CN110488630B - Test system and test method for controlling stability-increasing flight control computer - Google Patents
Test system and test method for controlling stability-increasing flight control computer Download PDFInfo
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- CN110488630B CN110488630B CN201910635610.1A CN201910635610A CN110488630B CN 110488630 B CN110488630 B CN 110488630B CN 201910635610 A CN201910635610 A CN 201910635610A CN 110488630 B CN110488630 B CN 110488630B
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Abstract
The invention discloses a test system and a test method for controlling a stability-increasing flight control computer, which comprises a complete machine comprehensive test platform and a function test module, wherein the test platform is provided with a simulation airplane bus module and is mainly used for simulating various bus signals cross-linked with the control stability-increasing flight control computer, the bus signals are converted by using GJB289A and ARINC429 bus board cards and are sent to the control stability-increasing flight control computer, and the system bus signals are tested by simulating a bus fault mode through software; the method is used for controlling the closed-loop dynamic working mode of the stability-increasing computer for real simulation, simulating backup function frequency response, various sensor signal dynamic simulation and various execution component model dynamic hardware-in-loop simulation. By means of the fault injection testing method, the problem that fault positioning is difficult in the testing process of the traditional testing equipment in the past is solved, and the practicability of the testing scheme is guaranteed.
Description
Technical Field
The invention relates to the field of testing of aircraft control systems, in particular to a testing system of a flight control computer, and belongs to the technical field of inspection or monitoring of control systems.
Background
The control and stability augmentation flight control computer is the core of the whole flight control system, a high-speed parallel bus is adopted to carry out the structural design of a redundancy system, the redundancies carry out information mutual transmission through high-speed digital differential signals, the structure and the function are complex, the internal/external cross-linking relation is multiple, the reliability, the testability, the fault diagnosis/maintenance guarantee requirement are high, the service period is long, and the technology upgrading capability is strong. It is a product of comprehensive application of modern electronic technology, microelectronic technology, digital technology, bus technology, computer technology, servo control technology, network technology and other advanced technologies. The external interface signals of a certain model of control stability-increasing flight control computer can reach more than 1000 paths, the types of the signals are various (including functional signals of fault detection, fault management, fault alarm, manual and automatic switching logic and the like), the precision requirement is high, if the traditional manual test equipment is used, the test coverage rate is low, the precision of an actuating mechanism model is poor, and the comprehensive test deviation of the control stability-increasing flight control computer is large. In order to provide an operating environment for the comprehensive performance verification and test of the control stability-increasing flight control computer, a test platform and a test method for controlling an interface and a functional module of the control stability-increasing flight control computer need to be designed, but the existing test means cannot meet the requirements, and a novel comprehensive test system and a test method special for the aircraft control stability-increasing flight control computer need to be developed.
Disclosure of Invention
The invention aims to provide an environment for providing operation for verifying and testing the comprehensive performance of a control stability-increasing flight control computer, and provides a test system for controlling an interface and a functional module of the control stability-increasing flight control computer, which is used for a special comprehensive test and test method for a novel airplane control stability-increasing flight control computer.
The problem of the invention is realized by the following technical scheme:
a test system for controlling and stabilizing a flight control computer comprises a complete machine comprehensive test platform and a function test module, wherein the test platform is provided with a simulation airplane bus module and is mainly used for simulating various bus signals cross-linked with the flight control computer for controlling and stabilizing, the bus signals are converted into bus signals by using GJB289A and ARINC429 bus board cards and are sent to the flight control computer for controlling and stabilizing, and the bus signals are tested by simulating a bus fault mode through software;
the functional module testing part comprises a PXI case, an adapter and an industrial personal computer software testing module, wherein the adapter is used for connecting a tested unit, and the PXI case comprises an ACE analog electronic testing module, a DCE digital electronic testing module, an avionic bus testing module, a special signal simulation module, an interface and a power supply system.
Each analog channel is configured with a plurality of independent excitation/measurement instruments: high-speed analog input/output and dynamic waveform editor, dynamic signal simulation analyzer, and high-precision embedded signal analyzer.
