Amphibious aircraft fire extinguishing task system testing method

Abstract

The invention discloses an amphibious aircraft fire extinguishing task system test method, which is characterized by comprising the steps of S1, test environment establishment: simulating a peripheral sensor signal crosslinked with a fire extinguishing task control subsystem, performing model simulation on a flight stage related to task execution, simulating an electromechanical system signal crosslinked with the flight stage, and establishing a test environment; simulating navigation and fuel oil signals which are cross-linked with the navigation signals and the fuel oil signals; s2, determining a test configuration and a test method based on test items and test purposes of the fire extinguishing task system ground comprehensive test; s3, designing a test case by adopting an MC / DC method; s4, performing a fire extinguishing task system ground comprehensive test according to the environment of S1, the method of S2 and the use case of S3; and S5, analyzing a test result, and compiling a test report. The system verification problem of the forest fire extinguishing special aircraft fire extinguishing task system is solved, and a test implementation scheme is provided for subsequent development and test verification of the type of aircraft task system.

Description

Technical Field

[0001] This invention belongs to the technical field of civil aircraft ground integrated testing and airworthiness verification testing, and relates to a testing method for an amphibious aircraft firefighting mission system, specifically to a research and development and airworthiness testing verification method for a special forest firefighting aircraft firefighting mission system. Background Technology

[0002] Specialized aircraft for forest fire fighting are primarily used for forest fire suppression. They can take off and land using both land and water methods. The fire fighting mission system for this type of aircraft is still under development, and there are still gaps in the relevant testing methods. Summary of the Invention

[0003] The purpose of this invention is to provide a testing method for an amphibious aircraft firefighting mission system. This invention solves the system verification problem of a special aircraft firefighting mission system for forest fires, and provides an experimental implementation scheme for the subsequent development and testing of this type of aircraft mission system.

[0004] Technical solution: A testing method for an amphibious aircraft firefighting mission system, comprising: S1. Test environment setup: Simulate the peripheral sensor signals that are interconnected with the firefighting mission control subsystem, perform model simulation of the flight phase related to mission execution, simulate the electromechanical system signals interconnected with it, and simulate the navigation and fuel signals interconnected with it. S2. Based on the test items and objectives of the ground integrated test of the fire extinguishing mission system, determine the test configuration and test methods; S3. Use the MC / DC (Modified Condition / Decision Coverage) method for test case design; S4. Conduct a comprehensive ground test of the firefighting mission system based on the environment of S1, the method of S2, and the use cases of S3; S5. Analyze the test results and compile a test report.

[0005] In the aforementioned test method for amphibious aircraft firefighting mission systems, the test environment setup in S1 includes the following test equipment components: the firefighting mission control subsystem, the water drop guidance subsystem, and the avionics system.

[0006] In the aforementioned test method for amphibious aircraft firefighting mission systems, the simulation system required for the test environment setup in S1 includes: Firefighting Mission Simulation Test System: This system stimulates the firefighting mission control subsystem; monitors the inputs and outputs of the firefighting mission control subsystem; simulates and stimulates the inputs and outputs of all interfaces, hardwired, and bus signals of the firefighting mission control subsystem; completes interface testing and alarm logic testing between the firefighting mission control subsystem and the agent injection subsystem, firefighting mission structure subsystem, and water injection guidance subsystem; completes cross-linking testing between the firefighting mission control subsystem and the fuel system, navigation system, and avionics system; and verifies the information cross-linking and input / output functions of the firefighting mission control subsystem, as well as conducting MOC4 airworthiness compliance verification tests for alarms. Avionics integration test environment: Simulates the electromechanical system signals that are interconnected with the firefighting mission control subsystem; simulates the avionics system and navigation system signals; and automatically simulates the normal process of the firefighting mission. The simulation results are sent to the firefighting mission control subsystem through the firefighting mission simulation test system to realize dynamic simulation testing of normal water injection and water extraction. Electromechanical signal simulation system: Simulation of analog and discrete quantities of electromechanical systems.

