A vulnerability detection apparatus and method for an airborne propulsion system
By using the fewest and simplest vulnerability detection devices, and simulating engine status commands and feedback signals to detect propulsion control systems, the problems of complex and costly devices in existing technologies are solved, and efficient vulnerability detection and potential defect discovery are achieved.
Patent Information
- Application Number
- CN202411217648.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-02
- Publication Date
- 2025-11-21
- Estimated Expiration
- 2044-09-02
AI Technical Summary
In existing technologies, propulsion control system vulnerability detection devices have complex structures, require multiple devices, are costly, and affect detection efficiency, making it impossible to effectively detect potential functional defects.
Employing the fewest and simplest vulnerability detection devices, including a simulated engine status command module, a servo module, a propulsion baffle module, and an angle sensor module, it provides vulnerability detection methods in both active and follow modes, detecting the functional consistency of the control system through simulated engine status commands and feedback signals.
It efficiently detects potential functional defects, avoids actual equipment damage, reduces testing costs, and improves testing efficiency.
Smart Images
Figure CN119063980B_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of testing technology for airborne propulsion systems, and relates to a vulnerability detection device and method for airborne propulsion systems. Background Technology
[0002] In the modern aviation industry, ensuring the safe and stable operation of aircraft in the air is of paramount importance. Especially before aircraft assembly, rigorous testing of airborne components is an essential step. The propulsion system, the aircraft's power source, is a core component ensuring normal flight. It not only provides the power required for takeoff, cruise, and landing but also affects the aircraft's range and fuel efficiency. The propulsion system's control system (i.e., the propulsion control system) is crucial, managing and regulating the engine's operating parameters to ensure optimal performance and reliability of the propulsion system.
[0003] The propulsion control system can receive commands from the left and right engines and control the left propulsion baffle (e.g., Figure 2 (middle F) and right propulsion baffle (e.g.) Figure 2 (G) move and ensure that the workflow is effective on both sides of the wing (e.g. Figure 2 The normal working process on the propulsion control system is as follows: Figure 1 As shown, engine A sends a command to propulsion control system B. Propulsion control system B calculates the command and sends a control command to servo motor C. Servo motor C controls the propulsion baffles D on both wings to move. Angle sensor E detects the angle change of propulsion baffle D and sends it to propulsion control system B.
[0004] However, in actual aircraft operation, situations may arise where the propulsion control system fails to receive status commands from one of the engine sides. In such cases, the wing on the failed side will be controlled according to the commands from the non-failed side. For example, when the propulsion control system cannot receive status commands from the left engine, the status commands from the right engine will be used as the control basis for the left engine. A malfunction in the propulsion control system will lead to a decline in engine performance and may even cause a flight accident. Therefore, vulnerability detection of the propulsion system's control system is a crucial step in ensuring flight safety.
[0005] Currently, the vulnerability detection of the control system of the propulsion system mainly focuses on testing the existing functions in the control system to detect whether the current functions meet the design requirements. The vulnerability detection of the control system mainly relies on command simulation and feedback signal reception. Command simulation inputs a series of predetermined commands through test software or hardware devices, which simulates various control signals that the propulsion system may receive during flight. The simulation commands are transmitted to the control unit of the propulsion system to observe the reaction of the control unit. This process aims to simulate the command operation in the real flight environment to ensure that the control system can correctly receive and process the commands. During the execution of the command, the feedback signals of the propulsion system are collected. The collected feedback signals are compared with the expected results to analyze whether the control system executes the command as designed. If the feedback signals do not match the expected results, further investigation is needed to identify potential problems in the control system. However, the current vulnerability detection device for the control system has a complex structure and needs to be used with multiple devices to simulate on-board equipment, which is not only costly but also affects the detection efficiency. SUMMARY
[0006] Therefore, the present application provides a vulnerability detection device and method for an airborne propulsion system, which can simulate engine state commands, rudders, propulsion baffles and angle sensors, and uses the least and simplest device to detect the propulsion control system, not only avoiding the loss of actual equipment, but also efficiently discovering potential functional defects, especially in detecting the control system, showing unique advantages.