A test method for controlling a stability-increasing flight control computer comprises the following steps:
step 1: the power supply system on the analog machine provides power for three power supplies of the control stability-increasing flight control computer, and can independently control the on-off of the three power supplies to monitor and protect the power supply;
and 2, step: acquiring an output power supply signal of a control stability augmentation flight control computer;
and step 3: the communication and data cross-linking are carried out with a control stability augmentation flight control computer through an RS422 communication interface;
and 4, step 4: discrete input and output signals of the analog control stability-increasing flight control computer comprise 28V/on signals and 15V ground/on signals;
and 5: simulating HB6096 bus and GJB289A bus signals to complete bus communication and detection with the to-be-detected control stability-increasing flight control computer;
step 6: completing the simulation of various sensor signals, including the simulation of alternating current sensors such as dynamic and static pressures, sideslip angles, left and right attack angles, angular displacement and the like, and direct current sensors such as acceleration, angular velocity and the like;
and 7: finishing the simulation of various horizontal tail, aileron and rudder steering engine signals, including the simulation of horizontal tail, limit, front fly, flaperon, rudder and other signals;
and 8: the method can complete the setting of the analog signal of the control stability-increasing flight control computer and can acquire the output of the analog signal of the computer in real time.
The test method completes the test and record of the product to be tested, the input/output management and channel fault logic, the bus receiving/sending test and the CCDL transmission.
According to the test method, simulation tests of a left/right horizontal tail steering engine, a left/right front fly aileron steering engine, a direction steering engine, a left/right servo amplification loop, synchronization and signal cross transmission control tests among channels, voting and monitoring tests of redundancy signals, and system control logic synthesis and control mode conversion tests are realized.
The invention has the beneficial effects that:
the invention has the advantages of automatic test function, high-precision automatic analysis of test results, automatic comparison of test results according to product tolerance requirements, elimination of errors caused by artificial tests, high test precision and complete fitting of various steering engine and sensor parameters and various simulation modules, and meets the requirement of controlling the flight control computer for stability augmentation by more than 95%.
The test of the functional signal interfaces, such as fault detection, fault management, fault alarm, manual and automatic switching logic, and the like, outside the control stability-increasing flight control computer can be realized.
The test of the whole machine and the functional module can be realized, the closed loop dynamic working mode of the stability-increasing computer is controlled for real simulation, and the frequency response of the backup function, the dynamic simulation of various sensor signals and the dynamic hardware-in-loop simulation of various executive component models are simulated. By means of the fault injection testing method, the problem that fault positioning is difficult in the testing process of the traditional testing equipment in the past is solved, and whether the equipment is in a normal working state or not can be judged. The problem that communication fault tracking is not compiled is solved, the practicability of the test scheme is guaranteed, and the defect that false alarm is easy to occur due to the fact that multiple paths of excitation and acquisition signals are detected conventionally is overcome.
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The invention will be further described with reference to the accompanying drawings.
FIG. 1 is a schematic block diagram of the test and verification of the comprehensive test platform of the flight control computer for controlling stability augmentation according to the present invention;
FIG. 2 is a flow chart of the operation of a computer test algorithm for controlling stability augmentation;
the list of reference numbers in the figures is: 1. the method comprises the steps of controlling and stabilizing a flight control computer comprehensive test platform, 1-1, an industrial control computer (test software), 1-2, a PXI case, 1-3, an adapter, 2, a tested unit, 3 and a software test platform.
Detailed Description
Referring to fig. 1, the invention is a test system for controlling a stability-increasing flight control computer, which comprises a complete machine comprehensive test platform and a function test module, wherein the test platform is provided with a simulation aircraft bus module and is mainly used for simulating various bus signals cross-linked with the control stability-increasing flight control computer, converting the bus signals into bus signals by using GJB289A and ARINC429 bus board cards, sending the bus signals to the control stability-increasing flight control computer, and testing system bus signals by simulating a bus fault mode through software;
the functional module testing part comprises a PXI case, an adapter and an industrial personal computer software testing module, wherein the adapter is used for connecting a tested unit, and the PXI case comprises an ACE analog electronic testing module, a DCE digital electronic testing module, an avionic bus testing module, a special signal simulation module, an interface and a power supply system.
Each analog channel is configured with multiple independent excitation/measurement instruments: high-speed analog input/output and dynamic waveform editor, dynamic signal simulation analyzer, and high-precision embedded signal analyzer.
Firstly, the equipment mainly comprises a complete machine comprehensive test part and a functional module test part, and the equipment carries out system self-check before being electrified and tests each test board card and each power supply. After the equipment is powered on, the analog electronic testing module, the digital electronic testing module, the avionic bus testing module, the cabinet, the power supply system and the special signal simulation module are sequentially detected according to each calling instruction, and the rewinding fault injection test is carried out, so that the real-time collection of products by the upper computer is realized.
