Hydraulic mechanism heterogeneous control method and system for large transport aircraft

Abstract

The present application belongs to the field of airborne electromechanical, discloses a hydraulic mechanism heterogeneous control method and system for large transport aircraft, the method comprises: dividing the hydraulic system into two groups, collecting on-board state signals, flight control system state signals and first and second hydraulic pressures of the sub-hydraulic system, setting on-board state threshold, low pressure threshold, hydraulic safety threshold and sub-hydraulic system relationship table; using the first control logic architecture constructed to automatically control the start and stop of the electric pumps in the first group through the above data; using the second control logic architecture constructed to automatically control the start and stop of the electric pumps in the second group through the above data. The system comprises a grouping module, a control logic construction module and two control units, the control unit comprises an acquisition module, a data scheduling module, a staggered start module, an anti-overpressure protection module and an anti-error working module. All electric pumps are controlled through two heterogeneous logic architectures, improving control accuracy and safety.

Description

Technical Field

[0001] This invention belongs to the field of airborne electromechanical systems and relates to hydraulic mechanism control technology, specifically to a heterogeneous control method and system for the hydraulic mechanism of a large transport aircraft. Background Technology

[0002] The hydraulic system of large transport aircraft is one of the key systems related to flight safety. The electric pump in the hydraulic system provides hydraulic or fluid power to the hydraulic transmission system to drive and control various aircraft mechanisms, such as landing gear and control surfaces. The hydraulic system is characterized by high frequency of use and high system safety requirements during the flight of large transport aircraft. Currently, most of them are controlled by automation to improve energy efficiency and reduce safety hazards.

[0003] However, currently all redundancy sub-hydraulic systems in the hydraulic system are controlled by the same control logic. If safety design considerations are not taken into account, when external special risks or common mode risks occur, control abnormalities may occur, resulting in the loss or error of corresponding functions, affecting the normal operation of the mechanism, and in severe cases, causing catastrophic consequences.

[0004] In addition, due to the high complexity of hydraulic systems, it is difficult to guarantee that no abnormalities will occur during long-term operation. Mitigation measures need to be designed for abnormal situations. For example, when the data source is abnormal or the electric pump control logic is abnormal, how to avoid the drawbacks of erroneous commands causing overpressure damage to the hydraulic transmission system or underpressure failure to drive the mechanism. Summary of the Invention

[0005] To address the technical problem that the hydraulic systems of large transport aircraft often use the same control logic to control all electric pumps, leading to control anomalies, loss of function, or malfunctions that affect the normal operation of the mechanism and, in severe cases, catastrophic consequences, this invention discloses a heterogeneous control method for the hydraulic mechanisms of large transport aircraft. The hydraulic system includes multiple sub-hydraulic systems, each equipped with an electric pump. The method controls each of these electric pumps, and includes:

[0006] S1. Divide all the sub-hydraulic systems into two groups, each group including at least one of the sub-hydraulic systems;

[0007] S2. Real-time acquisition of onboard status signals, flight control system status signals, and the first and second hydraulic pressures of each of the sub-hydraulic systems;

[0008] S3. Using the constructed first control logic architecture, based on the onboard status threshold, low pressure threshold, sub-hydraulic system relationship table, the onboard status signal, the flight control system status signal, and the first hydraulic pressure of the two associated sub-hydraulic systems, the electric pump installed on each of the sub-hydraulic systems in the first group is automatically controlled to start and stop.

[0009] S4. Using the constructed second control logic architecture, based on the machine status threshold, the low pressure threshold, the hydraulic safety threshold, the machine status signal, the first hydraulic pressure and the second hydraulic pressure of each of the sub-hydraulic systems in the second group, the electric pump installed on each of the sub-hydraulic systems in the second group is automatically controlled to start and stop.

[0010] Further, in step S3 above, the constructed first control logic architecture is adopted, and based on the onboard state threshold, low pressure threshold, sub-hydraulic system relationship table, the onboard state signal, the flight control system state signal, and the first hydraulic pressure of the two associated sub-hydraulic systems, the electric pump installed on each of the sub-hydraulic systems in the first group is automatically controlled to start and stop, including:

[0011] S31. Construct a first control logic architecture that includes an error prevention working mechanism and a mistime start mechanism, and establish a sub-hydraulic system relationship table for all the sub-hydraulic systems in the first group;

[0012] S32. Extract the machine status signal. When the machine status signal is less than the machine status threshold, output a command to shut down the electric pump. Based on the command to shut down the electric pump and the electric pump control result of the sub-hydraulic system associated with the controlled sub-hydraulic system, shut down the electric pump or output an alarm signal based on the error prevention mechanism and the sub-hydraulic system relationship table.

