Auxiliary method and auxiliary system for automatic test run of aero-engine

Abstract

The invention discloses an auxiliary method and an auxiliary system for automatic test run of an aero-engine. The method comprises the following steps: constructing a test run program table based on a data acquisition system of an aero-engine; in response to a selection operation of a user, calling a target test run program table corresponding to the selection operation to start execution; reading state items in the target test run program table in sequence, setting software and hardware participating in the test run of the aero-engine according to the corresponding test run state attributes, and acquiring test run data according to the corresponding data acquisition attributes for interpretation; and in response to the fact that the target test run program table is executed completely and is judged to be qualified, generating a test run report according to the test run data of each state item. According to the invention, the efficiency in the test run process of the aero-engine can be improved, errors caused by manual operation are reduced, and the working intensity is reduced.

Description

Technical Field

[0001] This invention relates to the field of aero-engine testing technology, and in particular to an auxiliary method and system for automatic aero-engine testing. Background Technology

[0002] With the development of the aviation industry, aircraft engine testing has become an indispensable part of aircraft production. It is a crucial step in verifying the performance, reliability, and safety of aircraft engines. During engine testing, the engine's operating state needs to be frequently and precisely changed, while simultaneously conducting extensive data acquisition, load control, and video monitoring.

[0003] Currently, existing engine test process control has the following drawbacks: First, the test state switching is frequent, the workload is high, and it is difficult to avoid errors introduced by manual operation; second, there is a lack of overall consideration of various factors such as the timeliness, accuracy, and safety of engine testing, and there is a lack of optimization of the connection and coordination of various operation links, resulting in a long overall test process. Summary of the Invention

[0004] In view of this, embodiments of the present invention provide an auxiliary method and system for automatic test firing of aero engines, with the aim of assisting in aero engine test firing and solving problems such as low efficiency, numerous errors, and high workload in existing aero engine test firing processes.

[0005] To achieve the above objectives, according to a first aspect of the present invention, an auxiliary method for automatic test firing of an aircraft engine is provided, comprising:

[0006] A test procedure table is constructed based on the data acquisition system of the aero-engine. Each state item in the test procedure table includes predefined test state attributes and data acquisition attributes.

[0007] In response to the user's selected operation, the target test program table corresponding to the selected operation is retrieved and execution begins;

[0008] The status items in the target test procedure table are read sequentially, the software and hardware participating in the aero-engine test are set according to the corresponding test status attributes, and the test data is collected and interpreted according to the corresponding data acquisition attributes.

[0009] In response to the completion and qualified reading of the status item, a test report is generated based on the test data of the status item.

[0010] Furthermore, the status items include self-test status items, transitional status items, and stable status items;

[0011] The status items in the target test procedure table are read sequentially, and the hardware and software participating in the aero-engine test are set according to the corresponding test status attributes. Test data is collected and interpreted according to the corresponding data acquisition attributes, including:

[0012] The self-test status item is read, and the hardware and software participating in the aero-engine test are configured according to the test status attribute corresponding to the self-test status item. A first test dataset is collected according to the corresponding data acquisition attribute and a first interpretation is performed.

[0013] In response to the first reading being passed, the transition state item is read, the software and hardware participating in the aero-engine test are set according to the test state attribute corresponding to the transition state item, and the test dataset is collected according to the corresponding data acquisition attribute and a second reading is performed.

[0014] In response to the second reading being passed, the stable state item is read, the software and hardware participating in the aero-engine test are set according to the test state attribute corresponding to the stable state item, and the third test dataset is collected according to the corresponding data acquisition attribute and the third reading is performed.

[0015] In response to the third successful judgment, the first test dataset, the second test dataset, and the third test dataset are stored.

[0016] Furthermore, the status item also includes a test report standard text, which includes a first type of text and a second type of text. The first type of text is plain text, and the second type of text includes mapping variables.

