A method and system for protecting a hydraulic drive system

Abstract

The present application belongs to the field of hydraulic transmission system design, and discloses a hydraulic transmission system protection method and system, the protection method comprising: collecting machine state signals, flight control system state signals and first and second hydraulic pressures of each hydraulic pipeline in the hydraulic transmission system in real time; according to the machine state signals, outputting electric pump closing instructions and hydraulic pressure logic judgment instructions through machine state threshold values and first electric pump control logic, and shutting down the electric pump connected to the hydraulic pipeline according to the electric pump closing instructions; according to the hydraulic pressure logic judgment instructions, obtaining the flight control system state signals, the first and second hydraulic pressures, and automatically controlling the electric pump through a second electric pump control mechanism and a hydraulic pipeline protection mechanism by using low pressure threshold values and pressure safety threshold values. The present application can automatically control the opening of each electric pump, protect the hydraulic pipeline through multiple mechanisms, and improve flight safety.

Description

Technical Field

[0001] This invention belongs to the field of hydraulic transmission system design and relates to a protection method and system for hydraulic transmission systems. Background Technology

[0002] In aircraft systems, the output of electric pumps is typically connected to the input of the hydraulic transmission system. The operation of the electric pump controls the hydraulic pressure or fluid power to drive mechanisms connected to the hydraulic transmission system. For example, in aircraft hydraulic transmission systems, electric pump control systems generally employ dual-redundancy or higher redundancy. Electric pumps are used frequently and in various scenarios, and currently, automated control replaces manual pilot control. However, during the control process, data source anomalies or control logic errors can still occur, leading to the continuous and erroneous activation or deactivation of the electric pump. This provides incorrect hydraulic power and pressure to the hydraulic transmission system, potentially causing overpressure or underpressure and affecting flight safety. Summary of the Invention

[0003] To address the technical problem of abnormal data sources or control logic in automated hydraulic transmission systems, leading to incorrect hydraulic power and pressure levels, resulting in overpressure or underpressure, and thus affecting the normal operation and safety of the mechanism, this invention discloses a hydraulic transmission system protection method, which includes the following steps:

[0004] S2. Real-time acquisition of onboard status signals, flight control system status signals, and the current hydraulic pressure of each hydraulic line in the hydraulic transmission system, wherein the current hydraulic pressure includes a first hydraulic pressure and a second hydraulic pressure;

[0005] S3. Based on the machine status signal, output an electric pump shutdown command and a hydraulic pressure logic judgment command through the machine status threshold and the first electric pump control logic, and shut down the electric pump connected to the hydraulic pipeline according to the electric pump shutdown command.

[0006] S4. Based on the hydraulic pressure logic judgment command, obtain the flight control system status signal, the first hydraulic pressure and the second hydraulic pressure, and automatically control the electric pump connected to each hydraulic pipeline by using the low pressure threshold and the pressure safety threshold, and adopting the second electric pump control mechanism and the hydraulic pipeline protection mechanism.

[0007] Furthermore, the method also includes:

[0008] S11. Set the machine status threshold. When the machine status signal is less than the machine status threshold, output an electric pump shutdown command. When the machine status signal is greater than or equal to the machine status threshold, output a hydraulic pressure logic judgment command to construct the first electric pump control logic.

[0009] Furthermore, the method also includes:

[0010] S12. Given the low-pressure threshold and the pressure safety threshold, obtain the first hydraulic pressure according to the hydraulic pressure logic judgment instruction, compare the first hydraulic pressure with the low-pressure threshold, and if the first hydraulic pressure is less than or equal to the low-pressure threshold, output a hydraulic pipeline protection start instruction, and control the start of the electric pump connected to the hydraulic pipeline according to the hydraulic pipeline protection start instruction through the second hydraulic pressure, the pressure safety threshold, and the hydraulic pipeline protection mechanism; if the first hydraulic pressure is greater than the low-pressure threshold, output a machine-controlled mechanism logic judgment instruction.