[0013] S33. When the machine status signal is greater than or equal to the machine status threshold, an electric pump start command or a machine-controlled mechanism logic judgment command is obtained based on the first hydraulic pressure and the low pressure threshold. Based on the electric pump start command and the electric pump control result, the electric pump is started or an alarm signal is output through the error prevention working mechanism and the staggered start mechanism.

[0014] S34. Obtain the flight control system status signal according to the logic judgment instruction of the controlled mechanism on the aircraft, and determine whether the controlled mechanism needs pressure based on the flight control system status signal; if it is determined that there is a pressure requirement, output an electric pump start command, and start the electric pump or output an alarm signal according to the electric pump start command and the electric pump control result through the error prevention working mechanism and the staggered start mechanism; if it is determined that there is no pressure requirement, shut down the electric pump based on the error prevention working mechanism.

[0015] Further, in step S32 above, based on the electric pump shutdown command and the electric pump control result of the sub-hydraulic system associated with the controlled sub-hydraulic system, the electric pump is shut down or an alarm signal is output based on the error prevention mechanism and the sub-hydraulic system relationship table, including: performing a consistency judgment between the electric pump shutdown command and the electric pump control result; if the judgment is consistent, the electric pump is shut down according to the electric pump shutdown command; if the judgment is inconsistent, an alarm signal is output.

[0016] In steps S33 and S34 above, the electric pump is started or an alarm signal is output according to the electric pump start command and the electric pump control result through the error prevention working mechanism and the staggered start mechanism. This includes: determining the consistency between the electric pump start command and the electric pump control result; if the determination is consistent, the electric pump is started according to the electric pump start command through the staggered start mechanism; if the determination is inconsistent, an alarm signal is output.

[0017] Further, in step S4 above, the constructed second control logic architecture is adopted, and based on the machine status threshold, the low pressure threshold, the hydraulic safety threshold, the machine status signal, and the first and second hydraulic pressures of each sub-hydraulic system in the second group, the electric pump installed on each of the sub-hydraulic systems in the second group is automatically controlled to start and stop, including:

[0018] S41. Construct a second control logic architecture that includes an overpressure protection mechanism and a timed start-up mechanism;

[0019] S42. Extract the on-board status signal, and when the on-board status signal is less than the on-board status threshold, output a command to shut down the electric pump, and shut down the electric pump according to the command to shut down the electric pump.

[0020] S43. When the on-board status signal is greater than or equal to the on-board status threshold, an electric pump start command or an on-board controlled mechanism logic judgment command is obtained based on the first hydraulic pressure and the low pressure threshold. The second hydraulic pressure is obtained based on the electric pump start command. The electric pump is started or an alarm signal is output based on the second hydraulic pressure and the hydraulic safety threshold through the overpressure protection mechanism and the staggered start mechanism.

[0021] S44. Obtain the flight control system status signal according to the logic judgment instruction of the controlled mechanism on the aircraft, and determine whether the controlled mechanism needs pressure based on the flight control system status signal; if it is determined that there is a pressure requirement, output an electric pump start command, obtain the second hydraulic pressure according to the electric pump start command, and start the electric pump or output an alarm signal according to the second hydraulic pressure and the hydraulic safety threshold through the overpressure protection mechanism and the staggered start mechanism; if it is determined that there is no pressure requirement, shut down the electric pump.

[0022] Further, in steps S43 and S44 above, obtaining the second hydraulic pressure according to the electric pump start command, and starting the electric pump or outputting an alarm signal according to the second hydraulic pressure and the hydraulic safety threshold through the overpressure protection mechanism and the staggered start mechanism, includes:

[0023] The second hydraulic pressure is obtained according to the electric pump start command. The second hydraulic pressure is compared with the hydraulic safety threshold. If the second hydraulic pressure is greater than or equal to the hydraulic safety threshold, the electric pump shut-off command, the start-stop flag and the overpressure alarm signal are output.

[0024] If the second hydraulic pressure is less than the hydraulic safety threshold, a start flag is output, and the electric pump is started through the staggered start mechanism according to the electric pump start command and the start flag.

[0025] Furthermore, the above methods also include:

[0026] Define the starting priority order of the electric pumps connected to all the sub-hydraulic systems in the first group and the second group respectively, give the data waiting time corresponding to each priority level in the priority order, and identify the priority level of the electric pump connected to the sub-hydraulic system corresponding to the first hydraulic pressure according to the priority order;

[0027] The system starts counting based on the start signal of the next higher priority level and the start counter of the priority level. When the count value reaches the data waiting time corresponding to the priority level and the start signal of the next higher priority level is received, the system outputs an electric pump start command to construct the staggered start mechanism.

