CN111605724B - Simulation test method for atmospheric data system - Google Patents
Simulation test method for atmospheric data system Download PDFInfo
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Abstract
The invention discloses an atmospheric data system simulation test method, which belongs to the technical field of aviation systems and is characterized by comprising the following steps: a. setting a flight envelope test point, extracting the height and Mach number of a turning point on a flight envelope as a test base point, and deducing the test point and the range according to the flight envelope characteristics, the sensor measurement accuracy and an atmospheric parameter formula; b. designing a hardware platform according to the characteristics of the atmospheric data system; c. and (4) carrying out software design according to the test points and ranges selected by the flight envelope, imaging the test result, and visually judging whether the test data is qualified. The invention introduces the flight envelope into the atmospheric data simulation, can realize the verification of the dynamic characteristics of the atmospheric data system, and can verify the reliability of the system in various flight states.
Description
Technical Field
The invention relates to the technical field of aviation systems, in particular to an atmospheric data system simulation test method.
Background
The atmospheric data system is an airborne avionics system for realizing atmospheric parameter measurement and calculation, original atmospheric data is measured by using a sensor, important flight parameters which can be used by an airborne key system of aircraft navigation and flight control are output through calculation and correction of a computer, and the flight safety and the quality of an aircraft are concerned. Therefore, air data system testing is essential in aircraft manufacture, maintenance and repair.
At present, a test system developed by a domestic large-scale aircraft manufacturer aiming at an aircraft atmospheric data system can carry out conventional performance test on the aircraft atmospheric data system. The standard atmospheric system is used for providing altitude and speed change parameters required in the measurement process of the aircraft atmospheric data system, and the operation conditions of the aircraft atmospheric data system under different atmospheric pressures are detected. The static test method adopting the traditional fixed-point setting can not verify the reliability of the air data system in different flight states of the airplane and can not realize the verification of the dynamic characteristics of the air data system. Meanwhile, when the conventional atmospheric data system testing equipment is used for on-board atmospheric data system inspection, operators need to manually read the test result of the atmospheric data system, so that the conditions of misjudgment and missed judgment are easy to occur, the test result is inaccurate, and the flight safety is influenced.
Chinese patent documents with publication number CN 110455331A and publication date of 2019, 11 and 15 disclose an intelligent air data tester for an airplane, which is characterized by comprising an air data input module and an airborne data acquisition and processing module; the atmospheric data input module is connected with the airplane atmospheric data system, outputs atmospheric pressure to the airplane atmospheric data system, and displays parameters of height, speed, left fuselage pressure and right fuselage pressure in real time; the air data input module sends a signal that the input air pressure reaches the specified requirement to the airborne data acquisition and processing module, and the airborne data acquisition and processing module is connected with the aircraft flight parameter system inspection interface and acquires the air parameters output by the aircraft air data system; and the collected atmospheric parameters are subjected to reduction processing and automatic judgment, and the automatic judgment result is displayed.
The intelligent airplane atmospheric data tester disclosed in the patent document automatically records and judges whether the atmospheric pressure altitude, Mach number, full pressure and static pressure parameters output by an atmospheric system are qualified or not by inputting a plurality of groups of different altitude and speed signals, automatically finishes all parameter input of the atmospheric system and automatically judges, stores and records calculation parameters of the atmospheric system, and greatly simplifies the inspection of an airplane atmospheric data system. However, the dynamic characteristics of the air data system cannot be verified, and the reliability of the system in various flight states cannot be verified.
Disclosure of Invention
The invention introduces the flight envelope into the atmospheric data simulation, can realize the verification of the dynamic characteristics of the atmospheric data system, and can verify the reliability of the system in various flight states.
The invention is realized by the following technical scheme:
a simulation test method for an atmospheric data system is characterized by comprising the following steps:
a. setting a flight envelope test point, extracting the height and Mach number of a turning point on a flight envelope as a test base point, and deducing the test point and the range according to the flight envelope characteristics, the sensor measurement accuracy and an atmospheric parameter formula;
b. designing a hardware platform according to the characteristics of the atmospheric data system;
c. and (4) carrying out software design according to the test points and ranges selected by the flight envelope, imaging the test result, and visually judging whether the test data is qualified.