[0011] The flight control system status signal is obtained according to the logic judgment instruction of the onboard controlled mechanism. Based on the flight control system status signal, it is determined whether the controlled mechanism needs pressure. If it is determined that there is a pressure requirement, a hydraulic pipeline protection start command is output. According to the hydraulic pipeline protection start command, the electric pump connected to the hydraulic pipeline is started and controlled through the second hydraulic pressure, the pressure safety threshold and the hydraulic pipeline protection mechanism. If it is determined that there is no pressure requirement, an electric pump shut-off command is output, and the second electric pump control logic is constructed.

[0012] Furthermore, the method also includes:

[0013] S13. Obtain the second hydraulic pressure according to the hydraulic pipeline protection start command, compare the second hydraulic pressure with the pressure safety threshold, if the second hydraulic pressure is greater than or equal to the pressure safety threshold, output a shutdown command for the electric pump, an electric pump prohibition flag and an overpressure alarm signal to the second electric pump control logic; if the second hydraulic pressure is less than the pressure safety threshold, output an electric pump start flag to the second electric pump control logic, and construct the hydraulic pipeline protection mechanism.

[0014] Preferably, the method further includes:

[0015] S14. After outputting the hydraulic pipeline protection start command, start timing. If the second electric pump control logic does not receive the electric pump prohibition flag or the electric pump start flag output by the hydraulic pipeline protection mechanism within the set time period, activate the timeout emergency mechanism, and control the electric pump to start according to the electric pump start command output by the second electric pump control logic based on the timeout emergency mechanism.

[0016] Furthermore, the flight control system status signals include landing gear signals and control surface status signals, the onboard status signals include ground speed signals, and the controlled mechanisms include landing gear and control surfaces.

[0017] Furthermore, in step S12, determining whether the controlled mechanism requires pressure based on the flight control system status signal includes:

[0018] S121. Determine whether the landing gear has a pressure requirement based on the landing gear signal. If the landing gear signal is a retracting signal or a lowering signal, it is determined that the landing gear has a pressure requirement.

[0019] S122. Determine whether the control surface has a pressure requirement based on the control surface status signal. If the control surface status signal is a signal to change the control surface position, it is determined that the control surface has a pressure requirement.

[0020] S123. When any one or both of the control surfaces and the landing gear have a pressure requirement, it is determined that the controlled mechanism needs pressure.

[0021] This invention also provides a hydraulic transmission system protection system, which includes a data acquisition module, a data scheduling module, a monitoring module, and multiple electric pump control modules. Each electric pump control module is connected to an electric pump, and the output of the data acquisition module is connected to the input of the data scheduling module and the monitoring module.

[0022] Both the data scheduling module and the monitoring module are connected to each of the electric pump control modules. The electric pump control module, based on the onboard status signal, flight control system status signal, and first hydraulic pressure of the hydraulic line extracted from the data scheduling module, outputs electric pump control signals and starts hydraulic line protection commands using first electric pump control logic and second electric pump control logic. The monitoring module extracts the second hydraulic pressure of the hydraulic line based on the starts hydraulic line protection command, and outputs an electric pump start flag or an electric pump stop flag to the electric pump control module through the second hydraulic pressure and the pressure safety threshold.

[0023] Furthermore, the protection system also includes a power supply module. The input terminal of the power supply module is connected to the on-board power supply, and the output terminal is connected to the acquisition module, the data scheduling module, the monitoring module, and each of the electric pump control modules. The power supply module supplies power to the acquisition module, the data scheduling module, the monitoring module, and the electric pump control module.

[0024] Furthermore, the hydraulic transmission system has at least two hydraulic lines, and there are at least two electric pump control modules. Each electric pump control module is connected to one hydraulic line in the hydraulic transmission system via one electric pump, and the acquisition module is connected to the hydraulic lines via two acquisition channels.

[0025] Compared with the prior art, the beneficial effects that at least one technical solution adopted in the embodiments of this specification can achieve include at least:

[0026] 1. By automating the control of the electric pump on the hydraulic line, the pilot does not need to spend a lot of energy on controlling the electric pump during the mission, which significantly reduces the pilot's workload.