[0028] 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 onboard controlled mechanisms include landing gear and control surfaces.

[0029] Furthermore, in steps S34 and S44 above, determining whether the controlled mechanism requires pressure based on the flight control system status signal includes:

[0030] 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.

[0031] 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.

[0032] 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.

[0033] This invention also provides a heterogeneous control system for the hydraulic mechanism of a large transport aircraft, including a grouping module, a control logic construction module, a first control unit, and a second control unit.

[0034] The grouping module is used to divide all the sub-hydraulic systems into two groups, each group including at least one of the sub-hydraulic systems;

[0035] The control logic construction module is used to construct a first control logic architecture and a first control logic architecture through various data in the machine state threshold, low pressure threshold, hydraulic safety threshold and sub-hydraulic system relationship table;

[0036] The first control unit is used to automatically control the start and stop of the electric pump installed on each of the sub-hydraulic systems in the first group by adopting the constructed first control logic architecture, based on the on-board status threshold, low pressure threshold, sub-hydraulic system relationship table, the on-board status signal, the flight control system status signal and the first hydraulic pressure of the two associated sub-hydraulic systems.

[0037] The second control unit is used to automatically control the start and stop of the electric pump installed on each of the sub-hydraulic systems in the second group by adopting the constructed second control logic architecture, based on the machine status threshold, the low pressure threshold, the hydraulic safety threshold, the machine status signal, the first hydraulic pressure and the second hydraulic pressure of each of the sub-hydraulic systems in the second group.

[0038] Furthermore, both the first control unit and the second control unit include an acquisition module, a data scheduling module, and multiple control modules; all the control modules in the first control unit are connected in sequence to form a closed-loop architecture, and the control modules of the first control unit include an error prevention module and a timed start-up module; the control modules of the second control unit include a timed start-up module and an overpressure protection module.

[0039] 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:

[0040] 1. By using different control architectures to automatically control the electric pumps of the two sub-hydraulic systems, on the one hand, the pilots do not need to spend a lot of energy on controlling the electric pumps during missions, significantly reducing their workload; on the other hand, it can ensure that if one control architecture malfunctions, the electric pumps can be controlled through the other control architecture, ensuring the normal operation of the hydraulic system and further improving flight safety.

[0041] 2. By automatically controlling the opening and closing of the electric pumps based on the real-time collected aircraft status, the risks of excessive aircraft energy consumption and overpressure damage to the hydraulic system caused by the need to start all electric pumps throughout the process are avoided.

[0042] 3. By designing a heterogeneous integrated control system, the functions of the automatic control system are distributed in two different physical entities, which can support the installation of the two different entities in different areas of the aircraft. This can avoid the complete loss of system functions due to special risk factors such as fire or bird strikes. At the same time, it can also avoid the problem of complete loss of system functions due to common mode failure.

[0043] 4. Protection methods are designed for both the electric pump and the hydraulic transmission system. The first control unit can avoid electric pump control abnormalities caused by the failure of a single control module through a joint decision-making mechanism of control modules, and implement additional protection for the electric pump, significantly enhancing the safety and stability of the system, extending the service life of the electric pump, and thus enhancing aircraft safety. The second control unit periodically monitors the status of the hydraulic transmission system through an overpressure protection module with an independent input source. When a serious failure of the control module causes the electric pump to be erroneously started, the corresponding electric pump is shut down with higher priority, thereby protecting the hydraulic transmission system. At the same time, while ensuring the safety of the hydraulic transmission system, the electric pump is further protected. When the overpressure protection module is given a signal that it can be opened, the start-up time of the electric pump is controlled according to predefined priorities and rules, thereby protecting the electric pump and the aircraft power supply. Attached Figure Description

[0044] 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.

[0045] Figure 1 This is a flowchart of a heterogeneous control method for the hydraulic mechanism of a large transport aircraft disclosed in an embodiment of the present invention;

[0046] Figure 2 This is a flowchart illustrating the control of an electric pump in a first set of sub-hydraulic systems via a first control logic architecture, as disclosed in an embodiment of the present invention.

[0047] Figure 3 This is a flowchart of the error prevention mechanism in the first control logic architecture disclosed in an embodiment of the present invention;

[0048] Figure 4This is a flowchart of the error prevention mechanism and the time-lapse startup mechanism in the first control logic architecture disclosed in the embodiments of the present invention;

[0049] Figure 5 This is a flowchart illustrating the control of the electric pump of the second sub-hydraulic system through a second control logic architecture, as disclosed in an embodiment of the present invention.