In the step a, the setting of the flying envelope test point specifically comprises:
s1, extracting the height and Mach number of the turning point, wherein the height of the first point is 100m, and the Mach number is 1; the height of the second point is 8900m, and the Mach number is 2; the height of the third point is 18000m, and the Mach number is 2; the fourth point height is 18000m, and the Mach number is 0.6; the height of the fifth point is 9000m, and the Mach number is 0.2;
s2, defining a flight line segment between two adjacent test base points, wherein the first flight line segment is a flight parameter curve with the Mach number and the height uniformly increased; the second flight line section is a flight parameter curve with equal Mach number and uniformly raised height; the third flight line segment is a flight parameter curve with equal height and uniformly reduced Mach number; the fourth flight line segment is a flight parameter curve with the Mach number and the height uniformly reduced;
s3, calculating the test point number of the height and Mach number of the four flight line segments according to the formula 1-4;
in the formula: n is the number of height test points;
H height of The highest height in the flight line segment;
H is low in Is the lowest altitude in the flight line segment;
J H to a high degree of accuracy;
in the formula: m is the number of Mach number test points;
M big (a) The maximum Mach number in the flight line segment;
M small The minimum Mach number in the flight line segment;
M H mach number accuracy;
in the formula: h Become Is the rate of change of height;
in the formula: m Become Mach number rate of change;
s4, after the test points are selected, defining the height and Mach number range of each test point, calculating the height and Mach number range of each test point according to an atmospheric parameter correlation formula 5-9, and judging that the test points are qualified if the actual values of the test points are in the ranges during the test;
height calculation formula:
β＝(T H -T b )/(H-H b ) Formula 5
The math calculation formula:
m is less than 1:
m is more than 1:
in the step b, the hardware platform comprises an atmospheric data testing device and an air source control system, the atmospheric data testing device is connected with the air source control system through serial port communication, the full static pressure change of the atmospheric data system is remotely controlled, atmospheric parameters at the same time are collected, and the storage and interpretation of the test result are automatically completed; the air source control system provides complete pressure and vacuum measurement and control for the atmospheric data system by automatically or manually controlling the full static pressure and air pressure parameters required by the test.
The atmospheric data testing device comprises an industrial personal computer, an analog quantity acquisition and conversion module, a discrete quantity simulation acquisition module, a serial port communication module and a signal conditioning box; the industrial personal computer is used for remotely controlling the air source, providing a simulation signal source for the tested product through each functional module, and collecting, processing and outputting an output signal of the tested product; the analog quantity acquisition conversion module finishes the acquisition of analog quantity signals of a tested product through a bus system of the upper computer system; the discrete quantity simulation acquisition module is used for generating a required discrete quantity signal, acquiring the discrete quantity signal of a tested product and converting and outputting the resistance value of the total temperature resistor; the serial port communication module is connected with the industrial personal computer through Ethernet, the industrial personal computer virtualizes a plurality of serial ports on the upper computer, transmits simulation digital signals required by testing to the tested products through the serial port communication module, and transmits the serial digital signals of the tested products to the industrial personal computer through a network; and the signal conditioning box is used for providing a working power supply for each functional module, providing the analog quantity signal and the discrete quantity signal of each functional module for a test product, outputting the analog quantity and the discrete quantity of the test product to each functional module, and analyzing, processing, storing and outputting the analog quantity and the discrete quantity by the industrial personal computer.
The air source control system comprises a digital signal processing system, a pneumatic control unit, a pressure sensor, a pressure source and a communication module, wherein the digital signal processing system samples pressure data of the pressure sensor through an acquisition circuit to carry out corresponding pressure calculation, and the system controls a total channel, a static channel and a differential pressure channel according to an atmospheric pressure target value set by a user; the pneumatic control unit is used for finishing starting the pressure switch of the corresponding pressure channel, enabling the system to enter a pressure control preparation state and controlling the servo system of the corresponding channel to finish the control process of setting pressure; the pressure sensor adopts a high-precision quartz resonant pressure sensor to acquire the pressure values of positive pressure and negative pressure in a pressure source; the pressure source comprises a pressure pump and a vacuum pump, and provides positive pressure and negative pressure; the communication module is a serial port bus communication receiving sending end and is used for realizing communication with an industrial control computer in the atmospheric data testing device and controlling air source pressure points and pressure change rate parameters.
In the step c, the software design specifically means that LabVIEW and LabWindow/CVI test software are used as software development tools, an industrial personal computer firstly enters an automatic test program to start automatic test, and sends a current test point control command to the air source control system after reading a corresponding test point; the industrial personal computer reads the total static pressure value uploaded by the air data system, compares the total static pressure value with the total static pressure value of the current test point, if the difference value is greater than the control precision, reads again and compares the difference value, if the difference value is less than the control precision, records the data, and simultaneously draws a curve; and then judging whether the test point reaches the last test point, if not, entering the next test point, if so, ending the test, and returning the air source control system to the ground state by the full static pressure.