[0007] In the aforementioned test method for amphibious aircraft firefighting mission systems, the test objectives in S2 are: interface verification between the firefighting mission control subsystem and other subsystems within the firefighting mission system (firefighting mission structure subsystem, agent injection subsystem, water drop guidance subsystem, fuselage water drop hatch) and interface verification with external systems (avionics system, electromechanical system); verification of the normal functional performance of the firefighting mission system; verification of the water drop function of the firefighting mission control subsystem under emergency / emergency conditions such as firefighting mission computer failure or aircraft hydraulic power source failure; and verification of the system display, control, and abnormal alarm functions.

[0008] In the aforementioned test methods for amphibious aircraft firefighting mission systems, S2 includes the following test methods: static excitation response test method, dynamic integrated test method, and fault injection test method.

[0009] In the aforementioned test method for amphibious aircraft firefighting mission systems, the fault injection test method in S2 includes: Bus fault injection: The A429 and discrete signals output by the fire extinguishing mission simulation test system are injected with specified messages on the bus under test to achieve preset error injection and emergency simulation. Soft fault injection: Fault logic is built in the avionics integration test environment, and fault message output is realized through simulation. Hardware fault injection: Simulation of a fault where the hardware input is disconnected.

[0010] In the aforementioned test method for amphibious aircraft firefighting mission systems, the alarm test case design method in S3 is as follows: The MC / DC method is used for test coverage. Specifically, each condition must independently affect the decision result; that is, changing the value of this condition while keeping all other conditions unchanged will change the decision result. The test case design employs a rapid design method using a minimal test case set. Details are as follows: a) Design the first test case that directly affects the result for the first condition; b) For each subsequent condition, in the previously designed test cases, select the test case that directly affects the result as the reference object, change the value of the condition, and keep the values ​​of all other conditions unchanged, so that the result is changed. c) Each condition should take all possible values; d) For a case with N independent conditions, and each independent condition has two possible values: 0 and 1, the total number of test cases is N+1.

[0011] In the aforementioned test method for amphibious aircraft firefighting mission systems, section S5 includes the analysis of test results, which includes: 1) Verification of interface tests: The test results should meet the requirements of the signal interface control document of the system to which the interface is cross-linked; 2) The display of the test results, including text size, graphics, font, and color, must be consistent with the pilot operating procedures (POP) requirements of the firefighting mission system and avionics system. 3) The alarm test of the system must conform to the requirements of POP or alarm, including the text, graphic display, light and voice of the alarm, duration, and the equipment fault list must be consistent with the alarm. 4) For combined alarms, higher priority alarms must be able to suppress lower priority alarms; 5) Effective fire extinguishing mission system test coverage and test conclusions must be provided.

[0012] Advantages of this invention: In order to meet the requirements of research and development verification and airworthiness verification tests of aircraft firefighting mission systems, this invention analyzes the usage patterns of amphibious aircraft during forest firefighting, studies an index system that can evaluate the design of this type of aircraft firefighting mission system, establishes a complete set of test environments, requirements, verification methods, test data processing and analysis methods, and test environment construction schemes for ground integrated tests of amphibious aircraft firefighting mission systems, and forms a system that can scientifically evaluate the design and system deficiencies of forest firefighting special aircraft (amphibious aircraft) firefighting mission systems.

[0013] The testing method of this invention enables comprehensive verification testing of the internal systems, interfaces with external systems, control logic, display, and alarm logic of a firefighting mission system. It tests the system's functionality and performance, significantly shortening the system development cycle, reducing flight test risks and system development costs. It also supports multiple rounds of design change verification and proposes a minimum test case set testing method, which can improve the efficiency of airworthiness verification testing, enhance the maturity and safety of newly developed products, accelerate TC certification progress, and thus effectively control system development risks. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the system test of the present invention. Detailed Implementation

[0015] Example 1. A test method for an amphibious aircraft firefighting mission system, see [link to example]. Figure 1 ,include: Step 1: Setting up the test environment required for the firefighting mission system test: Simulate the signals of peripheral sensors that are interconnected with the firefighting mission control subsystem, perform model simulation of the flight phase related to the execution of the firefighting mission system, simulate the signals of the electromechanical system interconnected with the firefighting mission system, and simulate the signals of the navigation system, fuel system, etc. interconnected with the firefighting mission system. Step 2: Determine the test objectives and test items for the ground integrated test of the fire extinguishing mission system, and determine the test configuration and test methods accordingly; Step 3: Design test cases using the MC / DC method; Step 4: Conduct a comprehensive ground test of the fire extinguishing mission system based on the environment of Step 1, the method of Step 2, and the use cases of Step 3. Record the test results using display and control viewing and data monitoring. Step 5: Analyze the test results, prepare a test report, and submit it to the relevant authorities for approval.