[0050] Figure 6 This is a flowchart of the overpressure protection mechanism in the second control logic architecture disclosed in an embodiment of the present invention;

[0051] Figure 7 This is a flowchart of the overpressure protection mechanism and the time-lapse start mechanism in the second control logic architecture disclosed in this embodiment of the invention;

[0052] Figure 8 This is an architecture diagram of a heterogeneous control system for the hydraulic mechanism of a large transport aircraft disclosed in an embodiment of the present invention;

[0053] Figure 9 This is a schematic diagram of the first control unit and the second control unit disclosed in an embodiment of the present invention;

[0054] Figure 10 This is a schematic diagram of a computer device disclosed in an embodiment of the present invention;

[0055] Among them, 801 is the grouping module; 802 is the control logic construction module; 803 is the first control unit; 804 is the second control unit; 1 is the acquisition module; 2 is the data scheduling module; 3 is the control module; 31 is the error prevention module; 32 is the timed start module; 33 is the overpressure protection module; 101 is the memory; and 102 is the processor. Detailed Implementation

[0056] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0057] 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.

[0058] This invention discloses a heterogeneous control method for the hydraulic mechanism of a large transport aircraft. The hydraulic system includes multiple sub-hydraulic systems, each equipped with an electric pump. The method controls each of the electric pumps. (See also...) Figure 1 As shown, the method includes:

[0059] S1. Divide all the sub-hydraulic systems into two groups, each group including at least one of the sub-hydraulic systems;

[0060] S2. Real-time acquisition of onboard status signals, flight control system status signals, and the first and second hydraulic pressures of each of the sub-hydraulic systems;

[0061] S3. Using the constructed first control logic architecture, based on the onboard status threshold, low pressure threshold, sub-hydraulic system relationship table, the onboard status signal, the flight control system status signal, and the first hydraulic pressure of the two associated sub-hydraulic systems, the electric pump installed on each of the sub-hydraulic systems in the first group is automatically controlled to start and stop.

[0062] S4. Using the constructed second control logic architecture, based on the machine status threshold, the low pressure threshold, the hydraulic safety threshold, the machine status signal, the first hydraulic pressure and the second hydraulic pressure of each of the sub-hydraulic systems in the second group, the electric pump installed on each of the sub-hydraulic systems in the second group is automatically controlled to start and stop.

[0063] Furthermore, in step S3 above, see... Figure 2 , Figure 3 and Figure 4 As shown, using the constructed first control logic architecture, based on the onboard state threshold, low pressure threshold, sub-hydraulic system relationship table, the onboard state signal, the flight control system state signal, and the first hydraulic pressure of the two associated sub-hydraulic systems, the automatic start-stop control of the electric pump installed on each of the sub-hydraulic systems in the first group is performed, including:

[0064] S31. Construct a first control logic architecture that includes an error prevention working mechanism and a mistime start mechanism, and establish a sub-hydraulic system relationship table for all the sub-hydraulic systems in the first group;

[0065] S32. Extract the machine status signal. When the machine status signal is less than the machine status threshold, output a command to shut down the electric pump. Based on the command to shut down the electric pump and the electric pump control result of the sub-hydraulic system associated with the controlled sub-hydraulic system, shut down the electric pump or output an alarm signal based on the error prevention mechanism and the sub-hydraulic system relationship table.

[0066] S33. When the machine status signal is greater than or equal to the machine status threshold, an electric pump start command or a machine-controlled mechanism logic judgment command is obtained based on the first hydraulic pressure and the low pressure threshold. Based on the electric pump start command and the electric pump control result, the electric pump is started or an alarm signal is output through the error prevention working mechanism and the staggered start mechanism.

[0067] S34. Obtain the flight control system status signal according to the logic judgment instruction of the controlled mechanism on the aircraft, and determine whether the controlled mechanism needs pressure based on the flight control system status signal; if it is determined that there is a pressure requirement, output an electric pump start command, and start the electric pump or output an alarm signal according to the electric pump start command and the electric pump control result through the error prevention working mechanism and the staggered start mechanism; if it is determined that there is no pressure requirement, shut down the electric pump based on the error prevention working mechanism.

[0068] Furthermore, in step S32 above, see... Figure 3 and Figure 4 As shown, based on the electric pump shutdown command and the electric pump control result of the sub-hydraulic system associated with the controlled sub-hydraulic system, the electric pump is shut down or an alarm signal is output based on the error prevention mechanism and the sub-hydraulic system relationship table. This includes: determining the consistency between the electric pump shutdown command and the electric pump control result; if the determination is consistent, the electric pump is shut down according to the electric pump shutdown command; if the determination is inconsistent, an alarm signal is output.

[0069] In steps S33 and S34 above, see... Figure 3 and Figure 4 As shown, the process of starting the electric pump or outputting an alarm signal based on the electric pump start command and the electric pump control result through the error prevention mechanism and the staggered start mechanism includes: determining the consistency between the electric pump start command and the electric pump control result; if the determination is consistent, starting the electric pump based on the electric pump start command through the staggered start mechanism; if the determination is inconsistent, outputting an alarm signal.