The invention has the beneficial effects that:
the fixed point test mode of the traditional test method is changed, the flight envelope is introduced into the atmospheric data simulation, the dynamic characteristic verification of the atmospheric data system can be realized, and the reliability of the system in various flight states can be verified. Meanwhile, the atmospheric data testing device can automatically set pressure and speed switching of each point, automatic change of testing conditions is realized, actual parameters are imaged, testing results are more visual and clear, and the conditions of misjudgment and missed judgment are avoided.
Drawings
The invention will be further described in detail with reference to the drawings and the detailed description, wherein:
FIG. 1 is a block diagram of a flying envelope test point selection according to the present invention;
FIG. 2 is a block diagram of a hardware platform of the present invention;
FIG. 3 is a block diagram of an atmospheric data testing apparatus according to the present invention;
FIG. 4 is a block diagram of an air supply control system of the present invention;
FIG. 5 is a flow chart of the automatic control of the present invention.
Detailed Description
Example 1
Referring to fig. 1-5, an atmospheric data system simulation test method includes the following steps:
a. setting a flight envelope test point, extracting the height and Mach number of a turning point on a flight envelope as a test base point, and deducing the test point and the range according to the flight envelope characteristics, the sensor measurement accuracy and an atmospheric parameter formula;
b. designing a hardware platform according to the characteristics of the atmospheric data system;
c. and (4) carrying out software design according to the test points and ranges selected by the flight envelope, imaging the test result, and visually judging whether the test data is qualified.
Example 2
Referring to fig. 1-5, an atmospheric data system simulation test method includes the following steps:
a. setting a flight envelope test point, extracting the height and Mach number of a turning point on a flight envelope as a test base point, and deducing the test point and the range according to the flight envelope characteristics, the sensor measurement accuracy and an atmospheric parameter formula;
b. designing a hardware platform according to the characteristics of the atmospheric data system;
c. and (4) carrying out software design according to the test points and ranges selected by the flight envelope, imaging the test result, and visually judging whether the test data is qualified.
In the step a, the setting of the flying envelope test point specifically comprises:
s1, extracting the height and Mach number of the turning point, wherein the height of the first point is 100m, and the Mach number is 1; the height of the second point is 8900m, and the Mach number is 2; the height of the third point is 18000m, and the Mach number is 2; the fourth point height is 18000m, and the Mach number is 0.6; the height of the fifth point is 9000m, and the Mach number is 0.2;
s2, defining a flight line segment between two adjacent test base points, wherein the first flight line segment is a flight parameter curve with the Mach number and the height uniformly increased; the second flight line section is a flight parameter curve with equal Mach number and uniformly raised height; the third flight line segment is a flight parameter curve with equal height and uniformly reduced Mach number; the fourth flight line segment is a flight parameter curve with the Mach number and the height uniformly reduced;
s3, calculating the test point number of the height and Mach number of the four flight line segments according to the formula 1-4;
in the formula: n is the number of height test points;
H height of The highest height in the flight line segment;
H is low with Is the lowest altitude in the flight line segment;
J H to a high degree of accuracy;
in the formula: m is the number of Mach number test points;
M big (a) The maximum Mach number in the flight line segment;
M small The minimum Mach number in the flight line segment;
M H mach number accuracy;
in the formula: h Become Is a heightA rate of change;
in the formula: m Become Mach number rate of change;
s4, after the test points are selected, defining the height and Mach number range of each test point, calculating the height and Mach number range of each test point according to the atmospheric parameter correlation formula 5-9, and judging that the test points are qualified if the actual values of the test points are in the ranges during the test;
height calculation formula:
β＝(T H -T b )/(H-H b ) Formula 5
The math calculation formula:
m is less than 1:
m is greater than 1:
example 3
Referring to fig. 1-5, an atmospheric data system simulation test method includes the following steps:
a. setting a flight envelope test point, extracting the height and Mach number of a turning point on the flight envelope as a test base point, and deducing the test point and the range according to the characteristics of the flight envelope, the measurement precision of a sensor and an atmospheric parameter formula;
b. designing a hardware platform according to the characteristics of the atmospheric data system;
c. and (4) carrying out software design according to the test points and ranges selected by the flight envelope, imaging the test result, and visually judging whether the test data is qualified.