[0007] A vulnerability detection device for an airborne propulsion system, the vulnerability detection device comprising a simulated engine state command module 1, a simulated rudder module 2, a simulated propulsion baffle module 3, a simulated angle sensor module 4 and a display module 5; the simulated engine state command module 1 is used to simulate left and right engines, and sends simulated engine commands of the left and right engines to the to-be-tested propulsion control system 6; the simulated rudder module 2 is used to simulate left and right propulsion rudders, receives control commands sent by the to-be-tested propulsion control system 6 and controls the simulated propulsion baffle module 3 to generate simulated action commands; the simulated propulsion baffle module 3 is used to simulate the propulsion baffles of the left and right wings, generates simulated action signals according to the simulated action commands sent by the simulated propulsion baffle module 3; the simulated angle sensor module 4 is used to detect the simulated action signals generated by the simulated propulsion baffle module 3 and sends simulated angle sensor commands to the to-be-tested propulsion control system 6; the to-be-tested propulsion control system 6 receives the simulated angle sensor commands and judges whether they are consistent with the control command signals calculated based on the simulated engine commands, and sends the judgment results to the display module 5 for display.
[0008] The vulnerability detection device has two detection modes, namely active mode and follow-up mode.
[0009] In the active mode, the vulnerability detection device detects the synchronization of the engine state instructions on both sides, that is, the vulnerability detection device simultaneously sends the state instructions of the left and right engines to the to-be-tested propulsion control system 6, and feeds back the judgment result of the propulsion control system to the vulnerability detection device; if any side propulsion baffle cannot work normally, it indicates that the propulsion control system fails in the active mode, so as to judge that the whole propulsion control system cannot work normally.
[0010] In the following mode, the vulnerability detection device only simulates the instruction of one side engine, and copies the instruction to the other side, and simultaneously sends the two same instructions to the to-be-tested propulsion control system 6 to execute the vulnerability detection process; if any side propulsion baffle cannot work normally, it indicates that the propulsion control system fails in the following mode, so as to judge that the whole propulsion control system cannot work normally.
[0011] Further, the vulnerability detection device can increase other modes according to needs in addition to the active mode and the following mode.
[0012] Further, all the instruction signals transmitted in the vulnerability detection device can be analog signals or numerical signals, wherein the analog signals include voltage and current.
[0013] Further, the vulnerability detection device can be a computer operating system, or can be a software and hardware combined system combined with hardware devices, including external rudders, angle sensors and the like hardware devices.
[0014] The application also provides a vulnerability detection method for an airborne propulsion system, which comprises the following processes:
[0015] Step 1, the to-be-tested propulsion control system 6 is communicated with the vulnerability detection device.
[0016] Step 2, in the active mode, the vulnerability detection is carried out: the simulation engine state instruction module 1 simulates the left and right engines to simultaneously send the state instructions of the left and right engines to the to-be-tested propulsion control system 6, the to-be-tested propulsion control system 6 sends the control instructions to the simulation rudder module 2 after calculation, the simulation rudder module 2 receives the control instructions to control the simulation propulsion baffle module 3 to form the simulation action signal to simulate the movement of the propulsion baffle, the simulation angle sensor module 4 detects the simulation action signal to form the simulation action signal and sends it to the to-be-tested propulsion control system 6, the to-be-tested propulsion control system 6 receives the simulation action signal, judges whether it is consistent with the control instruction signal calculated by the to-be-tested propulsion control system 6 based on the simulation engine instruction, if consistent, the to-be-tested propulsion control system 6 is normal, if not consistent, the to-be-tested propulsion control system 6 cannot work normally, and the judgment result is sent to the display module 5 for display.
[0017] Step 3, carry out the vulnerability detection in the following mode: the simulation engine state instruction module 1 only simulates the instruction of an engine, and copies the instruction to the other side, and sends the two same state instructions to the to-be-tested propulsion control system 6, the to-be-tested propulsion control system 6 sends a control instruction to the simulation rudder module 2 after calculation, the simulation rudder module 2 controls the simulation propulsion damper module 3 to form a simulation action signal after receiving the control instruction, so as to simulate the movement of the propulsion damper, the simulation angle sensor module 4 detects the simulation action signal to form a simulation action signal and sends it to the to-be-tested propulsion control system 6, the to-be-tested propulsion control system 6 receives the simulation action signal, and judges whether it is consistent with the control instruction signal calculated by the to-be-tested propulsion control system 6 based on the simulation engine instruction, if consistent, the to-be-tested propulsion control system 6 is normal, if not consistent, the to-be-tested propulsion control system 6 cannot work normally, and the judgment result is sent to the display module 5 for display.
