CN117872801A - Automatic flight control computer signal MATLAB simulation test device and test method - Google Patents
Automatic flight control computer signal MATLAB simulation test device and test method Download PDFInfo
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- CN117872801A CN117872801A CN202311795958.XA CN202311795958A CN117872801A CN 117872801 A CN117872801 A CN 117872801A CN 202311795958 A CN202311795958 A CN 202311795958A CN 117872801 A CN117872801 A CN 117872801A
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- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
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Abstract
The invention relates to the technical field of onboard automatic flight control computer test, in particular to an automatic flight control computer signal MATLAB simulation test device and a test method, wherein the test device comprises a cabinet; the industrial computer is arranged in the cabinet; the display, the keyboard and the mouse are arranged in the cabinet and are matched with the industrial computer; the system comprises a double-circuit direct-current stabilized voltage supply, a signal conditioning cabinet, an operating panel and a junction box. The invention can realize the functions of switching different states of the product, inputting initial parameters, collecting bus data, simulating automatic flight control signals and the like. The method can be used for online parameter adjustment, real-time check of test and automatic flight control signal output results, and simultaneously can also be used for simulating an air state and reproducing a flight process for air fault analysis. The dynamic excitation test is adopted in the test process, so that the real working state of the product is intuitively reflected, and the product repair quality is improved.
Description
Technical Field
The invention relates to the technical field of onboard automatic flight control computer testing, in particular to an automatic flight control computer signal MATLAB simulation testing device and a testing method.
Background
The automatic flight control computer is the core of the data processing, control and integration of the aircraft flight control system, and the reliability of the automatic flight control computer has a crucial influence on the flight safety of the aircraft. A certain automatic flight control computer adopts a three-axis full-digital automatic flight control system, a dual-redundancy control technology and an automatic throttle control technology. The system is crosslinked with an aircraft avionics system, a fly-by-wire flight control system, a power system, a sensor and the like to complete the functions of analog input/output, discrete input/output, GJB289A bus input/output, HB6O96 bus input/output, control law calculation, BIT and the like of an automatic flight control system.
Currently, commonly used automatic flight control computer test equipment generally adopts a static test method, and the method supplies power, starts and tests to an automatic flight control computer by manually stirring a switch, selecting an operating state and giving static excitation. In the test process, an operator is required to prompt operation according to equipment, observe the working state of a product and record output data. The method has the risks of single testing method, long testing time, incomplete testing points, incapability of reproducing on-board faults and the like, and does not meet the requirement of product testing.
The test system comprises an automatic flight control signal transmission disconnection device, automatic flight control system test interface equipment, an airborne crosslinked data bus coupler, a flight simulation system, an airborne crosslinked equipment simulator, a field visual operation guiding unit and a test system consisting of simulation test application software, wherein the test system is used for completing the simulation of the motion characteristics of an airplane in the test of the automatic flight control system, the simulation of crosslinked airborne equipment in a visual mode, and improving the test efficiency by taking the automatic flight control device, an automatic flight control computer, the flight control system bus coupler, an electric transmission flight control computer and an electric transmission flight actuating system as objects.
The method is a simulation of the motion characteristics of the aircraft in the test of an automatic flight control system and a simulation of cross-linked airborne equipment. There are the following disadvantages: firstly, the test system only realizes the simulation of the motion characteristics of the aircraft and the onboard equipment, is only the system function simulation, does not realize the analysis and the processing of the output control signals of an automatic flight control computer, and does not use visual simulation tools such as MATLAB and the like for visual display; secondly, the test program set by the test system is a single-variable excitation test, and in practice, the input variables on the machine are large, and the test system cannot be simulated.
Disclosure of Invention
In order to solve the technical problems, the invention provides an automatic flight control computer signal MATLAB simulation test device and a test method. The method can simulate the airplane to provide power for the automatic flight control computer, control the working state of the product, test the performance parameters in different states, store, display and calculate the parameters, and simultaneously determine the output characteristic curve of the automatic flight control signal of the product by applying dynamic excitation to the product in the test process, thereby completing the modeling of the product.