[0027] 2. By automatically controlling the opening and closing of the electric pump according to different aircraft conditions, this system avoids the need to keep the electric pump running throughout the entire process, significantly reducing aircraft energy consumption, improving energy utilization efficiency, and also preventing overpressure damage to the hydraulic transmission system in the hydraulic pipeline, thus improving flight safety.

[0028] 3. The hydraulic transmission system is designed with two levels of protection. The monitoring module continuously and independently monitors the status of each hydraulic pipeline. When the pressure of the hydraulic pipeline is too high, it can output an overpressure alarm to the electric pump control module. When the internal fault of the electric pump control module is caused by data source or logic abnormality, the electric pump can be shut down in time. Otherwise, if a more serious situation occurs, such as a hardware failure of the control module driver, the monitoring module can act as a second line of defense to directly shut down the corresponding electric pump, thereby enhancing the protection effect.

[0029] 4. By configuring an electric pump control module for each hydraulic line in the protection system, the problem of a single fault causing control failure and damage to the hydraulic transmission system is avoided, thus enhancing the safety of the aircraft.

[0030] 5. An overtime emergency mechanism was designed based on the hydraulic pipeline protection mechanism. In extreme cases where the electric pump control module fails to receive the indication signal from the monitoring module, the electric pump can be started normally, ensuring the integrity and safety of the aircraft functions. Attached Figure Description

[0031] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0032] Figure 1 This is a flowchart of a hydraulic transmission system protection method disclosed in an embodiment of the present invention;

[0033] Figure 2 The algorithm flow of the hydraulic pipeline protection mechanism disclosed in the embodiments of the present invention is as follows;

[0034] Figure 3This is the algorithm flow after the second electric pump control outputs the command to start the hydraulic pipeline protection, as disclosed in an embodiment of the present invention;

[0035] Figure 4 This is an architecture diagram of the hydraulic transmission system protection system disclosed in an embodiment of the present invention;

[0036] The system comprises: 1. Acquisition module; 2. Data scheduling module; 3. Monitoring module; 4. Electric pump control module; and 5. Power supply module. Detailed Implementation

[0037] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0038] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features of the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0039] This invention discloses a protection method for a hydraulic transmission system, see [link to relevant documentation]. Figure 1 and Figure 2 As shown, the method includes the following steps:

[0040] S2. Real-time acquisition of onboard status signals, flight control system status signals, and the current hydraulic pressure of each hydraulic line in the hydraulic transmission system, wherein the current hydraulic pressure includes a first hydraulic pressure and a second hydraulic pressure;

[0041] S3. Based on the machine status signal, output an electric pump shutdown command and a hydraulic pressure logic judgment command through the machine status threshold and the first electric pump control logic, and shut down the electric pump connected to the hydraulic pipeline according to the electric pump shutdown command.

[0042] S4. Based on the hydraulic pressure logic judgment command, obtain the flight control system status signal, the first hydraulic pressure and the second hydraulic pressure, and automatically control the electric pump connected to each hydraulic pipeline by using the low pressure threshold and the pressure safety threshold, and adopting the second electric pump control mechanism and the hydraulic pipeline protection mechanism.

[0043] Further, see Figure 1 and Figure 2As shown, the method further includes:

[0044] S11. Set the machine status threshold. When the machine status signal is less than the machine status threshold, output an electric pump shutdown command. When the machine status signal is greater than or equal to the machine status threshold, output a hydraulic pressure logic judgment command to construct the first electric pump control logic.

[0045] Furthermore, see Figure 1 and Figure 2 As shown, the method further includes:

[0046] S12. Given the low-pressure threshold and the pressure safety threshold, obtain the first hydraulic pressure according to the hydraulic pressure logic judgment instruction, compare the first hydraulic pressure with the low-pressure threshold, and if the first hydraulic pressure is less than or equal to the low-pressure threshold, output a hydraulic pipeline protection start instruction, and control the start of the electric pump connected to the hydraulic pipeline according to the hydraulic pipeline protection start instruction through the second hydraulic pressure, the pressure safety threshold, and the hydraulic pipeline protection mechanism; if the first hydraulic pressure is greater than the low-pressure threshold, output a machine-controlled mechanism logic judgment instruction.