[0018] The beneficial effects of the present application are that the present application uses the least simple device to detect the propulsion control system, not only avoids the loss of actual equipment, but also can efficiently find potential functional defects, especially in the detection of the control system, and shows unique advantages. BRIEF DESCRIPTION OF DRAWINGS
[0019] Figure 1 For the normal working process of the propulsion control system, in the figure, A is an engine, B is a propulsion control system, C is a rudder, D is a propulsion damper, and E is an angle sensor;
[0020] Figure 2 For the example of the propulsion control system controlling the propulsion dampers on both sides of the wing, in the figure, F is a left propulsion damper, and G is a right propulsion damper;
[0021] Figure 3 For the main vulnerability detection process of the propulsion control system;
[0022] Figure 4 For the vulnerability detection device of the propulsion control system;
[0023] Figure 5 For the working principle diagram of the active mode;
[0024] Figure 6 For the working principle diagram of the following mode;
[0025] In the figure: 1 simulation engine state instruction module; 2 simulation rudder module; 3 simulation propulsion damper module; 4 simulation angle sensor module; 5 display module; 6 to-be-tested propulsion control system. DETAILED DESCRIPTION
[0026] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. The drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0027] This embodiment provides a vulnerability detection device for airborne propulsion systems, such as... Figure 3 As shown, the vulnerability detection device includes a simulated engine status command module 1, a simulated servo module 2, a simulated propulsion baffle module 3, a simulated angle sensor module 4, and a display module 5. The simulated engine status command module 1 simulates the left and right engines, sending simulated engine commands for each engine to the propulsion control system under test (6). The simulated servo module 2 simulates the left and right propulsion servos, receiving control commands from the propulsion control system under test (6) and controlling the simulated propulsion baffle module 3 to generate simulated action commands. The simulated propulsion baffle module 3 simulates the propulsion baffles on the left and right wings, generating simulated action signals based on the simulated action commands sent by the simulated propulsion baffle module 3. The simulated angle sensor module 4 detects the simulated action signals generated by the simulated propulsion baffle module 3 and sends simulated angle sensor commands to the propulsion control system under test (6). The propulsion control system under test (6) receives the simulated angle sensor commands and determines whether they are consistent with the control command signals calculated based on the simulated engine commands, then sends the determination result to the display module 5 for display. All command signals transmitted in the vulnerability detection device are simulated signals.
[0028] The vulnerability detection device has two detection modes: active mode and follow mode. Active mode aims to detect whether the propulsion control system can simultaneously control the propulsion flaps of both wings and ensure that this workflow is effective on both wings. However, during actual flight, the propulsion control system may fail to receive status commands from the engines of one wing. In this case, the wing on the failed side will be controlled according to the commands from the non-failed side. To address this situation, the vulnerability detection device includes a follow mode. Specifically:
[0029] In active mode (working principle as follows) Figure 5 As shown), the vulnerability detection device performs synchronous vulnerability detection on the status commands of the engines on both sides. That is, the vulnerability detection device sends the status commands of the left and right engines to the propulsion control system 6 under test at the same time, and feeds back the judgment result of the propulsion control system to the vulnerability detection device. If the propulsion baffle on either side fails to work properly, it indicates that the propulsion control system has failed in active mode, thus indicating that the propulsion control system as a whole cannot operate normally.
[0030] In the following mode (working principle as shown in Figure 6 , the vulnerability detection device only simulates the instructions of one side engine, and copies the instructions to the other side, and sends the two same instructions to the tested propulsion control system 6 to execute the vulnerability detection process; if any side propulsion baffle cannot work normally, it indicates that the propulsion control system fails in the following mode, so as to judge that the whole propulsion control system cannot work normally.
[0031] The embodiment also provides a vulnerability detection method for an airborne propulsion system, and the flow chart is as shown in Figure 4 The vulnerability detection method comprises the following steps:
[0032] Step 1, the tested propulsion control system 6 is connected with the vulnerability detection device.