[0016] In step 1 above, the environmental requirements are as follows: 1) The fire extinguishing mission system includes: fire extinguishing mission control subsystem, fire extinguishing mission structure subsystem, agent injection subsystem, water injection guidance subsystem, and fuselage water injection hatch; 2) Avionics systems include communication systems, navigation systems, display and control systems, crew alarm systems, flight parameter recording, OMS, and flight control systems; 3) The firefighting mission simulation test system 101 includes a main control computer, operating program, excitation module, acquisition module, signal conditioning module, etc. It is mainly used to simulate the peripheral sensor signals, agent injection subsystem signals, and fuselage water drop door sensor signals of the firefighting mission control subsystem 105. It can excite the main control equipment of the firefighting mission (firefighting mission computer and emergency control box), monitor the input and output of the main control equipment of the firefighting mission, realize the simulation excitation function of the input and output of the full interface and hardwired and bus signals of the main control equipment of the firefighting mission, support the completion of interface testing with subsystems such as agent injection, firefighting mission structure, and water drop guidance, and system alarm logic testing; cross-linking testing with external systems such as fuel, navigation, and avionics; and verify the information cross-linking and input / output functions of the firefighting mission control subsystem and perform alarm MOC4 airworthiness compliance verification test.

[0017] 4) Avionics integration test environment 102, comprising: test control system, integrated simulation system, flight simulation system, integrated wiring system, data acquisition test system, visual system, etc. It can simulate signals from electromechanical systems interconnected with the firefighting mission control subsystem, such as fuel computer and landing gear, as well as avionics and navigation system signals, such as atmospheric speed and radio altitude, and can collect and monitor these signals. Furthermore, the central control console can automatically simulate the normal firefighting mission process and transmit the data via Ethernet to the firefighting mission simulation test system 101, which in turn sends it to the firefighting mission control subsystem 105, enabling dynamic simulation testing of normal water injection, water extraction, etc. 5) Electromechanical signal simulation system 103, mainly realizes the simulation of analog and discrete signals of electromechanical systems, such as hydraulic source signals.

[0018] In step 2 above, the purpose of the test is as follows: to verify the interface with internal systems (such as water injection guidance and chemical injection) to verify the correctness of the system interface; to verify the interface with external systems to verify the correctness of the system interface; to verify the normal functional performance of the system, such as water injection, water sludge collection, chemical injection, various water injection modes (simultaneous injection, continuous injection, and separate injection), and special water injection functions; to verify the water injection function in emergency / emergency situations under fire-fighting mission computer failure or aircraft hydraulic power source failure or aircraft power failure; and to verify the system screen display, control, and abnormal alarm functions.

[0019] In step 2 above, the test items include at least: 1) Interface cross-linking test of fire extinguishing and avionics systems, including verification of internal and external interfaces, verification of normal water injection / drawing procedures, verification of normal water drop procedures in various modes under water-loaded / empty conditions, verification of special water drop functions, verification of chemical cleaning functions, verification of normal chemical injection procedures and injection time performance; verification of abnormal states during water drawing / dropping; verification of conditions under which various working modes cannot be executed, such as water drop not being allowed during the water surface stage.

[0020] 2) Warning-level alarm verification test, including verification of logic, screen and text display, voice, lights, etc.; 3) Alert-level alarm verification test, including verification of logic, screen and text display, voice, lights, etc.; 4) Alarm verification test at the prompt level, including verification of logic, screen and text display; 5) Verification test of combined fault alarms and verification of combined alarm suppression, such as when both warning and alert level floodgate lockout alarms occur simultaneously, the warning level alarm suppresses the alert level alarm, etc.