In the step a, the setting of the flying envelope test point specifically comprises:
s1, extracting the height and Mach number of the turning point, wherein the height of the first point is 100m, and the Mach number is 1; the height of the second point is 8900m, and the Mach number is 2; the height of the third point is 18000m, and the Mach number is 2; the fourth point height is 18000m, and the Mach number is 0.6; the height of the fifth point is 9000m, and the Mach number is 0.2;
s2, defining a flight line segment between two adjacent test base points, wherein the first flight line segment is a flight parameter curve with the Mach number and the height uniformly increased; the second flight line section is a flight parameter curve with equal Mach number and uniformly raised height; the third flight line segment is a flight parameter curve with equal height and uniformly reduced Mach number; the fourth flight line segment is a flight parameter curve with the Mach number and the height uniformly reduced;
s3, calculating the test point number of the height and Mach number of the four flight line segments according to the formula 1-4;
in the formula: n is the number of height test points;
H high (a) The highest height in the flight line segment;
H is low in Is the lowest altitude in the flight line segment;
J H to a high degree of accuracy;
in the formula: m is the number of Mach number test points;
M big (a) The maximum Mach number in the flight line segment;
M small The minimum Mach number in the flight line segment;
M H is Mach ofNumber precision;
in the formula: h Become Is the rate of change of height;
in the formula: m Become Mach number rate of change;
s4, after the test points are selected, defining the height and Mach number range of each test point, calculating the height and Mach number range of each test point according to the atmospheric parameter correlation formula 5-9, and judging that the test points are qualified if the actual values of the test points are in the ranges during the test;
height calculation formula:
β＝(T H -T b )/(H-H b ) Formula 5
The math calculation formula:
m is less than 1:
m is more than 1:
in the step b, the hardware platform comprises an atmospheric data testing device and an air source control system, the atmospheric data testing device is connected with the air source control system through serial port communication, the full static pressure change of the atmospheric data system is remotely controlled, atmospheric parameters at the same time are collected, and the storage and interpretation of the test result are automatically completed; the air source control system provides complete pressure and vacuum measurement and control for the atmospheric data system by automatically or manually controlling the full static pressure and air pressure parameters required by the test.
Example 4
Referring to fig. 1-5, an atmospheric data system simulation test method includes the following steps:
a. setting a flight envelope test point, extracting the height and Mach number of a turning point on a flight envelope as a test base point, and deducing the test point and the range according to the flight envelope characteristics, the sensor measurement accuracy and an atmospheric parameter formula;
b. designing a hardware platform according to the characteristics of the atmospheric data system;
c. and (4) carrying out software design according to the test points and ranges selected by the flight envelope, imaging the test result, and visually judging whether the test data is qualified.
In the step a, the setting of the flying envelope test point specifically comprises:
s1, extracting the height and Mach number of the turning point, wherein the height of the first point is 100m, and the Mach number is 1; the height of the second point is 8900m, and the Mach number is 2; the height of the third point is 18000m, and the Mach number is 2; the fourth point height is 18000m, and the Mach number is 0.6; the height of the fifth point is 9000m, and the Mach number is 0.2;
s2, defining a flight line segment between two adjacent test base points, wherein the first flight line segment is a flight parameter curve with the Mach number and the height uniformly increased; the second flight line section is a flight parameter curve with equal Mach number and uniformly raised height; the third flight line segment is a flight parameter curve with equal height and uniformly reduced Mach number; the fourth flight line segment is a flight parameter curve with the Mach number and the height uniformly reduced;
s3, calculating the test point number of the height and Mach number of the four flight line segments according to the formula 1-4;
in the formula: n is the number of height test points;
H height of The highest height in the flight line segment;
H is low in Is the lowest altitude in the flight line segment;
J H to a high degree of accuracy;
in the formula: m is the number of Mach number test points;
M big (a) The maximum Mach number in the flight line segment;
M small The minimum Mach number in the flight line segment;
M H mach number accuracy;
in the formula: h Become Is the rate of change of height;
in the formula: m Become Mach number rate of change;
s4, after the test points are selected, defining the height and Mach number range of each test point, calculating the height and Mach number range of each test point according to the atmospheric parameter correlation formula 5-9, and judging that the test points are qualified if the actual values of the test points are in the ranges during the test;
height calculation formula:
β＝(T H -T b )/(H-H b ) Formula 5
The math calculation formula:
m is less than 1:
m is more than 1:
in the step b, the hardware platform comprises an atmospheric data testing device and an air source control system, the atmospheric data testing device is connected with the air source control system through serial port communication, the full static pressure change of the atmospheric data system is remotely controlled, atmospheric parameters at the same time are collected, and the storage and interpretation of the test result are automatically completed; the air source control system provides complete pressure and vacuum measurement and control for the atmospheric data system by automatically or manually controlling the full static pressure and air pressure parameters required by the test.