[0033] Step 2, in the active mode, the vulnerability detection is carried out: the simulation engine state instruction module 1 simulates the left and right engine state instructions to the tested propulsion control system 6, the tested propulsion control system 6 sends the control instructions to the simulation rudder module 2 after calculation, the simulation rudder module 2 controls the simulation propulsion baffle module 3 to form the simulation action signal to simulate the movement of the propulsion baffle, the simulation angle sensor module 4 detects the simulation action signal to form the simulation action signal and sends it to the tested propulsion control system 6, the tested propulsion control system 6 receives the simulation action signal, and judges whether it is consistent with the control instruction signal calculated by the tested propulsion control system 6 based on the simulation engine instruction, if yes, the tested propulsion control system 6 is normal, if not, the tested propulsion control system 6 cannot work normally, and the judgment result is sent to the display module 5 for display.
[0034] Step 3, in the following mode, the vulnerability detection is carried out: the simulation engine state instruction module 1 only simulates the instructions of one side engine, and copies the instructions to the other side, and sends the two same state instructions to the tested propulsion control system 6, the tested propulsion control system 6 sends the control instructions to the simulation rudder module 2 after calculation, the simulation rudder module 2 controls the simulation propulsion baffle module 3 to form the simulation action signal to simulate the movement of the propulsion baffle, the simulation angle sensor module 4 detects the simulation action signal to form the simulation action signal and sends it to the tested propulsion control system 6, the tested propulsion control system 6 receives the simulation action signal, and judges whether it is consistent with the control instruction signal calculated by the tested propulsion control system 6 based on the simulation engine instruction, if yes, the tested propulsion control system 6 is normal, if not, the tested propulsion control system 6 cannot work normally, and the judgment result is sent to the display module 5 for display.
[0035] The above described embodiments only express the implementation ways of the present application, but cannot be understood as the limitation to the scope of the present application. It should be pointed out that, for the person skilled in the art, several variations and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application.
Claims
1. A vulnerability detection device for an airborne propulsion system, characterized in that, The vulnerability detection device includes a simulated engine status command module (1), a simulated servo module (2), a simulated propulsion baffle module (3), a simulated angle sensor module (4), and a display module (5). The simulated engine status command module (1) is used to simulate the left and right engines and send simulated engine commands for the left and right engines to the propulsion control system under test (6). The simulated servo module (2) is used to simulate the left and right propulsion servos, receive control commands sent by the propulsion control system under test (6), and control the simulated propulsion baffle module (3) to generate simulated action commands. The simulated propulsion baffle module (3) is used to simulate the left and right propulsion servos. The simulated propulsion baffles on the left and right wings generate simulated action signals according to the simulated action commands sent by the simulated propulsion baffle module (3); the simulated angle sensor module (4) is used to detect the simulated action signals generated by the simulated propulsion baffle module (3) and send simulated angle sensor commands to the propulsion control system under test (6); the propulsion control system under test (6) receives the simulated angle sensor commands and determines whether they are consistent with the control command signals calculated based on the simulated engine commands, and sends the determination results to the display module (5) for display; the vulnerability detection device is equipped with two detection modes, namely active mode and follow mode.
2. The vulnerability detection device for an airborne propulsion system according to claim 1, characterized in that, In the active mode, the vulnerability detection device sends the status commands of the left and right engines to the propulsion control system under test (6) at the same time, and feeds back the judgment result of the propulsion control system to the vulnerability detection device; if the propulsion baffle on either side fails to work properly, it indicates that the propulsion control system has failed in the active mode.
3. The vulnerability detection device for an airborne propulsion system according to claim 1, characterized in that, In the follow mode, the vulnerability detection device simulates the command of one side of the engine and copies the command to the other side. At the same time, the two identical commands are sent to the propulsion control system (6) under test to execute the vulnerability detection process. If the propulsion baffle on either side fails to work properly, it indicates that the propulsion control system has failed in the follow mode.
4. A vulnerability detection device for an airborne propulsion system according to any one of claims 1-3, characterized in that, The vulnerability detection device can be equipped with other modes as needed.