[0021] In step 2 above, the test configuration is as follows: the fire-fighting mission system avionics test laboratory adopts a semi-physical simulation method, the water drop guidance subsystem 104, the fire-fighting mission control subsystem 105, and the avionics system 106 adopt real airborne equipment, and the remaining peripheral systems and sensors are tested by simulation. In step 2 above, the test method includes at least: 1) Static excitation-response testing method: This method involves interface cross-linking tests with internal systems (chemical injection, water injection, water intake, doors, butterfly valves, control components, etc.), avionics systems (display and control, alarms, flight parameters, OMS, atmosphere, etc.), electromechanical systems (fuel, hydraulics, landing gear, etc.), and system alarm logic verification. For example, the normal / fault status of chemical injection pumps and valves can be simulated to provide excitation to the main control equipment for firefighting missions, so that the response results can be seen on the display screen. 2) Dynamic integrated (semi-automated) testing method: For normal task modes such as water injection, water scooping, chemical injection, and water drop, a dynamic integrated (semi-automated) testing method is adopted. That is, when water drop, the simulation system automatically sends the corresponding water drop cabin door unlocking, scooping, and locking signals within a specified time according to the unlocking (opening), retraction, and locking commands sent by the main control equipment of the fire extinguishing task. Water scooping and chemical injection are similar. 3) Fault Injection Testing Method: When problems occur during onboard ground testing and flight testing, fault injection testing is required for the fire suppression system to support fault reproduction and troubleshooting, as well as to support testing of normal and abnormal aircraft operations. This specifically includes: ① Bus ​​fault injection: For the A429 and discrete signals output by the excitation simulation system, the user can inject a specified message on a certain bus to realize certain error injection and emergency simulation functions, such as agent injection pump / valve failure, water tank door sensor failure, etc. During the test, fault messages can be sent through simulation to realize certain error injection. ② Soft fault injection: Fault logic can be built inside the simulation model and fault message output can be realized through simulation, such as the simulation of alarms such as "unauthorized opening of water drop hatch during land / water takeoff" and "accidental opening of any water drop hatch during landing / water surface stage". For the flight stage, fault logic needs to be built through simulation. ③ Hardware fault injection: Simulation of faults such as disconnection of a real component input, or short circuit to ground of a certain real component input, such as a fault in the main control equipment for fire extinguishing missions. During testing, it can be disconnected.

[0022] In step 3 above, the alarm test cases are designed using the following method: Since the alarm triggering logic consists of combinations of Boolean expressions, the MC / DC method is used for test coverage. Specifically, each condition must independently affect the decision result; that is, changing the value of this condition while keeping all other conditions unchanged will alter the decision result. A rapid design method using a minimal test case set is employed during test case design. Details are as follows: a) Design the first test case that directly affects the result for the first condition; b) For each subsequent condition, in the previously designed test cases, select the test case that directly affects the result as the reference object, change the value of the condition, and keep the values ​​of all other conditions unchanged, so that the result is changed. c) Each condition should take all possible values; d) It should be noted that the minimum set of test cases designed according to the above approach is not unique, because the first value of some conditions is not unique. If there are N independent conditions, and each independent condition has two values ​​(such as 0 and 1), the total number of test cases is N+1.

[0023] Following the above method, if we test the following logic: (A or B) and (C or D), as shown in Table 1: Table 1 Examples of Test Case Design Methods

[0024] In step 2 above, the test verification includes at least the following: the test environment must be intact during each test, the test equipment must be within the calibration validity period, and the test conditions must be carried out under the conditions of room temperature and relative humidity ≤95%. In step 2 above, the ground integrated test should generally include, but is not limited to, the following test specimens: 1) A complete test prototype of a real fire-fighting mission control subsystem includes: system computer, emergency control box, various operation panels, display and control panels, and related cables and connectors; 2) A complete test prototype of a real water drop guidance subsystem includes: guidance display and control board, photoelectric search equipment, etc. 3) A complete avionics system test piece includes, but is not limited to: Integrated Management Assembly (IMA) platform, various display and control panels, alarm light boxes, displays, crew alarm system, flight parameter recorder, audio integration system, OMS, and related cables and connectors; 4) A simulated cockpit consisting of left and right control consoles, a central control console, a seat, and related test components.