[0047] The flight control system status signal is obtained according to the logic judgment instruction of the onboard controlled mechanism. Based on the flight control system status signal, it is determined whether the controlled mechanism needs pressure. If it is determined that there is a pressure requirement, a hydraulic pipeline protection start command is output. According to the hydraulic pipeline protection start command, the electric pump connected to the hydraulic pipeline is started and controlled through the second hydraulic pressure, the pressure safety threshold and the hydraulic pipeline protection mechanism. If it is determined that there is no pressure requirement, an electric pump shut-off command is output, and the second electric pump control logic is constructed.

[0048] Furthermore, see Figure 1 and Figure 2 As shown, the method further includes:

[0049] S13. Obtain the second hydraulic pressure according to the hydraulic pipeline protection start command, compare the second hydraulic pressure with the pressure safety threshold, if the second hydraulic pressure is greater than or equal to the pressure safety threshold, output a shutdown command for the electric pump, an electric pump prohibition flag and an overpressure alarm signal to the second electric pump control logic; if the second hydraulic pressure is less than the pressure safety threshold, output an electric pump start flag to the second electric pump control logic, and construct the hydraulic pipeline protection mechanism.

[0050] Preferred, see Figure 3 The method described herein also includes:

[0051] S14. After outputting the hydraulic pipeline protection start command, start timing. If the second electric pump control logic does not receive the electric pump prohibition flag or the electric pump start flag output by the hydraulic pipeline protection mechanism within the set time period, activate the timeout emergency mechanism, and control the electric pump to start according to the electric pump start command output by the second electric pump control logic based on the timeout emergency mechanism.

[0052] Furthermore, the flight control system status signals include landing gear signals and control surface status signals, the onboard status signals include ground speed signals, and the controlled mechanisms include landing gear and control surfaces.

[0053] Furthermore, see Figure 1 and Figure 2 As shown, in step S12, determining whether the controlled mechanism requires pressure based on the flight control system status signal includes:

[0054] S121. Determine whether the landing gear has a pressure requirement based on the landing gear signal. If the landing gear signal is a retracting signal or a lowering signal, it is determined that the landing gear has a pressure requirement.

[0055] S122. Determine whether the control surface has a pressure requirement based on the control surface status signal. If the control surface status signal is a signal to change the control surface position, it is determined that the control surface has a pressure requirement.

[0056] S123. When any one or both of the control surfaces and the landing gear have a pressure requirement, it is determined that the controlled mechanism needs pressure.

[0057] Based on the same inventive concept, this invention also provides a hydraulic transmission system protection system, as described in the following embodiments. The hydraulic transmission system protection system is used to implement the aforementioned hydraulic transmission system protection method. As used below, the terms "unit" or "module" can refer to a combination of software and / or hardware that performs a predetermined function. Although the apparatus described in the following embodiments is preferably implemented in software, hardware implementation, or a combination of software and hardware, is also possible and contemplated.

[0058] See Figure 4 As shown, the protection system includes a data acquisition module 1, a data scheduling module 2, a monitoring module 3, and multiple electric pump control modules 4. Each electric pump control module 4 is connected to an electric pump. The output of the data acquisition module 1 is connected to the input of the data scheduling module 2 and the monitoring module 3.

[0059] Both the data scheduling module 2 and the monitoring module 3 are connected to each of the electric pump control modules 4. The electric pump control module 4, based on the onboard status signal, flight control system status signal, and first hydraulic pressure of the hydraulic pipeline extracted from the data scheduling module 2, outputs electric pump control signals and starts hydraulic pipeline protection commands using first electric pump control logic and second electric pump control logic. The monitoring module 3, based on the starts hydraulic pipeline protection command, extracts the second hydraulic pressure of the hydraulic pipeline and outputs an electric pump start flag or an electric pump stop flag to the electric pump control module 4 through the second hydraulic pressure and the pressure safety threshold.