5. A vulnerability detection device for an airborne propulsion system according to claim 1, characterized in that, The instruction signals transmitted in the vulnerability detection device are either analog or numerical signals.
6. A vulnerability detection device for an airborne propulsion system according to claim 1, characterized in that, The vulnerability detection device is a computer operating system or a combined hardware and software system composed of hardware devices.
7. A vulnerability detection method for an airborne propulsion system, implemented based on the vulnerability detection device according to any one of claims 1-3, characterized in that, The vulnerability detection method includes the following process: Step 1: Connect the propulsion control system (6) under test to the vulnerability detection device; Step 2, vulnerability detection in active mode: Simulated engine status command module (1) simulates the left and right engines simultaneously sending the status commands of the left and right engines to the propulsion control system under test (6). The propulsion control system under test (6) calculates and sends control commands to simulated servo module (2). After receiving the control commands, simulated servo module (2) controls simulated propulsion baffle module (3) to form simulated action signals to simulate the movement of propulsion baffle. Simulated angle sensor module (4) detects the simulated action signals and forms simulated action signals to send to the propulsion control system under test (6). The propulsion control system under test (6) receives the simulated action signals and judges whether they are consistent with the control command signals calculated by the propulsion control system under test (6) based on simulated engine commands. If they are consistent, the propulsion control system under test (6) is normal. If they are inconsistent, the propulsion control system under test (6) cannot work properly and sends the judgment result to display module (5) for display. Step 3, vulnerability detection in follow mode: The simulated engine status command module (1) simulates the command of one side of the engine and copies the command to the other side. At the same time, the two identical status commands are sent to the propulsion control system under test (6). The propulsion control system under test (6) calculates and sends the control command to the simulated servo module (2). After receiving the control command, the simulated servo module (2) controls the simulated propulsion baffle module (3) to form a simulated action signal to simulate the movement of the propulsion baffle. The simulated angle sensor module (4) detects the simulated action signal and forms a simulated action signal to send to the propulsion control system under test (6). The propulsion control system under test (6) receives the simulated action signal and judges whether it is consistent with the control command signal calculated by the propulsion control system under test (6) based on the simulated engine command. If they are consistent, the propulsion control system under test (6) is normal. If they are inconsistent, the propulsion control system under test (6) cannot work properly and sends the judgment result to the display module (5) for display.
8. A vulnerability detection method for an airborne propulsion system, implemented based on the vulnerability detection device described in claim 4, characterized in that, The vulnerability detection method includes the following process: Step 1: Connect the propulsion control system (6) under test to the vulnerability detection device; Step 2, vulnerability detection in active mode: Simulated engine status command module (1) simulates the left and right engines simultaneously sending the status commands of the left and right engines to the propulsion control system under test (6). The propulsion control system under test (6) calculates and sends control commands to simulated servo module (2). After receiving the control commands, simulated servo module (2) controls simulated propulsion baffle module (3) to form simulated action signals to simulate the movement of propulsion baffle. Simulated angle sensor module (4) detects the simulated action signals and forms simulated action signals to send to the propulsion control system under test (6). The propulsion control system under test (6) receives the simulated action signals and judges whether they are consistent with the control command signals calculated by the propulsion control system under test (6) based on simulated engine commands. If they are consistent, the propulsion control system under test (6) is normal. If they are inconsistent, the propulsion control system under test (6) cannot work properly and sends the judgment result to display module (5) for display. Step 3, vulnerability detection in follow mode: The simulated engine status command module (1) simulates the command of one side of the engine and copies the command to the other side. At the same time, the two identical status commands are sent to the propulsion control system under test (6). The propulsion control system under test (6) calculates and sends the control command to the simulated servo module (2). After receiving the control command, the simulated servo module (2) controls the simulated propulsion baffle module (3) to form a simulated action signal to simulate the movement of the propulsion baffle. The simulated angle sensor module (4) detects the simulated action signal and forms a simulated action signal to send to the propulsion control system under test (6). The propulsion control system under test (6) receives the simulated action signal and judges whether it is consistent with the control command signal calculated by the propulsion control system under test (6) based on the simulated engine command. If they are consistent, the propulsion control system under test (6) is normal. If they are inconsistent, the propulsion control system under test (6) cannot work properly and sends the judgment result to the display module (5) for display.
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