[0017] Furthermore, in response to the completion and qualification of the status item, a test report is generated based on the test data of the status item, including:

[0018] In response to the completion of the target test run program table and its passing the test, the test data in the first test run dataset, the second test run dataset, and the third test run dataset are inserted into the second type of text according to the preset correspondence between the test run data and the mapping variable.

[0019] The first type of text and the second type of text of each of the aforementioned status items are merged to generate the test report.

[0020] Furthermore, the hardware includes an alarm switch, an ignition switch, a valve switch, and a throttle lever; the software includes control programs for the alarm switch, the ignition switch, and the valve switch; the test drive status attributes include a status name, a status identifier, a status duration, and a status command; the data acquisition attributes include the acquisition parameter vector and the acquisition parameter range vector of the hardware and software; and the status commands include control commands from the control program and control commands from the throttle lever.

[0021] Furthermore, the hardware also includes a video acquisition device, and the status command also includes a video acquisition command from the video acquisition device; the method further includes:

[0022] Collect and interpret the test video of the aircraft engine test according to the video acquisition command in the status item;

[0023] In response to the detection of flames, smoke, or people in the test video, an early warning signal is generated and a predefined safety operation is triggered, and the corresponding test video is stored.

[0024] According to a second aspect of the present invention, an auxiliary system for automatic test firing of an aircraft engine is provided, comprising:

[0025] A construction module is used to build a test procedure table based on the data acquisition system of an aero-engine. Each status item in the test procedure table includes predefined test status attributes and data acquisition attributes.

[0026] The selected module is used to respond to the user's selected operation by retrieving the target test program table corresponding to the selected operation and starting execution;

[0027] The execution module is used to sequentially read the status items in the target test program table, set the software and hardware participating in the aero-engine test according to the corresponding test status attributes, and collect and interpret test data according to the corresponding data acquisition attributes.

[0028] The generation module is used to generate a test report based on the test data of the status item in response to the completion of the status item and the determination that it is qualified.

[0029] According to a third aspect of the present invention, a computer-readable storage medium is provided having a program stored thereon that, when executed by a processor, implements the steps of the auxiliary method for automatic test firing of an aero-engine as described in the first aspect of the present invention.

[0030] According to a fourth aspect of the present invention, a terminal device is provided, including a memory, a processor, and a program stored in the memory and executable on the processor, wherein the processor executes the program to implement the steps in the auxiliary method for automatic test firing of an aero-engine as described in the first aspect of the present invention.

[0031] According to a fifth aspect of the present invention, a computer program product is provided, comprising a computer program that, when executed by a processor, implements the steps in the auxiliary method for automatic test firing of an aero-engine as described in the first aspect of the present invention.

[0032] The embodiments of the present invention have at least one of the following advantages or beneficial effects:

[0033] This invention integrates traditionally manual processes such as test self-inspection, status setting, status switching, data acquisition, and report generation into a seamless automated process by constructing a predefined test procedure table for automatic execution. This greatly reduces the workload of operators and avoids inefficiencies and inconsistencies caused by human delays, negligence, or skill differences. It achieves full-process automation and intelligence, significantly improving test efficiency and reliability.

[0034] This invention decomposes the test process into multiple state items such as self-check, transition, and steady state, and predefines complete test state attributes and data acquisition attributes for each state item. This structured design, through the refined design of "state items", ensures the standardization of the test process and the integrity of the data.

[0035] This invention solves the problems of low efficiency and error-proneness in traditional manual report writing by setting a standard report text containing mapping variables and automatically filling the template with the collected test data after the test run, thereby improving the automation and efficiency of test run report generation.

[0036] The system of this invention integrates the control commands of key hardware such as alarm switch, ignition switch, valve switch and throttle lever into the status attribute, and constructs a hardware and software collaborative control system. This realizes the accurate driving of hardware actions by software commands. This centralized and unified control mode ensures that various equipment involved in the aero-engine test can respond quickly and synchronously when the status changes, and improves the accuracy, timeliness and stability of the switching transition.