[0070] Furthermore, in step S4 above, see... Figure 5 , Figure 6 and Figure 7 As shown, the constructed second control logic architecture, based on the machine status threshold, the low pressure threshold, the hydraulic safety threshold, the machine status signal, and the first and second hydraulic pressures of each sub-hydraulic system in the second group, performs automatic start-stop control of the electric pump installed on each sub-hydraulic system in the second group, including:

[0071] S41. Construct a second control logic architecture that includes an overpressure protection mechanism and a timed start-up mechanism;

[0072] S42. Extract the on-board status signal, and when the on-board status signal is less than the on-board status threshold, output a command to shut down the electric pump, and shut down the electric pump according to the command to shut down the electric pump.

[0073] S43. When the on-board status signal is greater than or equal to the on-board status threshold, an electric pump start command or an on-board controlled mechanism logic judgment command is obtained based on the first hydraulic pressure and the low pressure threshold. The second hydraulic pressure is obtained based on the electric pump start command. The electric pump is started or an alarm signal is output based on the second hydraulic pressure and the hydraulic safety threshold through the overpressure protection mechanism and the staggered start mechanism.

[0074] S44. Obtain the flight control system status signal according to the logic judgment instruction of the controlled mechanism on the aircraft, and determine whether the controlled mechanism needs pressure based on the flight control system status signal; if it is determined that there is a pressure requirement, output an electric pump start command, obtain the second hydraulic pressure according to the electric pump start command, and start the electric pump or output an alarm signal according to the second hydraulic pressure and the hydraulic safety threshold through the overpressure protection mechanism and the staggered start mechanism; if it is determined that there is no pressure requirement, shut down the electric pump.

[0075] Furthermore, in steps S43 and S44 above, see... Figure 6 and Figure 7 As shown, the second hydraulic pressure is obtained according to the electric pump start command, and the electric pump is started or an alarm signal is output according to the second hydraulic pressure and the hydraulic safety threshold through the overpressure protection mechanism and the staggered start mechanism, including:

[0076] The second hydraulic pressure is obtained according to the electric pump start command. The second hydraulic pressure is compared with the hydraulic safety threshold. If the second hydraulic pressure is greater than or equal to the hydraulic safety threshold, the electric pump shut-off command, the start-stop flag and the overpressure alarm signal are output.

[0077] If the second hydraulic pressure is less than the hydraulic safety threshold, a start flag is output, and the electric pump is started through the staggered start mechanism according to the electric pump start command and the start flag.

[0078] Furthermore, see Figure 4 and Figure 7 As shown, the above method also includes:

[0079] Define the starting priority order of the electric pumps connected to all the sub-hydraulic systems in the first group and the second group respectively, give the data waiting time corresponding to each priority level in the priority order, and identify the priority level of the electric pump connected to the sub-hydraulic system corresponding to the first hydraulic pressure according to the priority order;

[0080] The system starts counting based on the start signal of the next higher priority level and the start counter of the priority level. When the count value reaches the data waiting time corresponding to the priority level and the start signal of the next higher priority level is received, the system outputs an electric pump start command to construct the staggered start mechanism.

[0081] 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 onboard controlled mechanisms include landing gear and control surfaces.

[0082] Furthermore, in steps S34 and S44 above, see... Figure 2 and Figure 5 As shown, determining whether the controlled mechanism requires pressure based on the flight control system status signal includes:

[0083] 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.

[0084] 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.

[0085] 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.

[0086] Based on the same inventive concept, this invention also provides a heterogeneous control system for the hydraulic mechanism of a large transport aircraft, as described in the following embodiments. Since the principle of solving the problem in the heterogeneous control system for the hydraulic mechanism of a large transport aircraft is similar to the heterogeneous control method for the hydraulic mechanism of a large transport aircraft disclosed in the above embodiments, the implementation of the heterogeneous control system for the hydraulic mechanism of a large transport aircraft can refer to the implementation of the heterogeneous control method for the hydraulic mechanism of a large transport aircraft, and repeated details will not be elaborated further. 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.

[0087] Figure 8 This is a structural block diagram of a heterogeneous control system for the hydraulic mechanism of a large transport aircraft disclosed in an embodiment of the present invention, such as... Figure 8 As shown, the heterogeneous control system of the hydraulic mechanism includes a grouping module 801, a control logic construction module 802, a first control unit 803, and a second control unit 804. The structure is described below.