The technical problems to be solved by the invention are realized by adopting the following technical scheme:
an automatic flight control computer signal MATLAB simulation test device comprising:
a cabinet;
the industrial computer is arranged in the cabinet, an 18-slot PXI backboard is arranged in the industrial computer, and various boards are arranged in the 18-slot PXI backboard so as to realize switching, acquisition, transmission and calculation of related signals;
the display, the keyboard and the mouse are arranged in the cabinet and are matched with the industrial computer for user interaction operation;
the double-circuit direct-current stabilized power supply is arranged in the cabinet and used for providing two-circuit +28VDC working power supplies for the tested products;
the signal conditioning cabinet is arranged in the cabinet and connected with the industrial computer signal and the tested product, and is used for intensively processing various signals output by the industrial computer;
the control panel is arranged in the cabinet and used for providing a switching value signal and completing the simulation test of the tested product;
and the junction box is arranged in the cabinet and is used for leading out the electric wires.
Preferably, the industrial computer is provided with a GJB289A bus collector, an HB6096 bus collector, a discrete measurement board card, an analog measurement board card and a relay board card.
Preferably, the direct current stabilized power supply comprises two power supply sub-modules, namely a 220V/50Hz power supply sub-module and a +28VDC power supply sub-module.
A test method of an automatic flight control computer signal MATLAB simulation test device is applied to the automatic flight control computer signal MATLAB simulation test device, and comprises the following steps:
step 1, correctly connecting an automatic flight control computer with a testing device;
step 2, confirming that all switches on the front panel of the detection adapter of the testing device are at initial positions;
step 3, switching on an external 220V/50Hz power supply, starting a testing device, switching on a direct-current stabilized power supply switch, and regulating and outputting +28V direct-current voltage;
step 4, sequentially switching on a power supply of the automatic flight control system, a balancing power supply and a power-on switch of the automatic flight control system, and completing power-on of the system;
and 5, starting a testing task by the testing device. Simulating an external crosslinking environment of an automatic flight control computer to perform signal injection and acquisition;
step 6, completing dynamic injection of analog quantity signals, discrete quantity signals, GJB289A bus signals and HB6096 bus signals;
step 7, monitoring and collecting automatic flight control signals, real-time monitoring important input, output and state parameters of a system, resolving and converting in real time, and storing test results and readback in real time;
step 8, drawing an automatic flight control signal change curve in real time by using MATLAB simulation software;
and 9, after the work is completed, storing the simulation result.
Preferably, the state parameters in step 7 include angular position stability, barometric altitude stability, radio altitude stability, leveling.
Preferably, the angular position stability calculation is as follows:
wherein ny Given a given An overload value output by the computer; k (K) θ Is the pitch angle transmission ratio; θ 1 The real-time pitch angle of the aircraft is received by a computer; θ 2 The pitch angle is output by a computer;is a filtering time constant; />Is a signal proportional to overload;
wherein, gamma Given a given A tilt angle output for the computer;heading angle transmission ratio; θ 1 The real-time course angle of the aircraft is received by a computer; θ 2 And the heading angle is output by a computer.
Preferably, the air pressure altitude stability calculation is as follows:
wherein K is ΔH Is a height difference transmission ratio; ΔH is an air pressure height difference signal;is a vertical lifting speed transmission ratio; v y Is the vertical lifting speed.
Preferably, the radio highly stable calculation procedure is as follows:
preferably, the leveling calculation procedure is as follows:
the beneficial effects of the invention are as follows:
the invention provides the automatic flight control computer signal MATLAB simulation test device and the test method, which can realize the functions of switching different states of a product, inputting initial parameters, collecting bus data, simulating an automatic flight control signal and the like. The method can be used for online parameter adjustment, real-time check of test and automatic flight control signal output results, and simultaneously can also be used for simulating an air state and reproducing a flight process for air fault analysis. The dynamic excitation test is adopted in the test process, so that the real working state of the product is intuitively reflected, and the product repair quality is improved.