[0037] This invention also constructs an automatic safety defense line by pre-setting acquisition commands for video acquisition equipment and performing real-time judgment of flames, smoke, and personnel intrusion. Once a risk is identified, the system can immediately trigger predefined safety operations (such as alarms and shutdown), thereby improving the safety of aero-engine testing.

[0038] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages may become apparent from the description or be learned by practicing the invention. The objects and other advantages of this invention can be realized and obtained through the details specifically pointed out in the description and drawings. Attached Figure Description

[0039] The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0040] Figure 1 This is a schematic diagram of the main flow of the auxiliary method for automatic test firing of an aero-engine according to an embodiment of the present invention;

[0041] Figure 2 This is a schematic diagram of the main flow of an auxiliary method for automatic test firing of an aircraft engine according to another embodiment of the present invention.

[0042] Figure 3 This is a schematic diagram of the main modules of the auxiliary system for automatic test firing of an aero-engine according to an embodiment of the present invention;

[0043] Figure 4 This is a schematic diagram of the composition of a terminal device according to an embodiment of the present invention. Detailed Implementation

[0044] Preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which form part of this application and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0045] Example 1

[0046] Figure 1 This is a schematic diagram of the main flow of an auxiliary method for automatic test firing of an aircraft engine according to an embodiment of the present invention, as shown below. Figure 1 As shown, the auxiliary method for automatic test running of an aircraft engine in this embodiment of the present invention includes the following steps S101 to S104.

[0047] Step S101: Construct a test procedure table based on the data acquisition system of the aero-engine. Each state item in the test procedure table includes predefined test state attributes and data acquisition attributes.

[0048] Step S102: In response to the user's selected operation, the target test program table corresponding to the selected operation is retrieved and execution begins;

[0049] Step S103: Read the status items in the target test procedure table in sequence, set the software and hardware participating in the aero-engine test according to the corresponding test status attributes, and collect test data according to the corresponding data acquisition attributes for interpretation.

[0050] Step S104: In response to the completion and qualified reading of the status item, a test report is generated based on the test data of the status item.

[0051] Understandably, aircraft engine testing requires the use of a data acquisition system to collect test data sent from aircraft engine valves, PLC controllers, ESCs, flight controllers, etc. During the test, this embodiment and some embodiments of the present invention can construct a test procedure table based on the attributes of these data, which on the one hand allows for centralized management of the data, and on the other hand facilitates automatic execution during the test.

[0052] Understandably, in this embodiment and some embodiments of the present invention, the test run program table can be constructed according to different test run items and objectives, so that users can select it as needed. Specifically, in this embodiment and some embodiments of the present invention, a human-machine interface is provided, from which users can select a target, i.e., the target test run program table, from the various test run program table options provided by the human-machine interface. In response to the user's selection operation, the machine or program calls up the target test run program table corresponding to the selected operation and begins execution, i.e., executes step S102.

[0053] Specifically, in this embodiment and some embodiments of the present invention, based on the test run process, the status items include self-check status items, transition status items, and stable status items, so as to predefine complete test run status attributes and data acquisition attributes, ensuring the standardization of the test run process and the integrity of the data. Therefore, more specifically, step S103 includes steps S103a to S103d.

[0054] Step S103a: Read the self-test status item, configure the hardware and software participating in the aero-engine test according to the test status attribute corresponding to the self-test status item, and collect the first test dataset according to the corresponding data acquisition attribute and perform the first interpretation. It is understood that the terms "first" and "second" are used for illustrative purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Features defined by "first" and "second" in this invention may explicitly or implicitly include at least one of those features.

[0055] Step S103b: In response to the first reading being passed, the transition state item is read, the software and hardware participating in the aero-engine test are set according to the test state attribute corresponding to the transition state item, and the test dataset is collected secondarily according to the corresponding data acquisition attribute and a second reading is performed.

[0056] Step S103c: In response to the second judgment passing, read the stable state item, set the software and hardware participating in the aero-engine test according to the test state attribute corresponding to the stable state item, and collect the third test dataset according to the corresponding data acquisition attribute and perform the third judgment.