[0088] The grouping module 801 is used to divide all the sub-hydraulic systems into two groups, each group including at least one of the sub-hydraulic systems;

[0089] The control logic construction module 802 is used to construct a first control logic architecture and a first control logic architecture through various data in the machine state threshold, low pressure threshold, hydraulic safety threshold and sub-hydraulic system relationship table;

[0090] The first control unit 803 is used to automatically control the start and stop of the electric pump installed on each of the sub-hydraulic systems in the first group by adopting the constructed first control logic architecture, based on the on-board status threshold, low pressure threshold, sub-hydraulic system relationship table, the on-board status signal, the flight control system status signal and the first hydraulic pressure of the two associated sub-hydraulic systems.

[0091] The second control unit 804 is used to employ the constructed second control logic architecture to automatically control the start and stop of the electric pump installed on each of the sub-hydraulic systems in the second group based on the machine status threshold, the low pressure threshold, the hydraulic safety threshold, the machine status signal, the first hydraulic pressure and the second hydraulic pressure of each of the sub-hydraulic systems in the second group.

[0092] Furthermore, see Figure 9 As shown, both the first control unit 801 and the second control unit 802 include a data acquisition module 1, a data scheduling module 2, and multiple control modules 3. Each sub-hydraulic system is connected to a control module 3. All the control modules 3 in the first control unit 801 are connected in sequence to form a closed-loop architecture. The control module 3 of the first control unit 801 includes an error prevention module 31 and a staggered start module 32. The control module 3 of the second control unit 802 includes a staggered start module 32 and an overpressure protection module 33.

[0093] 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:

[0094] 1. By using different control architectures to automatically control the electric pumps of the two sub-hydraulic systems, on the one hand, the pilots do not need to spend a lot of energy on controlling the electric pumps during missions, significantly reducing their workload; on the other hand, it can ensure that if one control architecture malfunctions, the electric pumps can be controlled through the other control architecture, ensuring the normal operation of the hydraulic system and further improving flight safety.

[0095] 2. By automatically controlling the opening and closing of the electric pumps based on the real-time collected aircraft status, the risks of excessive aircraft energy consumption and overpressure damage to the hydraulic system caused by the need to start all electric pumps throughout the process are avoided.

[0096] 3. By designing a heterogeneous integrated control system, the functions of the automatic control system are distributed in two different physical entities, which can support the installation of the two different entities in different areas of the aircraft. This can avoid the complete loss of system functions due to special risk factors such as fire or bird strikes. At the same time, it can also avoid the problem of complete loss of system functions due to common mode failure.

[0097] 4. Protection methods are designed for both the electric pump and the hydraulic transmission system. The first control unit can avoid electric pump control abnormalities caused by the failure of a single control module through a joint decision-making mechanism of control modules, and implement additional protection for the electric pump, significantly enhancing the safety and stability of the system, extending the service life of the electric pump, and thus enhancing aircraft safety. The second control unit periodically monitors the status of the hydraulic transmission system through an overpressure protection module with an independent input source. When a serious failure of the control module causes the electric pump to be erroneously started, the corresponding electric pump is shut down with higher priority, thereby protecting the hydraulic transmission system. At the same time, while ensuring the safety of the hydraulic transmission system, the electric pump is further protected. When the overpressure protection module is given a signal that it can be opened, the start-up time of the electric pump is controlled according to predefined priorities and rules, thereby protecting the electric pump and the aircraft power supply.

[0098] In this embodiment, a computer device is provided, such as... Figure 10 As shown, it includes a memory 101, a processor 102, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the above-mentioned heterogeneous control method for the hydraulic mechanism of any large transport aircraft.

[0099] Specifically, the computer device can be a computer terminal, a server, or a similar computing device.

[0100] In this embodiment, a computer-readable storage medium is provided, which stores a computer program that executes the above-described heterogeneous control method for the hydraulic mechanism of any of the large transport aircraft.

[0101] Specifically, computer-readable storage media include both permanent and non-permanent, removable and non-removable media that can store information using any method or technology. Information can be computer-readable instructions, data structures, program modules, or other data. Examples of computer-readable storage media include, but are not limited to, phase-change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technologies, CD-ROM, digital versatile optical disc (DVD) or other optical storage, magnetic tape, magnetic disk storage or other magnetic storage devices, or any other non-transfer medium that can be used to store information accessible by a computing device. As defined herein, computer-readable storage media do not include transient computer-readable media, such as modulated data signals and carrier waves.

[0102] Obviously, those skilled in the art should understand that the modules or steps of the above-described embodiments of the present invention can be implemented using general-purpose computing devices. They can be centralized on a single computing device or distributed across a network of multiple computing devices. Optionally, they can be implemented using computer-executable program code, thereby storing them in a storage device for execution by a computing device. In some cases, the steps shown or described can be performed in a different order than those presented here, or they can be fabricated as separate integrated circuit modules, or multiple modules or steps can be fabricated as a single integrated circuit module. Thus, the embodiments of the present invention are not limited to any particular hardware and software combination.