The atmospheric data testing device comprises an industrial personal computer, an analog quantity acquisition and conversion module, a discrete quantity simulation acquisition module, a serial port communication module and a signal conditioning box; the industrial personal computer is used for remotely controlling the air source, providing a simulation signal source for the tested product through each functional module, and collecting, processing and outputting an output signal of the tested product; the analog quantity acquisition conversion module finishes the acquisition of analog quantity signals of a tested product through a bus system of the upper computer system; the discrete quantity simulation acquisition module is used for generating a required discrete quantity signal, acquiring the discrete quantity signal of a tested product and converting and outputting the resistance value of the total temperature resistor; the serial port communication module is connected with the industrial personal computer through Ethernet, the industrial personal computer virtualizes a multi-path serial port on the upper computer, transmits simulation digital signals required by testing to the tested products through the serial port communication module, and transmits the serial digital signals of the tested products to the industrial personal computer through a network; and the signal conditioning box is used for providing a working power supply for each functional module, providing the analog quantity signal and the discrete quantity signal of each functional module for a test product, outputting the analog quantity and the discrete quantity of the test product to each functional module, and analyzing, processing, storing and outputting the analog quantity and the discrete quantity by the industrial personal computer.
Example 5
Referring to fig. 1-5, an atmospheric data system simulation test method includes the following steps:
a. setting a flight envelope test point, extracting the height and Mach number of a turning point on a flight envelope as a test base point, and deducing the test point and the range according to the flight envelope characteristics, the sensor measurement accuracy and an atmospheric parameter formula;
b. designing a hardware platform according to the characteristics of the atmospheric data system;
c. and (4) carrying out software design according to the test points and ranges selected by the flight envelope, imaging the test result, and visually judging whether the test data is qualified.
In the step a, the setting of the flying envelope test point specifically comprises:
s1, extracting the height and Mach number of the turning point, wherein the height of the first point is 100m, and the Mach number is 1; the height of the second point is 8900m, and the Mach number is 2; the height of the third point is 18000m, and the Mach number is 2; the fourth point height is 18000m, and the Mach number is 0.6; the height of the fifth point is 9000m, and the Mach number is 0.2;
s2, defining a flight line segment between two adjacent test base points, wherein the first flight line segment is a flight parameter curve with the Mach number and the height uniformly increased; the second flight line section is a flight parameter curve with equal Mach number and uniformly raised height; the third flight line segment is a flight parameter curve with equal height and uniformly reduced Mach number; the fourth flight line segment is a flight parameter curve with the Mach number and the height uniformly reduced;
s3, calculating the test point number of the height and Mach number of the four flight line segments according to the formula 1-4;
in the formula: n is the number of height test points;
H height of The highest height in the flight line segment;
H is low in Is the lowest altitude in the flight line segment;
J H to a high degree of accuracy;
in the formula: m is the number of Mach number test points;
M big (a) The maximum Mach number in the flight line segment;
M small The minimum Mach number in the flight line segment;
M H mach number accuracy;
in the formula: h Become Is the rate of change of height;
in the formula: m Become Mach number rate of change;
s4, after the test points are selected, defining the height and Mach number range of each test point, calculating the height and Mach number range of each test point according to the atmospheric parameter correlation formula 5-9, and judging that the test points are qualified if the actual values of the test points are in the ranges during the test;
the height calculation formula:
β＝(T H -T b )/(H-H b ) Formula 5
The math calculation formula:
m is less than 1:
m is more than 1:
in the step b, the hardware platform comprises an atmospheric data testing device and an air source control system, the atmospheric data testing device is connected with the air source control system through serial port communication, the full static pressure change of the atmospheric data system is remotely controlled, atmospheric parameters at the same time are collected, and the storage and interpretation of the test result are automatically completed; the air source control system provides complete pressure and vacuum measurement and control for the atmospheric data system by automatically or manually controlling the full static pressure and air pressure parameters required by the test.