[0057] In step S103d, in response to the third reading being passed, the first test dataset, the second test dataset, and the third test dataset are stored.

[0058] Specifically, in this embodiment and some embodiments of the present invention, the status item further includes a test report standard text, which includes a first type of text and a second type of text. The first type of text is plain text, and the second type of text includes mapping variables. Therefore, specifically, step S104 includes steps S104a and S104b.

[0059] Step S104a: In response to the completion and passing of the target test run procedure table, according to the preset correspondence between the test run data and the mapping variables, the test run data from the first test run dataset, the second test run dataset, and the third test run dataset are inserted into the second type of text. For example, the second type of text has a preset $ symbol to replace the content, such as '$Channel.PLA$', which refers to channel data and throttle lever angle, and the corresponding test run data needs to be filled in.

[0060] Step S104b: Merge the first type of text and the second type of text of each of the status items to generate the test report.

[0061] Furthermore, in this embodiment and some embodiments of the present invention, the hardware includes an alarm switch, an ignition switch, a valve switch, and a throttle lever; the software includes control programs for the alarm switch, the ignition switch, and the valve switch; the test drive status attributes include a status name, a status identifier, a status duration, and a status command; the data acquisition attributes include the acquisition parameter vector and the acquisition parameter range vector of the hardware and software; the status commands include control commands from the control program and control commands from the throttle lever.

[0062] Furthermore, in this embodiment and some embodiments of the present invention, the hardware further includes a video acquisition device, and the status command further includes a video acquisition command of the video acquisition device; the method further includes steps S105a and S105b: acquiring and interpreting the test video of the aero-engine according to the video acquisition command in the status item; in response to the determination that there is flame, smoke or people in the test video, generating a warning signal and triggering a predefined safety operation, and storing the corresponding test video.

[0063] It is understandable that aircraft engine testing includes multiple steps. In one case, the step includes a self-check state, a transition state, and a stable state after switching. In other cases, the step only needs to include the transition state and the stable state. In addition, each step can also generate test results independently. Therefore, in other embodiments of the present invention, the steps of the embodiments of the present invention are adjusted and / or executed cyclically according to the state items of each step and the needs of test report generation.

[0064] Example 2

[0065] This embodiment provides a detailed description of another specific implementation of the auxiliary method for automatic test firing of aero-engines according to the present invention.

[0066] Specifically, in this embodiment and some embodiments of the present invention, the steps of the aero-engine test run include pre-test inspection, dummy start-up, cold run, start-up, slow run, and shutdown.

[0067] Specifically, in this embodiment and some embodiments of the present invention, the test procedure table is constructed based on the data acquisition system of the aero-engine, and its status items include predefined test status attributes and data acquisition attributes. Specifically, the data acquisition attributes include test data items sent from acquisition systems such as LXI, scan valve, DewSoft, ESC, and flight control.

[0068] Specifically, the status data acquisition attributes include the data values ​​and value ranges corresponding to the status items, the acceptable value range, and, based on the embedded Lua scripting language, the acquired data is interpreted using calculation and judgment logic within the acceptable value range. In this embodiment and some embodiments of the present invention, the acquired data includes more than 800 test parameters such as throttle lever angle, low-pressure speed, high-pressure speed, oil pressure from the oil depot, thrust, inlet total pressure, cross-sectional wall static pressure, T495 temperature, low-pressure turbine rear total temperature, lubricating oil level, engine status words, and inspection faults (switch type).

[0069] Specifically, in this embodiment and some embodiments of the present invention, the test run program table includes a self-test status item. The command attributes of the self-test status item include self-test control commands for each alarm switch, ignition switch, and valve switch, as well as the self-test control command for the throttle lever. It also includes a video acquisition command, and the data acquisition data includes the data set to be acquired during the self-test. The self-test can perform a self-check on the test run parameters before the test run, ensuring that the test run parameters are all within the normal range. It also ensures through video inspection that there are no personnel, smoke, flames, or other such conditions in the test run room (the identification results are encoded to form the original data acquisition channel).