[0060] Furthermore, the protection system also includes a power supply module 5. The input end of the power supply module 5 is connected to the on-board power supply, and the output end is connected to the acquisition module 1, the data scheduling module 2, the monitoring module 3 and each of the electric pump control modules 4. The power supply module 5 supplies power to the acquisition module 1, the data scheduling module 2, the monitoring module 3 and the electric pump control module 4.

[0061] Furthermore, the hydraulic transmission system has at least two hydraulic lines, and there are at least two electric pump control modules 4. Each electric pump control module 4 is connected to one hydraulic line in the hydraulic transmission system via an electric pump, and the acquisition module is connected to the hydraulic lines via two acquisition channels.

[0062] 1. By automating the control of the electric pump on the hydraulic line, the pilot does not need to spend a lot of energy on controlling the electric pump during the mission, which significantly reduces the pilot's workload.

[0063] 2. By automatically controlling the opening and closing of the electric pump according to different aircraft conditions, this system avoids the need to keep the electric pump running throughout the entire process, significantly reducing aircraft energy consumption, improving energy utilization efficiency, and also preventing overpressure damage to the hydraulic transmission system in the hydraulic pipeline, thus improving flight safety.

[0064] 3. The hydraulic transmission system is designed with two levels of protection. The monitoring module continuously and independently monitors the status of each hydraulic pipeline. When the pressure of the hydraulic pipeline is too high, it can output an overpressure alarm to the electric pump control module. When the internal fault of the electric pump control module is caused by data source or logic abnormality, the electric pump can be shut down in time. Otherwise, if a more serious situation occurs, such as a hardware failure of the control module driver, the monitoring module can act as a second line of defense to directly shut down the corresponding electric pump, thereby enhancing the protection effect.

[0065] 4. By configuring an electric pump control module for each hydraulic line in the protection system, the problem of a single fault causing control failure and damage to the hydraulic transmission system is avoided, thus enhancing the safety of the aircraft.

[0066] 5. An overtime emergency mechanism was designed based on the hydraulic pipeline protection mechanism. In extreme cases where the electric pump control module fails to receive the indication signal from the monitoring module, the electric pump can be started normally, ensuring the integrity and safety of the aircraft functions.

[0067] Obviously, those skilled in the art should understand that the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Various modifications and variations of the embodiments of the present invention are possible for those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A protection method for a hydraulic transmission system, characterized in that, The method includes: The system collects real-time status signals from the aircraft, flight control system, and the current hydraulic pressure of each hydraulic line in the hydraulic transmission system. The current hydraulic pressure includes a first hydraulic pressure and a second hydraulic pressure. Based on the machine status signal, the machine status threshold and the first electric pump control logic output an electric pump shutdown command and a hydraulic pressure logic judgment command, and shut down the electric pump connected to the hydraulic pipeline according to the electric pump shutdown command; Based on the hydraulic pressure logic judgment command, the flight control system status signal, the first hydraulic pressure, and the second hydraulic pressure are obtained. Through the low pressure threshold and the pressure safety threshold, the electric pump connected to each hydraulic pipeline is automatically controlled using the second electric pump control mechanism and the hydraulic pipeline protection mechanism.

2. The hydraulic transmission system protection method according to claim 1, characterized in that, The method further includes: Set the machine status threshold. When the machine status signal is less than the machine status threshold, output an electric pump shutdown command. When the machine status signal is greater than or equal to the machine status threshold, output a hydraulic pressure logic judgment command to construct the first electric pump control logic.

3. The hydraulic transmission system protection method according to claim 2, characterized in that, The method further includes: Given the low-pressure threshold and the pressure safety threshold, the first hydraulic pressure is obtained according to the hydraulic pressure logic judgment instruction. The first hydraulic pressure and the low-pressure threshold are compared. If the first hydraulic pressure is less than or equal to the low-pressure threshold, a hydraulic pipeline protection start instruction is output. According to the hydraulic pipeline protection start instruction, the electric pump connected to the hydraulic pipeline is started and controlled through the second hydraulic pressure, the pressure safety threshold, and the hydraulic pipeline protection mechanism. If the first hydraulic pressure is greater than the low-pressure threshold, a controlled mechanism logic judgment instruction is output. The flight control system status signal is obtained according to the logic judgment instruction of the onboard controlled mechanism. Based on the flight control system status signal, it is determined whether the controlled mechanism needs pressure. If it is determined that there is a pressure requirement, a hydraulic pipeline protection start command is output. According to the hydraulic pipeline protection start command, the electric pump connected to the hydraulic pipeline is started and controlled through the second hydraulic pressure, the pressure safety threshold and the hydraulic pipeline protection mechanism. If it is determined that there is no pressure requirement, an electric pump shut-off command is output, and the second electric pump control logic is constructed.