[0103] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, various modifications and variations can be made to the embodiments of the present invention. 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 hydraulic mechanism heterogeneous control method for a large transport aircraft, a plurality of sub-hydraulic systems being included in a hydraulic system, an electric pump being provided on each of the sub-hydraulic systems, characterized by, The method controls each of the electric pumps, and the method comprises: dividing all the sub-hydraulic systems into two groups, each group comprising at least one of the sub-hydraulic systems; collecting, in real time, an on-board state signal, a flight control system state signal, and first and second hydraulic pressures of each of the sub-hydraulic systems; controlling, by using a first control logic architecture, an electric pump arranged on each of the sub-hydraulic systems in the first group according to the on-board state threshold, the low-pressure threshold, a sub-hydraulic system relationship table, the on-board state signal, the flight control system state signal, and the first hydraulic pressure of the two associated sub-hydraulic systems; controlling, by using a second control logic architecture, an electric pump arranged on each of the sub-hydraulic systems in the second group according to the on-board state threshold, the low-pressure threshold, a hydraulic safety threshold, the on-board state signal, the first and second hydraulic pressures of each of the sub-hydraulic systems in the second group.

2. The method of claim 1, wherein, controlling, by using a first control logic architecture, an electric pump arranged on each of the sub-hydraulic systems in the first group according to the on-board state threshold, the low-pressure threshold, a sub-hydraulic system relationship table, the on-board state signal, the flight control system state signal, and the first hydraulic pressure of the two associated sub-hydraulic systems, comprises: constructing a first control logic architecture comprising an error prevention mechanism and a staggered starting mechanism, and establishing the sub-hydraulic system relationship table of all the sub-hydraulic systems in the first group; extracting the on-board state signal, outputting a close electric pump instruction when the on-board state signal is less than the on-board state threshold, and closing an electric pump or outputting an alarm signal based on the error prevention mechanism and the sub-hydraulic system relationship table according to the close electric pump instruction and an electric pump control result of a sub-hydraulic system associated with the controlled sub-hydraulic system; when the on-board state signal is greater than or equal to the on-board state threshold, obtaining an electric pump opening instruction or an on-board controlled mechanism logic judgment instruction according to the first hydraulic pressure and the low-pressure threshold, opening an electric pump or outputting an alarm signal by using the error prevention mechanism and the staggered starting mechanism according to the electric pump opening instruction and the electric pump control result; acquiring a flight control system state signal according to the on-board controlled mechanism logic judgment instruction, judging whether a controlled mechanism needs pressure according to the flight control system state signal, outputting an electric pump opening instruction if it is judged that pressure is needed, opening an electric pump or outputting an alarm signal by using the error prevention mechanism and the staggered starting mechanism according to the electric pump opening instruction and the electric pump control result, and closing an electric pump based on the error prevention mechanism if it is judged that pressure is not needed.

3. The method of claim 2, wherein, closing an electric pump or outputting an alarm signal based on the error prevention mechanism and the sub-hydraulic system relationship table according to the close electric pump instruction and an electric pump control result of a sub-hydraulic system associated with the controlled sub-hydraulic system, comprises: The consistency of the electric pump closing instruction and the electric pump control result is judged, if consistent, the electric pump is closed according to the electric pump closing instruction, if inconsistent, an alarm signal is outputted; The consistency of the electric pump opening instruction and the electric pump control result is judged, if consistent, the electric pump is opened according to the electric pump opening instruction through the time-delay starting mechanism, if inconsistent, an alarm signal is outputted.

4. The method of heterogeneous control of hydraulic systems of a large transport category aircraft of claim 1, wherein, The second control logic architecture is constructed, and the on-off automatic control of the electric pump arranged on each of the sub-hydraulic systems in the second group is performed according to the on-board state threshold, the low pressure threshold, the hydraulic safety threshold, the on-board state signal, the first hydraulic pressure and the second hydraulic pressure of each of the sub-hydraulic systems in the second group, including: The second control logic architecture including the anti-overpressure protection mechanism and the time-delay starting mechanism is constructed; The on-board state signal is extracted, and an electric pump closing instruction is outputted when the on-board state signal is less than the on-board state threshold, and the electric pump is closed according to the electric pump closing instruction; When the on-board state signal is greater than or equal to the on-board state threshold, an electric pump opening instruction or an on-board controlled mechanism logical judgment instruction is obtained according to the first hydraulic pressure and the low pressure threshold, the second hydraulic pressure is obtained according to the electric pump opening instruction, and the electric pump is opened or an alarm signal is outputted according to the second hydraulic pressure and the hydraulic safety threshold through the anti-overpressure protection mechanism and the time-delay starting mechanism; The flight control system state signal is obtained according to the on-board controlled mechanism logical judgment instruction, and it is judged whether the controlled mechanism needs pressure according to the flight control system state signal; if it is judged that pressure is needed, an electric pump opening instruction is outputted, the second hydraulic pressure is obtained according to the electric pump opening instruction, and the electric pump is opened or an alarm signal is outputted according to the second hydraulic pressure and the hydraulic safety threshold through the anti-overpressure protection mechanism and the time-delay starting mechanism; if it is judged that pressure is not needed, the electric pump is closed.