[0025] The analysis of the test results in step 5 above shall include at least: 1) Verification of the interface test: The test results meet the requirements of the signal interface control document of the system with which it is interconnected; 2) The display of the test results, including text size, graphics, font, and color, must be consistent with the pilot operating procedures (POP) requirements of the firefighting mission system and avionics system. 3) The alarm test of the system must conform to the requirements of POP or alarm, including the text, graphic display, light and voice of the alarm, duration, etc., and the equipment fault list must be consistent with the alarm. 4) For combined alarms, higher priority alarms must be able to suppress lower priority alarms; 5) Provide effective test coverage and experimental conclusions for fire extinguishing mission systems.

[0026] Example 2. A test method for an amphibious aircraft firefighting mission system, see [link to example]. Figure 1 ,include: Step 1: Setting up the test environment required for the firefighting mission system test: Simulate the signals of peripheral sensors that are interconnected with the firefighting mission control subsystem, perform model simulation of the flight phase of the mission execution, simulate the signals of the electromechanical system interconnected with it, and simulate the signals of navigation, fuel, etc. interconnected with it. Step 2: Determine the test objectives and test items for the ground integrated test of the fire extinguishing mission system, and determine the test configuration and test methods accordingly; Step 3: Design test cases using the MC / DC method; Step 4: Conduct a comprehensive ground test of the fire extinguishing mission system based on the environment of Step 1, the method of Step 2, and the use cases of Step 3. Record the test results using display and control viewing and data monitoring. Step 5: Analyze the test results, prepare a test report, and submit it to the relevant authorities for approval.

[0027] The test environment requirements for step 1 are as follows: 1) The fire extinguishing mission simulation test system 101 includes a main control computer, operating program, excitation module, acquisition module, signal conditioning module, etc. It is mainly used to simulate the peripheral sensor signals of the fire extinguishing mission control subsystem, excite them, monitor the input and output of the fire extinguishing mission computer, realize the simulation excitation function of the input and output of the full interface and hardwired and bus signals of the fire extinguishing mission computer, support the completion of interface tests with subsystems such as agent injection and fire extinguishing mission structure, and system alarm logic tests; and cross-linking tests with external systems such as fuel, navigation, and avionics to verify the information cross-linking and input / output functions of the fire extinguishing mission control subsystem.

[0028] 2) Avionics integration test environment 102, comprising: test control system, integrated simulation system, flight simulation system, integrated wiring system, data acquisition and test system, visual system, etc. It can simulate signals from electromechanical systems interconnected with the firefighting mission control subsystem, such as fuel computer, flap computer, landing gear, etc., and can also simulate avionics and navigation system signals, such as atmospheric speed and radio altitude, and can collect and monitor these signals. Furthermore, the central control console can automatically simulate the normal firefighting mission process and transmit the data via Ethernet to 101, and then to 105, enabling dynamic simulation testing of normal water injection, water extraction, etc. 3) Electromechanical signal simulation system 103, mainly realizes the simulation of analog and discrete signals of electromechanical systems, such as hydraulic source signals; The actual test equipment in step 2 includes: 1) Components of the firefighting task control subsystem (firefighting task computer, emergency control box, etc.); 2) Actual components of the water injection guidance subsystem (photoelectric pod, guidance display and control panel, etc.); 3) Avionics system components include, but are not limited to, display processors, display control operation panels, displays, crew alarm systems, flight parameter records, OMS systems, and integrated processing (IMA) platforms.

[0029] The test items in step 2 include: 1) Signal interface test: Interface cross-connection verification: Used to verify the compliance of the interface requirements within the firefighting mission system and between the firefighting mission system and other systems on the aircraft, and to assess whether the electrical and signal interfaces of the firefighting mission system have met the requirements.