The atmospheric data testing device comprises an industrial personal computer, an analog quantity acquisition and conversion module, a discrete quantity simulation acquisition module, a serial port communication module and a signal conditioning box; the industrial personal computer is used for remotely controlling the air source, providing a simulation signal source for the tested product through each functional module, and collecting, processing and outputting an output signal of the tested product; the analog quantity acquisition conversion module finishes the acquisition of analog quantity signals of a tested product through a bus system of the upper computer system; the discrete quantity simulation acquisition module is used for generating a required discrete quantity signal, acquiring the discrete quantity signal of a tested product and converting and outputting the resistance value of the total temperature resistor; the serial port communication module is connected with the industrial personal computer through Ethernet, the industrial personal computer virtualizes a plurality of serial ports on the upper computer, transmits simulation digital signals required by testing to the tested products through the serial port communication module, and transmits the serial digital signals of the tested products to the industrial personal computer through a network; and the signal conditioning box is used for providing a working power supply for each functional module, providing the analog quantity signal and the discrete quantity signal of each functional module for a test product, outputting the analog quantity and the discrete quantity of the test product to each functional module, and analyzing, processing, storing and outputting the analog quantity and the discrete quantity by the industrial personal computer.
The air source control system comprises a digital signal processing system, a pneumatic control unit, a pressure sensor, a pressure source and a communication module, wherein the digital signal processing system samples pressure data of the pressure sensor through an acquisition circuit to carry out corresponding pressure calculation, and the system controls a total channel, a static channel and a differential pressure channel according to an atmospheric pressure target value set by a user; the pneumatic control unit is used for finishing starting the pressure switch of the corresponding pressure channel, enabling the system to enter a pressure control preparation state and controlling the servo system of the corresponding channel to finish the control process of setting pressure; the pressure sensor adopts a high-precision quartz resonant pressure sensor to acquire the pressure values of positive pressure and negative pressure in a pressure source; the pressure source comprises a pressure pump and a vacuum pump, and provides positive pressure and negative pressure; the communication module is a serial bus communication receiving sending end and is used for realizing communication with an industrial control machine in the atmospheric data testing device and controlling the pressure point and the pressure change rate parameter of the air source.
Example 6
Referring to fig. 1-5, an atmospheric data system simulation test method includes the following steps:
a. setting a flight envelope test point, extracting the height and Mach number of a turning point on a flight envelope as a test base point, and deducing the test point and the range according to the flight envelope characteristics, the sensor measurement accuracy and an atmospheric parameter formula;
b. designing a hardware platform according to the characteristics of the atmospheric data system;
c. and (4) carrying out software design according to the test points and ranges selected by the flight envelope, imaging the test result, and visually judging whether the test data is qualified.
In the step a, the setting of the flying envelope test point specifically comprises:
s1, extracting the height and Mach number of the turning point, wherein the height of the first point is 100m, and the Mach number is 1; the height of the second point is 8900m, and the Mach number is 2; the height of the third point is 18000m, and the Mach number is 2; the fourth point height is 18000m, and the Mach number is 0.6; the height of the fifth point is 9000m, and the Mach number is 0.2;
s2, defining a flight line segment between two adjacent test base points, wherein the first flight line segment is a flight parameter curve with the Mach number and the height uniformly increased; the second flight line section is a flight parameter curve with equal Mach number and uniformly raised height; the third flight line segment is a flight parameter curve with equal height and uniformly reduced Mach number; the fourth flight line segment is a flight parameter curve with the Mach number and the height uniformly reduced;
s3, calculating the test point number of the height and Mach number of the four flight line segments according to the formula 1-4;
in the formula: n is the number of height test points;
H height of The highest height in the flight line segment;
H is low in Is the lowest altitude in the flight line segment;
J H to a high degree of accuracy;
in the formula: m is the number of Mach number test points;
M big (a) The maximum Mach number in the flight line segment;
M small The minimum Mach number in the flight line segment;
M H mach number accuracy;
in the formula: h Become Is the rate of change of height;
in the formula: m Become Mach number rate of change;
s4, after the test points are selected, defining the height and Mach number range of each test point, calculating the height and Mach number range of each test point according to the atmospheric parameter correlation formula 5-9, and judging that the test points are qualified if the actual values of the test points are in the ranges during the test;
height calculation formula:
β＝(T H -T b )/(H-H b ) Formula 5
The math calculation formula:
m is less than 1:
m is more than 1:
in the step b, the hardware platform comprises an atmospheric data testing device and an air source control system, the atmospheric data testing device is connected with the air source control system through serial port communication, the full static pressure change of the atmospheric data system is remotely controlled, atmospheric parameters at the same time are collected, and the storage and interpretation of the test result are automatically completed; the air source control system provides complete pressure and vacuum measurement and control for the atmospheric data system by automatically or manually controlling the full static pressure and air pressure parameters required by the test.