4. The hydraulic transmission system protection method according to claim 3, characterized in that, The method further includes: The second hydraulic pressure is obtained according to the hydraulic pipeline protection start command. The second hydraulic pressure is compared with the pressure safety threshold. If the second hydraulic pressure is greater than or equal to the pressure safety threshold, the electric pump stop command, electric pump prohibition start flag and overpressure alarm signal are output to the second electric pump control logic. If the second hydraulic pressure is less than the pressure safety threshold, the electric pump start flag is output to the second electric pump control logic, thus constructing the hydraulic pipeline protection mechanism.

5. The hydraulic transmission system protection method according to claim 4, characterized in that, After the hydraulic pipeline protection command is output, a timer is started. If the second electric pump control logic does not receive the electric pump prohibition flag or the electric pump start flag output by the hydraulic pipeline protection mechanism within a set time period, the timeout emergency mechanism is activated. According to the timeout emergency mechanism, the electric pump is controlled to start using the electric pump start command output by the second electric pump control logic.

6. The hydraulic transmission system protection method according to any one of claims 3 to 5, characterized in that, The flight control system status signals include landing gear signals and control surface status signals, the onboard status signals include ground speed signals, and the controlled mechanisms include landing gear and control surfaces.

7. The hydraulic transmission system protection method according to claim 6, characterized in that, Determining whether the controlled mechanism requires pressure based on the flight control system status signal includes: The landing gear signal is used to determine whether the landing gear has a pressure requirement. If the landing gear signal is a retraction signal or a lowering signal, it is determined that the landing gear has a pressure requirement. The system determines whether the system has a pressure requirement based on the system status signal. If the system status signal is a signal to change the system position, it is determined that the system has a pressure requirement. When any one or both of the control surfaces and the landing gear have a pressure requirement, it is determined that the controlled mechanism needs pressure.

8. A hydraulic transmission system protection system for executing the hydraulic transmission system protection method according to any one of claims 1 to 7, characterized in that, The protection system includes a data acquisition module, a data scheduling module, a monitoring module, and multiple electric pump control modules. Each electric pump control module is connected to an electric pump. The output of the data acquisition module is connected to the input of the data scheduling module and the monitoring module. Both the data scheduling module and the monitoring module are connected to each of the electric pump control modules. The electric pump control module, based on the onboard status signal, flight control system status signal, and first hydraulic pressure of the hydraulic line extracted from the data scheduling module, outputs electric pump control signals and starts hydraulic line protection commands using first electric pump control logic and second electric pump control logic. The monitoring module extracts the second hydraulic pressure of the hydraulic line based on the starts hydraulic line protection command, and outputs an electric pump start flag or an electric pump stop flag to the electric pump control module through the second hydraulic pressure and the pressure safety threshold.

9. The hydraulic transmission system protection system according to claim 8, characterized in that, The protection system also includes a power supply module. The input terminal of the power supply module is connected to the on-board power supply, and the output terminal is connected to the acquisition module, the data scheduling module, the monitoring module and each of the electric pump control modules. The power supply module supplies power to the acquisition module, the data scheduling module, the monitoring module and the electric pump control module.

10. The hydraulic transmission system protection system according to claim 8, characterized in that, The hydraulic transmission system has at least two hydraulic lines, and there are at least two electric pump control modules. Each electric pump control module is connected to one hydraulic line in the hydraulic transmission system via one electric pump. The acquisition module is connected to the hydraulic lines via two acquisition channels.

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