[0070] Figure 2 This is a schematic diagram of the main flow of an auxiliary method for automatic test firing of an aircraft engine according to another embodiment of the present invention. Figure 2As shown, the auxiliary method for automatic test running of an aircraft engine in this embodiment of the present invention includes the following steps S201 to S203.

[0071] Step S201: In response to the user's selected operation, retrieve the target test program table corresponding to the selected operation.

[0072] Step S202: Perform the self-test status items according to the test procedure table, collect the self-test status dataset, and conduct a video inspection of the aero-engine test site environment. If the inspection passes, proceed to the next step; otherwise, troubleshoot the problem to ensure that there are no safety hazards in the test procedure table itself and the test site environment.

[0073] Step S203: Read the transition state item, set the software and hardware participating in the aero-engine test according to the test state attribute corresponding to the transition state item, and collect the test dataset according to the corresponding data acquisition attribute and interpret it.

[0074] Step S204: Read the stable state item, set the software and hardware participating in the aero-engine test according to the test state attribute corresponding to the stable state item, and collect the test dataset according to the corresponding data acquisition attribute and judge it. If the judgment is unqualified, proceed to step 205; otherwise, proceed to step S206.

[0075] Step S205: If the reading is unqualified, a pop-up information box will appear for the user to manually interpret. If the user ignores the message, proceed to step S206. Otherwise, maintain the aircraft engine test status for troubleshooting.

[0076] Step 206: In response to the current step's status item being deemed qualified, according to the preset correspondence between the test data and the mapping variable, the corresponding data from the self-test status dataset, the transition state dataset, and the stable state dataset are inserted into each of the second-type texts.

[0077] Step S207: Determine whether the current step is the end step. If so, output the test record sheet composed of the test texts of each generated step. Otherwise, return to step S203 to continue execution.

[0078] For details, see Figure 2 In this embodiment and some embodiments of the present invention, the automatic switching of software-level test drive status includes:

[0079] (1.1) After entering the test drive state, write the hardware control commands that need to be linked (control command groups for throttle lever, alarm switch, ignition switch and valve switch, video command group, etc.);

[0080] (1.2) Entering the transition state stage, the transition state data group is interpreted and passed (indicating that the adjustment of each linkage hardware is completed, and the values ​​meet the interpretation and storage of the transition state data group).

[0081] (1.3) Upon entering the steady state phase, timing begins;

[0082] (1.4) After the steady-state dwell time is satisfied, the steady-state data acquisition group is collected, interpreted, and stored. The test combination text is stored. After all three conditions are met, the next test state is switched.

[0083] For details, see Figure 2 In this embodiment and some embodiments of the present invention, for the hardware linkage control modules (including the throttle lever control module, the alarm switch, the ignition switch and valve switch control modules, and the video control module), each hardware component executes in a multi-threaded mode, with each thread basically divided into three stages:

[0084] (2.1) Stage 1: Read the linkage hardware control commands (throttle lever command group, PLC command group, and video movement strategy attributes in the current state);

[0085] (2.2) Stage 2: Issue control commands (the control modules of the throttle lever control module, video control module, alarm switch, ignition switch and valve switch call their respective control interfaces);

[0086] (2.3) Stage 3: Maintain the current state;

[0087] (2.4) After switching the test run status, the software-level test run status automatic switching function is written into the control command and set to enter stage 1, thereby achieving the function of automatic control.

[0088] For details, see Figure 2 In this embodiment and some embodiments of the present invention, for the throttle lever control module, the automatic switching of the hardware-level test drive state includes:

[0089] (3.1) A resolver simulation card is used to simulate resolver signals and replace the original physical throttle lever for software control;

[0090] (3.2) It can send a corresponding resolver signal according to the input throttle lever angle to change the throttle angle;

[0091] (3.3) The static numerical values ​​between the resolver angle and the throttle lever angle are recorded using feedback from the engine electronic controller. In practice, linear interpolation is used for calculation.