The atmospheric data testing device comprises an industrial personal computer, an analog quantity acquisition and conversion module, a discrete quantity simulation acquisition module, a serial port communication module and a signal conditioning box; the industrial personal computer is used for remotely controlling the air source, providing a simulation signal source for the tested product through each functional module, and collecting, processing and outputting an output signal of the tested product; the analog quantity acquisition conversion module finishes the acquisition of analog quantity signals of a tested product through a bus system of the upper computer system; the discrete quantity simulation acquisition module is used for generating a required discrete quantity signal, acquiring the discrete quantity signal of a tested product and converting and outputting the resistance value of the total temperature resistor; the serial port communication module is connected with the industrial personal computer through Ethernet, the industrial personal computer virtualizes a multi-path serial port on the upper computer, transmits simulation digital signals required by testing to the tested products through the serial port communication module, and transmits the serial digital signals of the tested products to the industrial personal computer through a network; and the signal conditioning box is used for providing a working power supply for each functional module, providing the analog quantity signal and the discrete quantity signal of each functional module for a test product, outputting the analog quantity and the discrete quantity of the test product to each functional module, and analyzing, processing, storing and outputting the analog quantity and the discrete quantity by the industrial personal computer.
The air source control system comprises a digital signal processing system, a pneumatic control unit, a pressure sensor, a pressure source and a communication module, wherein the digital signal processing system samples pressure data of the pressure sensor through an acquisition circuit to carry out corresponding pressure calculation, and the system controls a total channel, a static channel and a differential pressure channel according to an atmospheric pressure target value set by a user; the pneumatic control unit is used for finishing starting the pressure switch of the corresponding pressure channel, enabling the system to enter a pressure control preparation state and controlling the servo system of the corresponding channel to finish the control process of setting pressure; the pressure sensor adopts a high-precision quartz resonant pressure sensor to acquire the pressure values of positive pressure and negative pressure in a pressure source; the pressure source comprises a pressure pump and a vacuum pump, and provides positive pressure and negative pressure; the communication module is a serial bus communication receiving sending end and is used for realizing communication with an industrial control machine in the atmospheric data testing device and controlling the pressure point and the pressure change rate parameter of the air source.
In the step c, the software design specifically means that LabVIEW and LabWindow/CVI test software are used as software development tools, an industrial personal computer firstly enters an automatic test program to start automatic test, and sends a current test point control command to the air source control system after reading a corresponding test point; the industrial personal computer reads the total static pressure value uploaded by the air data system, compares the total static pressure value with the total static pressure value of the current test point, if the difference value is greater than the control precision, reads again and compares the difference value, if the difference value is less than the control precision, records the data, and simultaneously draws a curve; and then judging whether the test point reaches the last test point, if not, entering the next test point, if so, ending the test, and returning the air source control system to the ground state by the full static pressure.
Claims (5)
1. A simulation test method for an atmospheric data system is characterized by comprising the following steps:
a. setting a flight envelope test point, extracting the height and Mach number of a turning point on a flight envelope as a test base point, and deducing the test point and the range according to the flight envelope characteristics, the sensor measurement accuracy and an atmospheric parameter formula;
b. designing a hardware platform according to the characteristics of the atmospheric data system;
c. carrying out software design according to the test points and the range selected by the flight envelope, imaging the test result, and visually judging whether the test data is qualified;
in the step a, the setting of the flying envelope test point specifically comprises:
s1, extracting the height and Mach number of the turning point, wherein the height of the first point is 100m, and the Mach number is 1; the height of the second point is 8900m, and the Mach number is 2; the height of the third point is 18000m, and the Mach number is 2; the fourth point height is 18000m, and the Mach number is 0.6; the height of the fifth point is 9000m, and the Mach number is 0.2;
s2, defining a flight line segment between two adjacent test base points, wherein the first flight line segment is a flight parameter curve with the Mach number and the height uniformly increased; the second flight line section is a flight parameter curve with equal Mach number and uniformly raised height; the third flight line segment is a flight parameter curve with equal height and uniformly reduced Mach number; the fourth flight line segment is a flight parameter curve with the Mach number and the height uniformly reduced;
s3, calculating the test point number of the height and Mach number of the four flight line segments according to the formula 1-4;
in the formula: n is the number of height test points;
H height of The highest height in the flight line segment;
H is low in Is the lowest altitude in the flight line segment;
J H to a high degree of accuracy;
in the formula: m is the number of Mach number test points;
M big (a) The maximum Mach number in the flight line segment;
M small The minimum Mach number in the flight line segment;
M H mach number accuracy;
in the formula: h Become Is the rate of change of height;
in the formula: m Become Mach number rate of change;
s4, after the test points are selected, defining the height and Mach number range of each test point, calculating the height and Mach number range of each test point according to an atmospheric parameter correlation formula 5-9, and judging that the test points are qualified if the actual values of the test points are in the ranges during the test;
height calculation formula:
β＝(T H -T b )/(H-H b ) Formula 5
The math calculation formula:
m is less than 1:
m is more than 1:
wherein:
beta is a vertical temperature gradient;
T H corresponding to the atmospheric temperature for the respective altitude;
T b the atmospheric temperature of the corresponding layer;
h is the gravitational potential height;
H b the lower height of the corresponding layer;
p is the corresponding atmospheric static pressure at the corresponding height;
p b the atmospheric pressure below the corresponding layer;
g 0 is the free fall acceleration;
LR is a gas parameter;
exp is an exponential function with a natural constant e as the base;
Q c atmospheric dynamic pressure;
P s atmospheric static pressure;
M a is mach number.