The industrial personal computer is powered on or reset and then guided by a jump instruction to enter a system starting program, when the first synchronization, namely startup synchronization, is successful, then 50 ms task operation synchronization is carried out, and the synchronous waiting time is 50 ms. The software completes the initialization of computer initialization management and redundancy management; if the synchronous signal is not received in the synchronous waiting time, the system delays one beat to start synchronous recovery, and carries out computer power-on BIT test, wherein the time of the synchronous recovery is 51m s and is greater than the minimum monitoring period of 50 ms; and if the synchronization is successfully recovered, entering a 50 ms task and waiting for the next synchronization. If the synchronous recovery also fails, the synchronous permanent fault is recorded, the channel stops outputting, and the dead loop is entered. If synchronization fails again, the dual channels enter synchronization recovery at the same time, and further, conversion test of the functional modules is carried out according to input related signals.
Referring to fig. 2, the overall implementation flow chart of fault injection of the present invention includes the following specific steps: firstly, after the equipment is powered on, an upper computer turns off a certain channel power supply, namely, the channel crystal oscillator is in a non-working state, whether error signals exist in other channel computers or not is checked, if not, function voting output is set to be high level, local variables are initialized, each function of a computer to be tested is executed and tested according to a communication protocol, preset execution times are set, whether the operation of each channel computer is abnormal or not is detected, and when abnormality is found in the execution cycle detection process, a detection value DIA in each hardware module of the computer is set to be high, the abnormality of a corresponding detection point is displayed.
And (4) reserving the computer addresses of the channels where the errors are positioned for the DIA values of the other channels in sequence, voting, and when one fault occurs, continuing working, wherein the voted value is taken as a control instruction to control an execution mechanism.
When the DIA value and other channels are not 1, starting a tracking algorithm in the testing equipment, enabling a built-in synchronous indicator to work, simultaneously collecting input channels of related sensors, carrying out cross transmission on computers of all channels through CCDL, carrying out redundancy management on software, taking a voting value as a control instruction, and controlling the running of a testing system.
The invention discloses a method for testing a flight control computer for controlling stability augmentation, which comprises the following steps:
step 1: the power supply system on the analog machine provides power for three power supplies of the control stability-increasing flight control computer, and can independently control the on-off of the three power supplies to monitor and protect the power supply;
step 2: acquiring an output power supply signal of a control stability augmentation flight control computer;
and 3, step 3: the communication and data cross-linking are carried out with a control stability augmentation flight control computer through an RS422 communication interface;
and 4, step 4: discrete input and output signals of the analog control stability-increasing flight control computer comprise 28V/on signals and 15V ground/on signals;
and 5: simulating HB6096 bus and GJB289A bus signals to complete bus communication and detection with the control stability augmentation flight control computer to be detected;
and 6: completing the simulation of various sensor signals, including the simulation of alternating current sensors such as dynamic and static pressures, sideslip angles, left and right attack angles, angular displacement and the like, and direct current sensors such as acceleration, angular velocity and the like;
and 7: finishing the simulation of various horizontal tail, aileron and rudder steering engine signals, including the simulation of horizontal tail, limit, front fly, flaperon, rudder and other signals;
and step 8: the method can complete the setting of the analog signal of the control stability-increasing flight control computer and can acquire the output of the analog signal of the computer in real time.
The test method completes the test and record of the product to be tested, the input/output management and channel fault logic, the bus receiving/sending test and the CCDL transmission.
The testing method realizes simulation test of the left/right horizontal tail steering engine, the left/right flap aileron steering engine, the direction steering engine, the left/right servo amplification loop, synchronous and signal cross transmission control test among channels, voting and monitoring test of redundancy signals, and system control logic synthesis and control mode conversion test.