[0092] (3.4) When switching between test run and test run states, the following procedure shall be followed:

[0093] (3.4.1) Stage 1: Read the attributes of the test drive status, throttle lever angle (located in the throttle lever command group), and enter Stage 2;

[0094] (3.4.2) Stage 2: Call the control interface, input the throttle lever angle, change the resolver signal, and enter Stage 3;

[0095] (3.4.3) Stage 3: Maintain the current state.

[0096] (3.5) Limit value setting: The maximum and minimum values ​​of the input throttle lever angle are limited to prevent exceeding the limit.

[0097] Specifically, in this embodiment and some embodiments of the present invention, for the video control module, automatic video surveillance scanning includes:

[0098] (4.1) Cameras equipped with PTZ control all have an external interface to change the monitoring area and can directly issue commands to the camera;

[0099] (4.2) The scanning paths of different cameras are pre-recorded and numbered. Multiple path numbers are combined to form a control strategy, which is then configured for different test states.

[0100] (4.3) When switching test drive states, the configured strategy is invoked to control each camera involved individually, including:

[0101] (4.3.1) Phase 1: Read the video control strategy configured for the test run status and proceed to Phase 2;

[0102] (4.3.2) Stage 2: Call the pan-tilt control interface corresponding to each camera one by one, move according to the set scanning route, and enter Stage 3;

[0103] (4.3.3) Stage 3: Maintain the current state.

[0104] (4.4) Image recognition function, which can identify images in the monitored area, identify people, smoke and flames, and ensure that there are no staff in the monitored area and that the environment is safe;

[0105] (4.4) The images of flames, smoke and people that are identified are encoded to form test parameters and introduced into the data acquisition system to form a data channel.

[0106] For details, see Figure 2 In this embodiment and some embodiments of the present invention, the automatic control of the alarm switch, ignition switch, and valve switch includes:

[0107] (5.1) Hardware such as alarm switch, ignition switch and valve switch can be controlled by their respective control modules, and can be loaded to a specified value of voltage, a specified value of flow, and a switch type position;

[0108] (5.2) Add data blocks inside the control modules of the alarm switch, ignition switch and valve switch to store the corresponding status commands written;

[0109] (5.3) When switching between test drive and test run states,

[0110] (5.3.1) Stage 1: Read the control commands from the test run status configuration table and proceed to Stage 2;

[0111] (5.3.2) In stage 2, the data acquisition software writes the new command into the data block of the control module and enters stage 3;

[0112] (5.3.3) Stage 3, maintain the current state.

[0113] (5.4) Add program blocks inside the control modules of alarm switch, ignition switch and valve switch, and trigger execution according to the change of data block flag bit data to control alarm switch, ignition switch and valve switch to specified value (or position).

[0114] Those skilled in the art will understand that all or part of the processes of the methods described in the above embodiments can be implemented by a computer program instructing related hardware, and the program can be stored in a computer-readable storage medium.

[0115] Example 3

[0116] Figure 3 This is a schematic diagram of the constituent modules of an auxiliary system for automatic test firing of an aircraft engine according to an embodiment of the present invention. Figure 3 As shown, the collaborative spectrum sensing system based on a deep convolutional neural network in this embodiment of the present invention includes:

[0117] A construction module is used to build a test procedure table based on the data acquisition system of an aero-engine. Each status item in the test procedure table includes predefined test status attributes and data acquisition attributes.

[0118] The selected module is used to respond to the user's selected operation by retrieving the target test program table corresponding to the selected operation and starting execution;

[0119] The execution module is used to sequentially read the status items in the target test program table, set the software and hardware participating in the aero-engine test according to the corresponding test status attributes, and collect and interpret test data according to the corresponding data acquisition attributes.

[0120] The generation module is used to generate a test report based on the test data of the status item in response to the completion of the status item and the determination that it is qualified.