5. The method of heterogeneous control of hydraulic mechanisms of a large transport aircraft according to claim 4, characterized by The second hydraulic pressure is obtained according to the electric pump opening instruction, and the electric pump is opened or an alarm signal is outputted according to the second hydraulic pressure and the hydraulic safety threshold through the anti-overpressure protection mechanism and the time-delay starting mechanism, including: The second hydraulic pressure is obtained according to the electric pump opening instruction, and the second hydraulic pressure is compared with the hydraulic safety threshold, if the second hydraulic pressure is greater than or equal to the hydraulic safety threshold, an electric pump closing instruction, a starting termination flag and an overpressure alarm signal are outputted; If the second hydraulic pressure is less than the hydraulic safety threshold, a starting flag is outputted, and the electric pump is opened according to the electric pump opening instruction and the starting flag through the time-delay starting mechanism.

6. The method of claim 2-5, wherein, The method further includes: The priority order of starting the electric pump connected to each of the sub-hydraulic systems in the first group and the second group is defined respectively, a data waiting time corresponding to each priority level in the priority order is given, and the priority level of the electric pump connected to the sub-hydraulic system corresponding to the first hydraulic pressure is identified according to the priority order; According to the starting signal of the upper priority level of the priority level and the starting counter of the priority level, the starting counter starts counting, when the counting value reaches the data waiting time corresponding to the priority level, and the starting signal of the upper priority level of the priority level is received, an electric pump starting instruction is output, and the staggered starting mechanism is constructed.

7. The method of claim 2-5, wherein, The flight control system state signal includes a landing gear signal and a control surface state signal, the on-board state signal includes a ground speed signal, and the controlled mechanism includes a landing gear and a control surface.

8. The method of heterogeneous control of hydraulic mechanisms of a large transport aircraft according to claim 7, characterized by According to the flight control system state signal, it is determined whether the controlled mechanism needs pressure, including: According to the landing gear signal, it is determined whether the landing gear needs pressure, if the landing gear signal is a retracting signal or a lowering signal, it is determined that the landing gear needs pressure; According to the control surface state signal, it is determined whether the control surface needs pressure, if the control surface state signal is a control surface position changing signal, it is determined that the control surface needs pressure; When any one or both of the control surface and the landing gear needs pressure, it is determined that the controlled mechanism needs pressure.

9. A hydraulic mechanism isomerism control system of a large transport category aircraft for executing the hydraulic mechanism isomerism control method according to any one of claims 1 to 8, characterized by, Including: A grouping module is used to divide all the sub-hydraulic systems into two groups, each group including at least one sub-hydraulic system; A control logic construction module is used to construct a first control logic architecture and a second control logic architecture by using multiple types of on-board state thresholds, low pressure thresholds, hydraulic safety thresholds, and sub-hydraulic system relationship tables; A first control unit is used to adopt the constructed first control logic architecture, and according to the on-board state thresholds, the low pressure thresholds, the sub-hydraulic system relationship table, the on-board state signal, the flight control system state signal, and the first hydraulic pressure of the two associated sub-hydraulic systems, to automatically control the starting and stopping of the electric pump arranged on each of the sub-hydraulic systems in the first group; A second control unit is used to adopt the constructed second control logic architecture, and according to the on-board state thresholds, the low pressure thresholds, the hydraulic safety thresholds, the on-board state signal, the first hydraulic pressure and the second hydraulic pressure of each of the sub-hydraulic systems in the second group, to automatically control the starting and stopping of the electric pump arranged on each of the sub-hydraulic systems in the second group.

10. The hydraulic architecture heterogeneous control system of a large transport category aircraft of claim 9, wherein, The first control unit and the second control unit each include an acquisition module, a data scheduling module, and multiple control modules; all the control modules in the first control unit are connected in sequence to form a closed loop architecture, the control modules of the first control unit include an error prevention module and a staggered starting module; the control modules of the second control unit include a staggered starting module and an overpressure protection module.

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