Claims (2)
1. A test method for controlling and stabilizing a flight control computer is characterized in that a test system for controlling and stabilizing the flight control computer is adopted, the test system comprises a complete machine comprehensive test platform and a function test module, the test platform is provided with a simulation aircraft bus module and is mainly used for simulating various bus signals cross-linked with the control and stabilizing flight control computer, the bus signals are converted into the bus signals by using GJB289A and ARINC429 bus boards and are sent to the control and stabilizing flight control computer, and the system bus signals are tested by simulating a bus fault mode through software;
the functional module testing part comprises a PXI case, an adapter and an industrial personal computer software testing module, wherein the adapter is used for connecting a tested unit, and the PXI case comprises an ACE analog electronic testing module, a DCE digital electronic testing module, an avionic bus testing module, a special signal simulation module, an interface and a power supply system;
each analog channel is configured with multiple independent excitation/measurement instruments: a high-speed analog input/output and dynamic waveform editor, a dynamic signal simulation analyzer and a high-precision embedded signal analyzer;
the test method of the flight control computer for controlling stability augmentation adopts the following steps:
step 1: the power supply system on the analog plane provides power for three power supplies of the flight control computer for controlling stability augmentation, and can independently control the on-off of the flight control computer to monitor and protect the power supply;
step 2: acquiring an output power supply signal of a control stability augmentation flight control computer;
and step 3: the communication and data cross-linking are carried out with a control stability augmentation flight control computer through an RS422 communication interface;
and 4, step 4: discrete input and output signals of the analog control stability-increasing flight control computer comprise 28V/on signals and 15V ground/on signals;
and 5: simulating HB6096 bus and GJB289A bus signals to complete bus communication and detection with the control stability augmentation flight control computer to be detected;
step 6: completing the simulation of various sensor signals, including the simulation of alternating current sensors such as dynamic and static pressures, sideslip angles, left and right attack angles, angular displacement and the like, and direct current sensors such as acceleration, angular velocity and the like;
and 7: the simulation of various horizontal tail, aileron and rudder steering engine signals is completed, and the simulation of the horizontal tail, limit, front fly, flaperon, rudder and other signals is included;
and 8: the analog signal setting of the control stability-increasing flight control computer can be finished, and the output of the analog signal of the computer can be collected in real time;
completing the test and record of the product to be tested, the input/output management and channel fault logic, the bus receiving/sending test and the CCDL transmission;
the integrated fault injection implementation flow chart of the software simulation bus fault mode comprises the following specific steps: firstly, after equipment is powered on, an upper computer turns off a certain channel power supply, namely, the channel crystal oscillator is in a non-working state, whether error signals exist in other channel computers or not is checked, if the error signals do not exist, function voting output is set to be high level, a local variable is initialized, each function of a computer to be tested is executed and tested according to a communication protocol, preset execution times are set, whether the operation of each channel computer is abnormal or not is detected, when abnormality is found in the execution cycle detection process, a detection value DIA in each hardware module of the computer is set to be high, and the abnormality of a corresponding detection point is displayed;
sequentially reserving the computer addresses of the channels where the errors are located for the DIA values of the rest of channels, voting, and when one fault occurs, continuing working, taking the voting value as a control instruction, and controlling an execution mechanism;
when the DIA value and other channels are not 1, starting a tracking algorithm in the testing equipment, enabling a built-in synchronous indicator to work, simultaneously collecting input channels of related sensors, carrying out cross transmission on computers of all channels through CCDL, carrying out redundancy management on software, taking a voting value as a control instruction, and controlling the running of a testing system.
2. The method as claimed in claim 1, wherein the method for testing the control stability augmentation flight control computer realizes simulation test of a left/right horizontal tail steering engine, a left/right flap aileron steering engine, a directional steering engine, a left/right servo amplification loop, control test of synchronization and signal cross transmission between channels, voting and monitoring test of redundancy signals, and test of system control logic synthesis and control mode conversion.
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| CN112115552B (en) * | 2020-09-16 | 2022-10-25 | 天津津航计算技术研究所 | Airborne flight data recharging method and device |
| CN112346331B (en) * | 2020-11-18 | 2022-11-18 | 西安爱生技术集团公司 | Channel selection method of three-redundancy flight control computer |
| CN112596539B (en) * | 2020-12-04 | 2022-08-23 | 中国航空工业集团公司成都飞机设计研究所 | Differential extraction, construction and synchronization method for flight control stability augmentation controlled variable |
| CN113448784A (en) * | 2021-05-27 | 2021-09-28 | 中国航空工业集团公司沈阳飞机设计研究所 | Computer BIT system and method thereof |
| CN113703419B (en) * | 2021-08-08 | 2024-05-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Automatic testing method and device for redundancy management algorithm of flight control system |
| CN114200909B (en) * | 2021-11-08 | 2024-07-02 | 陕西千山航空电子有限责任公司 | Analog module test platform and test method based on PXI bus |
| CN114348291B (en) * | 2021-12-17 | 2023-10-24 | 国营芜湖机械厂 | Flight fault diagnosis method based on flight parameter data and simulation |
| CN114721358B (en) * | 2022-05-10 | 2022-08-23 | 中国民航大学 | Switching device for ground function test of flight control system |
| CN115755866A (en) * | 2022-12-21 | 2023-03-07 | 杭州牧星科技有限公司 | Unmanned aerial vehicle flies to control computer test system |
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