[0121] Example 4

[0122] like Figure 4 As shown, Embodiment 3 of the present invention provides a terminal device, including at least one processor and a memory communicatively connected to the at least one processor; wherein, the memory stores instructions executable by the at least one processor, the instructions being executed by the at least one processor to enable the at least one processor to perform the steps in the cooperative spectrum sensing method based on deep convolutional neural networks as described in the first aspect of the present invention.

[0123] The memory and processor are connected via a bus, which can include any number of interconnecting buses and bridges, connecting various circuits of one or more processors and memories. The bus can also connect various other circuits, such as peripherals, voltage regulators, and power management circuits, via interfaces, as is well known in the art. Interfaces provide a connection between the bus and the transceiver, such as communication interfaces or user interfaces. The transceiver can be a single component or multiple components, such as multiple receivers and transmitters, providing a unit for communicating with various other systems over a transmission medium. Data processed by the processor is transmitted over the wireless medium via an antenna, which further receives data and transmits it to the processor.

[0124] The processor manages the bus and general processing, and also provides various functions, including timing, peripheral interfaces, voltage regulation, power management, and other control functions. Memory is used to store data used by the processor during operation.

[0125] Example 5

[0126] Embodiment 5 of the present invention provides a computer-readable storage medium having a program stored thereon, which, when executed by a processor, implements the steps in the auxiliary method for automatic test firing of an aero-engine as described in the first aspect of the present invention.

[0127] Those skilled in the art will understand from the foregoing description that all or part of the steps in the methods of the above embodiments can be implemented by a program instructing related hardware. This program is stored in a storage medium and includes several instructions to cause a device (which may be a microcontroller, chip, etc.) or processor to execute all or part of the steps of the methods described in the various embodiments of this application. The aforementioned storage medium includes, but is not limited to, various media capable of storing program code, such as USB flash drives, portable hard drives, magnetic storage devices, and optical storage devices.

[0128] Example 6

[0129] Embodiment 6 of the present invention provides a computer program product, including a computer program that, when executed by a processor, implements the steps in the auxiliary method for automatic test firing of an aero-engine as described in the first aspect of the present invention.

[0130] Based on the detailed description of the embodiments of the present invention above, it can be more clearly understood that the present invention has the following advantages:

[0131] This invention integrates traditionally manual processes such as test self-inspection, status setting, status switching, data acquisition, and report generation into a seamless automated process by constructing a predefined test procedure table for automatic execution. This greatly reduces the workload of operators and avoids inefficiencies and inconsistencies caused by human delays, negligence, or skill differences. It achieves full-process automation and intelligence, significantly improving test efficiency and reliability.

[0132] This invention decomposes the test process into multiple state items such as self-check, transition, and steady state, and predefines complete test state attributes and data acquisition attributes for each state item. This structured design, through the refined design of "state items", ensures the standardization of the test process and the integrity of the data.

[0133] This invention solves the problems of low efficiency and error-proneness in traditional manual report writing by setting a standard report text containing mapping variables and automatically filling the template with the collected test data after the test run, thereby improving the automation and efficiency of test run report generation.

[0134] The system of this invention integrates the control commands of key hardware such as alarm switch, ignition switch, valve switch and throttle lever into the status attribute, and constructs a hardware and software collaborative control system. This realizes the accurate driving of hardware actions by software commands. This centralized and unified control mode ensures that various equipment involved in the aero-engine test can respond quickly and synchronously when the status changes, and improves the accuracy, timeliness and stability of the switching transition.

[0135] This invention also constructs an automatic safety defense line by pre-setting acquisition commands for video acquisition equipment and performing real-time judgment of flames, smoke, and personnel intrusion. Once a risk is identified, the system can immediately trigger predefined safety operations (such as alarms and shutdown), thereby improving the safety of aero-engine testing.

