressure sensors, the one absolute pressure sensor and the atmospheric temperature measurement module, and configured to calculate atmospheric data using a data fusion algorithm based on the first pressure difference, the second pressure difference, the third pressure difference, the absolute pressure and the atmospheric temperature; A secondary power supply is used to provide power to the air data measurement system.

2. The air data measurement system according to claim 1, characterized in that: The atmospheric data include: Angle of attack, sideslip angle, atmospheric altitude, airspeed and static atmospheric temperature.

3. The air data measurement system according to claim 2, characterized in that: The angle of attack is calculated based on the first pressure difference, the sideslip angle is calculated based on the second pressure difference, the airspeed is calculated based on the third pressure difference, the atmospheric altitude is calculated based on the absolute pressure, and the atmospheric static temperature is calculated based on the atmospheric temperature.

4. The air data measurement system according to claim 1, characterized in that: The atmospheric temperature measurement module comprises: Atmospheric temperature sensor, used to measure atmospheric temperature; The temperature acquisition circuit is composed of a ΣΔ modulator and a digital filter, and is electrically connected to the atmospheric temperature sensor to acquire the analog signal of the atmospheric static temperature of the atmospheric temperature sensor, and convert the analog signal into a digital signal and send it to the controller.

5. The air data measurement system according to claim 1, characterized in that: Also includes: A temperature sensor, used to collect the temperature of the circuit board where the controller is located, and send the temperature to the controller; A first heating circuit is provided, and the controller heats the controller through the first heating circuit based on the temperature.

6. The air data measurement system according to claim 1, characterized in that: Also includes: The second heating circuit is used to heat the five-hole probe type pitot tube.

7. The air data measurement system according to claim 1, characterized in that: Also includes: The communication circuit is respectively connected to the controller and the flight control computer for communication between the controller and the flight control computer.

8. The air data measurement system according to claim 1, characterized in that: Also includes: The communication circuit adopts Flexray plus RS422&RS485 dual-redundancy bus communication design.

9. The air data measurement system according to claim 8, characterized in that: The data fusion algorithm includes: Neural network algorithms.

10. An atmospheric data measurement method, based on the atmospheric data measurement system according to any one of claims 1 to 9, characterized in that: include: The three-way differential pressure sensor is used to measure the first pressure difference between the upper measuring point and the lower measuring point of the five-hole measuring points of the five-hole probe pitot tube, the second pressure difference between the left measuring point and the right measuring point, and the third pressure difference between the middle measuring point and the through measuring point; Measuring the absolute pressure of the middle measuring point of the five hole measuring points based on an absolute pressure sensor; Measuring atmospheric temperature based on atmospheric temperature measurement module; A data fusion algorithm is used to calculate atmospheric data based on the first pressure difference, the second pressure difference, the third pressure difference, the absolute pressure and the atmospheric temperature.

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