[0030] Functional performance testing includes verification of the normal water injection / drawing process, verification of the normal water injection process under various modes in both loaded and unloaded states, verification of special water injection functions, verification of chemical cleaning functions, verification of the normal chemical injection process and injection time performance; verification of abnormal states during water drawing / injection; and verification of conditions under which various working modes cannot be executed, such as the inability to inject water during the water surface stage. This is used to verify the compliance of the functional and performance requirements of the fire extinguishing task subsystems, subsystems, and the system as a whole. Using bilateral, multilateral, or unilateral methods, dynamic testing methods are employed to obtain the expected functional responses (response methods include: human-machine interface response, data forwarding response, redundancy selection response, control / guidance response, POP, and alarms) as the criterion to evaluate whether the functional performance design goals of the fire extinguishing task system have been achieved.

[0031] 2) Warning-level alarm verification test, including verification of logic, screen and text display, voice, lights, etc.; 3) Alert-level alarm verification test, including verification of logic, screen and text display, voice, lights, etc.; 4) Alarm verification test at the prompt level, including verification of logic, screen and text display; 5) Verification test of combined fault alarms and verification of combined alarm suppression, such as when both warning and alert level floodgate lockout alarms occur simultaneously, the warning level alarm suppresses the alert level alarm, etc.

[0032] The analysis of the test results in step 5 above shall include at least: 1) Verification of interface tests: The test results meet the electrical and signal interface requirements of the interconnected system; 2) The display of the test results, including text size, graphics, font, and color, must be consistent with the pilot operating procedures (POP) requirements of the firefighting mission system and avionics system. 3) The alarm test of the system must conform to the requirements of POP or unit alarm, including the text, color display, light and voice of the alarm, and the equipment fault list must be consistent with the alarm. 4) For combined alarms, higher priority alarms must be able to suppress lower priority alarms; 5) Provide effective test coverage and experimental conclusions for fire extinguishing mission systems.

[0033] Example 3. A test method for an amphibious aircraft firefighting mission system, see [link to example]. Figure 1 ,include: Step 1: Set up the test environment required for the fire-fighting mission system test, including the dynamic excitation simulation system for the fire-fighting control system, the avionics integration test environment, and the electromechanical signal simulation system; Step 2: Develop a dynamic test program for the firefighting mission system in the avionics integration test environment, and debug its test network with the dynamic excitation simulation system of the firefighting control system; Step 3: Confirm the hardware interface relationship of the device / system under test; complete the test cables for the dynamic excitation simulation system of the fire extinguishing control system and the fire extinguishing mission control system, the test cables for the water injection guidance system and the fire extinguishing mission control subsystem, and the test cables for the fire extinguishing mission control system, the water injection guidance system and the avionics system. Step 4: Perform continuity, voltage, and grounding tests on the test piece plug / socket to the test environment and other avionics system equipment; Step 5: Connect the test specimen to the test environment and conduct the test according to the requirements of the test outline; Step 6: Record the test results observed or monitored. If any abnormalities or malfunctions are encountered, the fault location should be identified, and solutions should be analyzed and eliminated. Step 7: Analyze the test data, obtain the test results, compile the test report, and give the test conclusions; For problems that arise during flight tests, the relevant equipment of the fire extinguishing mission system can be reproduced in the laboratory to locate the faults. The faults can be eliminated or the discovered design errors and defects can be resolved through measures such as software upgrades.

[0034] The above-described embodiments merely illustrate the implementation methods of the present invention, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements all fall within the protection scope of the present invention.

Claims

1. A testing method for an amphibious aircraft firefighting mission system, characterized in that, include: S1. Test environment setup: Simulate the peripheral sensor signals that are interconnected with the firefighting mission control subsystem, perform model simulation of the flight phase related to mission execution, simulate the electromechanical system signals interconnected with it, and simulate the navigation and fuel signals interconnected with it. S2. Based on the test items and objectives of the ground integrated test of the fire extinguishing mission system, determine the test configuration and test methods; S3. Use the MC / DC method to design test cases; S4. Conduct a comprehensive ground test of the firefighting mission system based on the environment of S1, the method of S2, and the use cases of S3; S5. Analyze the test results and compile a test report.