Drawings
The invention is further illustrated by the following examples in conjunction with the accompanying drawings:
FIG. 1 is a schematic diagram of a testing apparatus according to the present invention;
FIG. 2 is a schematic diagram of a connection structure between a testing device and a tested product according to the present invention;
FIG. 3 is a simulation result of a pitch control signal;
FIG. 4 is a highly preserved simulation result;
FIG. 5 is a simulation result of the auto throttle function;
fig. 6 is a flow chart of a signal simulation test.
Detailed Description
In order that the manner in which the invention is attained, as well as the features and advantages thereof, will be readily understood, a more particular description of the invention will be rendered by reference to the appended drawings.
An automatic flight control computer signal MATLAB simulation test device mainly carries out real-time calculation, signal real-time conversion and transmission of automatic flight control signals of an airplane. The test device adopts an integrated design principle, can adjust parameters online, check test and output results of automatic flight control signals in real time, and intuitively reflects the real working state of the product. And simultaneously, the method can simulate the air state and reproduce the flight process for air fault analysis. According to the configuration of the finished product operating system of the automatic flight control computer, the technical means such as bus control, signal conversion and the like are utilized to realize the excitation and detection of interface control signals and aviation bus signals; and the virtual instrument platform is utilized to develop test software to realize the construction of a performance verification platform of the product. The built testing device can realize the functions of switching different states of the product, inputting initial parameters, collecting bus data, simulating automatic flight control signals and the like.
Specifically, as shown in fig. 1, the testing device consists of a cabinet, an industrial computer, a double-circuit direct-current stabilized power supply, a signal conditioning cabinet, an operation panel, a junction box, a cable and the like.
The cabinet is a standard cabinet with the width of 19 inches and the height of 38U, and an industrial computer, a display, a keyboard mouse, a double-circuit direct-current stabilized power supply, a signal conditioning cabinet, an operation panel, a junction box and the like of the testing equipment are arranged in the cabinet. The tested product is connected with the testing device through a cable, and the cable is led out from the rear side of the cabinet.
The industrial computer accords with the standard specification of the PXI bus, adopts a standard 19-inch reinforced rack type design, is internally provided with an 18-slot PXI backboard, meets the requirement of a system slot, and provides a platform for system construction. The industrial computer is internally provided with a GJB289A bus collector, an HB6096 bus collector, a discrete measuring board card, an analog measuring board card and a relay board card, so that the switching, the collection, the transmission and the calculation of related signals are completed, and meanwhile, a display, a keyboard and a mouse are arranged for interactive operation of a user.
The double-circuit direct current stabilized power supply provides two paths of +28VDC working power supplies for products and comprises 2 power supply sub-modules: the input 220V/50Hz power supply sub-module outputs +28VDC power supply sub-module.
The signal conditioning case is mainly used for intensively processing various signals output by the motherboard, the required discrete quantity and analog quantity of the product and the GJB289A, HB6096 signals are led to the front panel, and during debugging, the conditioning case divides the signals into two parts through a circuit breaker, one part of the signals is connected to the front panel of the conditioning case for testing, and the other part of the signals is connected to the rear panel for connecting the tested product.
The control panel is used for providing a switching value signal and completing the simulation test of the tested product.
The junction box is used for leading out the electric wires, so that the circuit is tidier, the circuit staggering is reduced, and the circuit reliability is improved.
The cables are led out from the rear of the cabinet, and each cable is provided with a cable label for signal transmission of the testing device and the product.
The testing device is vertical equipment. The front of the device is a control and monitoring surface, a display, a keyboard mouse and a control panel of the adapter case. The rear part is a cable connection area, and a cable socket connected with the cable connection area and a cable socket connected with the flight control computer are arranged at the rear part of the cabinet.