[0136] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. An auxiliary method for automatic test firing of an aircraft engine, characterized in that, include: A test procedure table is constructed based on the data acquisition system of the aero-engine. Each state item in the test procedure table includes predefined test state attributes and data acquisition attributes. In response to the user's selected operation, the target test program table corresponding to the selected operation is retrieved and execution begins; The status items in the target test procedure table are read sequentially, the software and hardware participating in the aero-engine test are set according to the corresponding test status attributes, and the test data is collected and interpreted according to the corresponding data acquisition attributes. In response to the completion and qualified reading of the status item, a test report is generated based on the test data of the status item.

2. The method according to claim 1, characterized in that, The status items include self-test status items, transitional status items, and stable status items; The status items in the target test procedure table are read sequentially, and the hardware and software participating in the aero-engine test are set according to the corresponding test status attributes. Test data is collected and interpreted according to the corresponding data acquisition attributes, including: The self-test status item is read, and the hardware and software participating in the aero-engine test are configured according to the test status attribute corresponding to the self-test status item. A first test dataset is collected according to the corresponding data acquisition attribute and a first interpretation is performed. In response to the first reading being passed, the transition state item is read, the software and hardware participating in the aero-engine test are set according to the test state attribute corresponding to the transition state item, and the test dataset is collected according to the corresponding data acquisition attribute and a second reading is performed. In response to the second reading being passed, the stable state item is read, the software and hardware participating in the aero-engine test are set according to the test state attribute corresponding to the stable state item, and the third test dataset is collected according to the corresponding data acquisition attribute and the third reading is performed. In response to the third successful judgment, the first test dataset, the second test dataset, and the third test dataset are stored.

3. The method according to claim 2, characterized in that, The status item also includes a test report standard text, which includes a first type of text and a second type of text. The first type of text is plain text, and the second type of text includes mapping variables.

4. The method according to claim 3, characterized in that, In response to the completion and passing of the status item, a test report is generated based on the test data of the status item, including: In response to the completion of the target test run program table and its passing the test, the test data in the first test run dataset, the second test run dataset, and the third test run dataset are inserted into the second type of text according to the preset correspondence between the test run data and the mapping variable. The first type of text and the second type of text of each of the aforementioned status items are merged to generate the test report.

5. The method according to claim 2, characterized in that, The hardware includes an alarm switch, an ignition switch, a valve switch, and a throttle lever; the software includes control programs for the alarm switch, the ignition switch, and the valve switch; the test run status attributes include status name, status identifier, status duration, and status command; the data acquisition attributes include the acquisition parameter vector and acquisition parameter range vector of the hardware and software; the status commands include control commands from the control program and control commands from the throttle lever.

6. The method according to claim 2, characterized in that, The hardware also includes a video capture device, and the status command also includes a video capture command from the video capture device; the method further includes: Collect and interpret the test video of the aircraft engine test according to the video acquisition command in the status item; In response to the detection of flames, smoke, or people in the test video, an early warning signal is generated and a predefined safety operation is triggered, and the corresponding test video is stored.

7. An auxiliary system for automatic test firing of an aircraft engine, characterized in that, include: A construction module is used to build a test procedure table based on the data acquisition system of an aero-engine. Each status item in the test procedure table includes predefined test status attributes and data acquisition attributes. The selected module is used to respond to the user's selected operation by retrieving the target test program table corresponding to the selected operation and starting execution; The execution module is used to sequentially read the status items in the target test program table, set the software and hardware participating in the aero-engine test according to the corresponding test status attributes, and collect and interpret test data according to the corresponding data acquisition attributes. The generation module is used to generate a test report based on the test data of the status item in response to the completion of the status item and the determination that it is qualified.

8. A computer-readable storage medium, characterized in that, It stores a program that, when executed by a processor, implements an auxiliary method for automatic test firing of an aero-engine as described in any one of claims 1-6.

9. A terminal device, characterized in that, It includes a memory, a processor, and a program stored in the memory and executable on the processor, wherein the processor executes the program to implement an auxiliary method for automatic test firing of an aero-engine as described in any one of claims 1-6.

10. A computer program product, comprising a computer program, characterized in that, When the computer program is executed by the processor, it implements the auxiliary method for automatic test firing of the aero-engine as described in any one of claims 1-6.

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