2. The testing method for an amphibious aircraft firefighting mission system according to claim 1, characterized in that, In the test environment setup in S1, the test equipment components required for the test include: the fire extinguishing mission control subsystem (105) and the water drop guidance subsystem (104) in the fire extinguishing mission system, as well as the avionics system (106).

3. The testing method for an amphibious aircraft firefighting mission system according to claim 1, characterized in that, In setting up the test environment in S1, the simulation system required for the test includes: Firefighting mission simulation test system (101): Excites the firefighting mission control subsystem (105); monitors the input and output of the firefighting mission control subsystem (105); simulates and excites the input and output of all interfaces, hardwired and bus signals of the firefighting mission control subsystem (105); completes the interface test and alarm logic test between the firefighting mission control subsystem (105) and the agent injection subsystem, the firefighting mission structure subsystem, and the water injection guidance subsystem (104); completes the cross-link test between the firefighting mission control subsystem (105) and the fuel system, navigation system, and avionics system (106); verifies the information cross-link and input / output functions of the firefighting mission control subsystem (105) and performs the alarm MOC4 airworthiness compliance verification test; Avionics integration test environment (102): Simulates the electromechanical system signals that are interconnected with the fire-fighting mission control subsystem (105); simulates the avionics system and navigation system signals; automatically simulates the normal process of the fire-fighting mission, and sends the simulation results to the fire-fighting mission control subsystem (105) through the fire-fighting mission simulation test system (101) to realize the dynamic simulation test of normal water injection and water extraction; Electromechanical signal simulation system (103): Simulation of analog and discrete quantities of electromechanical systems.

4. The test method for an amphibious aircraft firefighting mission system according to claim 1, characterized in that, In S2, the test objectives are: interface verification between the fire extinguishing task control subsystem (105) and other subsystems within the fire extinguishing task system, as well as interface verification with external systems; normal function performance verification of the fire extinguishing task system; water injection function verification of the fire extinguishing task control subsystem (105) under fire extinguishing task computer failure or emergency situations such as aircraft hydraulic power source failure or aircraft power failure; and verification of system screen display, control, and abnormal alarm functions.

5. The test method for an amphibious aircraft firefighting mission system according to claim 1, characterized in that, In S2, the test methods include: static stimulus response test method, dynamic integrated test method, and fault injection test method.

6. The test method for an amphibious aircraft firefighting mission system according to claim 1, characterized in that, In S2, the fault injection test methods include: Bus fault injection: The A429 and discrete signals output by the fire extinguishing mission simulation test system are injected with specified messages on the bus under test to achieve preset error injection and emergency simulation. Soft fault injection: Fault logic is built in the avionics integration test environment (102), and fault message output is realized through simulation. Hardware fault injection: Simulation of a fault where the hardware input is disconnected.

7. The test method for an amphibious aircraft firefighting mission system according to claim 1, characterized in that, In S3, the alarm test case design method is as follows: Test coverage is achieved using the MC / DC method, specifically requiring that each condition independently affects the decision result; that is, changing the value of this condition while keeping all other conditions unchanged will alter the decision result. The test case design employs a rapid design method using a minimal test case set. Details are as follows: a) Design the first test case that directly affects the result for the first condition; b) For each subsequent condition, in the previously designed test cases, select the test case that directly affects the result as the reference object, change the value of the condition, and keep the values ​​of all other conditions unchanged, so that the result is changed. c) Each condition should take all possible values; d) For a case with N independent conditions, and each independent condition has two possible values: 0 and 1, the total number of test cases is N+1.

8. The test method for an amphibious aircraft firefighting mission system according to claim 1, characterized in that, In S5, the analysis of experimental results includes: 1) Verification of interface tests: The test results should meet the requirements of the signal interface control document of the system to which the interface is cross-linked; 2) The display of the test results, including text size, graphics, font, and color, must be consistent with the pilot operating procedures (POP) requirements of the firefighting mission system and avionics system. 3) The alarm test of the system must conform to the requirements of POP or alarm, including the text, graphic display, light and voice of the alarm, duration, and the equipment fault list must be consistent with the alarm. 4) For combined alarms, higher priority alarms must be able to suppress lower priority alarms; 5) Effective fire extinguishing mission system test coverage and test conclusions must be provided.

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