2. The atmospheric data system simulation test method of claim 1, wherein: in the step b, the hardware platform comprises an atmospheric data testing device and an air source control system, the atmospheric data testing device is connected with the air source control system through serial port communication, the full static pressure change of the atmospheric data system is remotely controlled, atmospheric parameters at the same time are collected, and the storage and interpretation of test results are automatically completed; the air source control system provides complete pressure and vacuum measurement and control for the atmospheric data system by automatically or manually controlling the full static pressure and air pressure parameters required by the test.
3. The atmospheric data system simulation test method of claim 2, wherein: the atmospheric data testing device comprises an industrial personal computer, an analog quantity acquisition and conversion module, a discrete quantity simulation acquisition module, a serial port communication module and a signal conditioning box; the industrial personal computer is used for remotely controlling the air source, providing a simulation signal source for the tested product through each functional module, and collecting, processing and outputting an output signal of the tested product; the analog quantity acquisition conversion module finishes the acquisition of analog quantity signals of a tested product through a bus system of the upper computer system; the discrete quantity simulation acquisition module is used for generating a required discrete quantity signal, acquiring the discrete quantity signal of a tested product and converting and outputting the resistance value of the total temperature resistor; the serial port communication module is connected with the industrial personal computer through Ethernet, the industrial personal computer virtualizes a plurality of serial ports on the upper computer, transmits simulation digital signals required by testing to the tested products through the serial port communication module, and transmits the serial digital signals of the tested products to the industrial personal computer through a network; and the signal conditioning box is used for providing a working power supply for each functional module, providing the analog quantity signal and the discrete quantity signal of each functional module for a test product, outputting the analog quantity and the discrete quantity of the test product to each functional module, and analyzing, processing, storing and outputting the analog quantity and the discrete quantity by the industrial personal computer.
4. The atmospheric data system simulation test method of claim 2, wherein: the air source control system comprises a digital signal processing system, a pneumatic control unit, a pressure sensor, a pressure source and a communication module, wherein the digital signal processing system samples pressure data of the pressure sensor through an acquisition circuit to carry out corresponding pressure calculation, and the system controls a total channel, a static channel and a differential pressure channel according to an atmospheric pressure target value set by a user; the pneumatic control unit is used for finishing starting the pressure switch of the corresponding pressure channel, enabling the system to enter a pressure control preparation state and controlling the servo system of the corresponding channel to finish the control process of setting pressure; the pressure sensor adopts a high-precision quartz resonant pressure sensor to acquire the pressure values of positive pressure and negative pressure in a pressure source; the pressure source comprises a pressure pump and a vacuum pump, and provides positive pressure and negative pressure; the communication module is a serial bus communication receiving sending end and is used for realizing communication with an industrial control machine in the atmospheric data testing device and controlling the pressure point and the pressure change rate parameter of the air source.
5. The atmospheric data system simulation test method of claim 2, wherein: in the step c, the software design specifically means that LabVIEW and LabWindow/CVI test software are used as software development tools, an industrial personal computer firstly enters an automatic test program to start automatic test, and sends a current test point control command to the air source control system after reading a corresponding test point; the industrial personal computer reads the total static pressure value uploaded by the air data system, compares the total static pressure value with the total static pressure value of the current test point, if the difference value is greater than the control precision, reads again and compares the difference value, if the difference value is less than the control precision, records the data, and simultaneously draws a curve; and then judging whether the test point reaches the last test point, if not, entering the next test point, if so, ending the test, and returning the air source control system to the ground state by the full static pressure.
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