The flow of the signal simulation test is shown in fig. 6. A test method of an automatic flight control computer signal MATLAB simulation test device is applied to the automatic flight control computer signal MATLAB simulation test device, and comprises the following steps:
and step 1, correctly connecting an automatic flight control computer with a testing device. Specifically, the correctness of the test cable connection is carefully checked according to the automatic flight control computer and test apparatus as shown in fig. 2.
And 2, confirming that all switches on the front panel of the detection adapter of the testing device are at initial positions.
And 3, switching on an external 220V/50Hz power supply, starting the testing device, switching on a direct-current stabilized power supply switch, and regulating and outputting +28V direct-current voltage.
And 4, sequentially switching on a power supply of the automatic flight control system, a balancing power supply and a power-on switch of the automatic flight control system, and completing power-on of the system.
And 5, starting a testing task by the testing device. And simulating an external crosslinking environment of an automatic flight control computer to perform signal injection and acquisition.
And 6, finishing dynamic injection of analog quantity signals, discrete quantity signals, GJB289A bus signals, HB6O96 bus signals and the like.
And 7, monitoring and collecting automatic flight control signals, and real-time monitoring important input, output and state parameters of the system, resolving and converting in real time, and storing test results and readback in real time.
(1) Angular position stabilization
In the case where the automatic control mode is allowed to be turned on without the air pressure altitude being stable, the radio altitude being stable, the leveling, landing, navigation and guidance modes, the device "automatic" signal lights are lit, indicating that the angular position stable mode is turned on.
Wherein ny Given a given An overload value output by the computer; k (K) θ Is the pitch angle transmission ratio; θ 1 The real-time pitch angle of the aircraft is received by a computer; θ 2 The pitch angle is output by a computer;as a filtering time constant, adjusting parameters according to the air pressure height and dynamic pressure;to compensate for the reduction of the vertical component of lift when the aircraft is tilted, for a signal proportional to the overload;
wherein, gamma Given a given A tilt angle output for the computer;heading angle transmission ratio; θ 1 The real-time course angle of the aircraft is received by a computer; θ 2 And the heading angle is output by a computer.
(2) High stability of air pressure
In the air pressure height stabilizing mode, the longitudinal channel stabilizes the air pressure height, and the lateral channel stabilizes the inclination angle and heading angle.
Wherein K is ΔH Is a height difference transmission ratio; ΔH is an air pressure height difference signal;is a vertical lifting speed transmission ratio; v y Is the vertical lifting speed.
(3) Radio is highly stable
Wherein f (DeltaH) r Vy) is related to topography variations, dynamic pressure, etc.
(4) Leveling device
In the method, in the process of the invention,and adjusting parameters according to the dynamic pressure.
And 8, drawing an automatic flight control signal change curve in real time by using MATLAB simulation software, wherein simulation results are shown in figures 3-5.
And 9, after the work is completed, storing the simulation result.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined in the appended claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (9)
1. An automatic flight control computer signal MATLAB emulation testing arrangement, its characterized in that: comprising the following steps:
a cabinet;
the industrial computer is arranged in the cabinet, an 18-slot PXI backboard is arranged in the industrial computer, and various boards are arranged in the 18-slot PXI backboard so as to realize switching, acquisition, transmission and calculation of related signals;
the display, the keyboard and the mouse are arranged in the cabinet and are matched with the industrial computer for user interaction operation;
the double-circuit direct-current stabilized power supply is arranged in the cabinet and used for providing two-circuit +28VDC working power supplies for the tested products;
the signal conditioning cabinet is arranged in the cabinet and connected with the industrial computer signal and the tested product, and is used for intensively processing various signals output by the industrial computer;
the control panel is arranged in the cabinet and used for providing a switching value signal and completing the simulation test of the tested product;
and the junction box is arranged in the cabinet and is used for leading out the electric wires.
2. An automatic flight control computer signal MATLAB simulation test device as claimed in claim 1, wherein: the industrial computer is provided with a GJB289A bus collector, an HB6096 bus collector, a discrete measurement board card, an analog measurement board card and a relay board card.
3. An automatic flight control computer signal MATLAB simulation test device as claimed in claim 1, wherein: the direct-current stabilized power supply comprises two power supply sub-modules, wherein the power supply sub-modules are input into a 220V/50Hz power supply sub-module and output into a +28VDC power supply sub-module.
4. A test method of an automatic flight control computer signal MATLAB simulation test device, applying an automatic flight control computer signal MATLAB simulation test device as claimed in any one of claims 1 to 3, comprising the steps of:
step 1, correctly connecting an automatic flight control computer with a testing device;
step 2, confirming that all switches on the front panel of the detection adapter of the testing device are at initial positions;
step 3, switching on an external 220V/50Hz power supply, starting a testing device, switching on a direct-current stabilized power supply switch, and regulating and outputting +28V direct-current voltage;
step 4, sequentially switching on a power supply of the automatic flight control system, a balancing power supply and a power-on switch of the automatic flight control system, and completing power-on of the system;
step 5, the testing device starts a testing task, and simulates an external cross-linking environment of an automatic flight control computer to perform signal injection and acquisition;
step 6, completing dynamic injection of analog quantity signals, discrete quantity signals, GJB289A bus signals and HB6096 bus signals;
step 7, monitoring and collecting automatic flight control signals, real-time monitoring important input, output and state parameters of a system, resolving and converting in real time, and storing test results and readback in real time;
step 8, drawing an automatic flight control signal change curve in real time by using MATLAB simulation software;
and 9, after the work is completed, storing the simulation result.
5. The method for testing an automatic flight control computer signal MATLAB simulation test device according to claim 4, wherein: the state parameters in step 7 include angular position stability, barometric altitude stability, radio altitude stability, leveling.
6. The method for testing an automatic flight control computer signal MATLAB simulation test device according to claim 5, wherein: the angular position stability calculation process is as follows:
wherein ny Given a given An overload value output by the computer; k (K) θ Is the pitch angle transmission ratio; θ 1 The real-time pitch angle of the aircraft is received by a computer; θ 2 The pitch angle is output by a computer;is a filtering time constant; />Is a signal proportional to overload;
wherein, gamma Given a given A tilt angle output for the computer;heading angle transmission ratio; θ 1 The real-time course angle of the aircraft is received by a computer; θ 2 And the heading angle is output by a computer.
7. The method for testing an automatic flight control computer signal MATLAB simulation test device according to claim 5, wherein: the calculation process of the high stability of the air pressure is as follows:
wherein K is ΔH Is a height difference transmission ratio; ΔH is an air pressure height difference signal; k (K) Vy Is a vertical lifting speed transmission ratio; v (V) y Is the vertical lifting speed.
8. The method for testing an automatic flight control computer signal MATLAB simulation test device according to claim 5, wherein: the radio highly stable calculation process is as follows:
9. the method for testing an automatic flight control computer signal MATLAB simulation test device according to claim 5, wherein: the leveling calculation process is as follows:
-ny given a given ＝K Vy ×V y 。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311795958.XA CN117872801A (en) | 2023-12-25 | 2023-12-25 | Automatic flight control computer signal MATLAB simulation test device and test method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202311795958.XA CN117872801A (en) | 2023-12-25 | 2023-12-25 | Automatic flight control computer signal MATLAB simulation test device and test method |
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| CN117872801A true CN117872801A (en) | 2024-04-12 |
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| CN202311795958.XA Pending CN117872801A (en) | 2023-12-25 | 2023-12-25 | Automatic flight control computer signal MATLAB simulation test device and test method |
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- 2023-12-25 CN CN202311795958.XA patent/CN117872801A/en active Pending
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