Heterogeneous control method and system for hydraulic mechanism of large transportation aircraft

Abstract

The invention belongs to the field of airborne electromechanics, and discloses a hydraulic mechanism heterogeneous control method and system.The method comprises the steps that hydraulic systems are divided into two groups, and on-board state signals, flight control system state signals and first hydraulic pressure and second hydraulic pressure of sub hydraulic systems are collected; giving an on-board state threshold value, a low-pressure threshold value, a hydraulic safety threshold value and a sub-hydraulic system relation table; starting and stopping automatic control is conducted on the electric pumps in the first group through the established first control logic architecture according to the data; and the electric pumps in the second group are automatically controlled to start and stop by adopting the constructed second control logic architecture through the data. The system comprises a grouping module, a control logic construction module and two control units, wherein each control unit comprises an acquisition module, a data scheduling module, a staggered starting module, an anti-overvoltage protection module and an anti-error working module. All the electric pumps are controlled through two heterogeneous logic architectures, and the control precision and safety are improved.

Description

Technical Field

[0001] The present invention belongs to the field of airborne electromechanical systems, and relates to hydraulic mechanism control technology, and in particular to a hydraulic mechanism heterogeneous control method and system for a large transport aircraft. Background Art

[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 liquid power to the hydraulic transmission system to drive and control various aircraft mechanisms, such as landing gear, rudder control, etc. The hydraulic system has the characteristics of high frequency of use and high system safety requirements when large transport aircraft are flying. At present, most of them are controlled by automation to improve energy efficiency and reduce safety hazards.

[0003] However, at present, all redundant sub-hydraulic systems in the hydraulic system are controlled by the same control logic. If their safety design is not considered, when external special risks or common mode risks occur, control abnormalities may occur, resulting in the loss of corresponding functions or errors, affecting the normal operation of the mechanism, and even causing catastrophic consequences in severe cases.

[0004] In addition, due to the high complexity of the hydraulic system itself, it is difficult to ensure that there will be no abnormalities during long-term operation, and 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 erroneous instructions causing the hydraulic transmission system to be over-pressurized and damaged, or under-pressurized and unable to drive the mechanism to work. Summary of the invention

[0005] In order to solve the technical problems that the hydraulic system of a large transport aircraft controls all electric pumps through the same control logic, which easily leads to abnormal control and causes the loss of corresponding functions or errors that affect the normal operation of the mechanism, and even causes catastrophic consequences in serious cases, the present invention discloses a heterogeneous control method for a hydraulic mechanism of a large transport aircraft, wherein the hydraulic system includes a plurality of sub-hydraulic systems, each of which is provided with an electric pump, and the method controls each of the electric pumps, and the method includes:

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

[0007] S2, collecting on-board status signals, flight control system status signals, and the first hydraulic pressure and the second hydraulic pressure of each of the sub-hydraulic systems in real time;

[0008] S3, using the constructed first control logic architecture, according to the onboard state threshold, the low pressure threshold, the 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, automatically controlling the start and stop of the electric pump provided on each of the sub-hydraulic systems in the first group;

[0009] S4. Adopting the constructed second control logic architecture, the electric pump provided on each of the sub-hydraulic systems in the second group is automatically started and stopped according to the on-board status threshold, the low pressure threshold, the hydraulic safety threshold, the on-board status signal, the first hydraulic pressure and the second hydraulic pressure of each of the sub-hydraulic systems in the second group.

[0010] Furthermore, in the above step S3, the first control logic architecture is constructed, and the electric pump provided on each of the sub-hydraulic systems in the first group is automatically started and stopped according to the onboard state threshold, the low pressure threshold, the 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, including:

[0011] S31, constructing a first control logic architecture including an anti-error working mechanism and a staggered start mechanism, and establishing a sub-hydraulic system relationship table of all the sub-hydraulic systems in the first group;

[0012] S32, extracting the on-board status signal, outputting an electric pump shut-down instruction when the on-board status signal is less than the on-board status threshold, shutting down the electric pump or outputting an alarm signal based on the error prevention working mechanism and the sub-hydraulic system relationship table according to the electric pump shut-down instruction and the electric pump control result of the sub-hydraulic system associated with the controlled sub-hydraulic system;

[0013] S33, when the on-board status signal is greater than or equal to the on-board status threshold, obtaining an electric pump start instruction or an on-board controlled mechanism logic judgment instruction according to the first hydraulic pressure and the low-pressure threshold, and starting the electric pump or outputting an alarm signal through the anti-error working mechanism and the staggered start mechanism according to the electric pump start instruction and the electric pump control result;

[0014] S34. Acquire the flight control system status signal according to the logic judgment instruction of the controlled mechanism on the aircraft, and judge whether the controlled mechanism needs pressure according to the flight control system status signal; if it is judged that there is a pressure demand, output the electric pump start instruction, and according to the electric pump start instruction and the electric pump control result, turn on the electric pump or output an alarm signal through the anti-error working mechanism and the staggered start mechanism; if it is judged that there is no pressure demand, turn off the electric pump based on the anti-error working mechanism.

[0015] Furthermore, in the above step S32, according to the electric pump shut-down instruction 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 anti-error working mechanism and the sub-hydraulic system relationship table, including: judging the consistency of the electric pump shut-down instruction and the electric pump control result, if the judgment is consistent, shutting down the electric pump according to the electric pump shut-down instruction, if the judgment is inconsistent, outputting an alarm signal.

[0016] In the above-mentioned step S33 and step S34, the electric pump is turned on or an alarm signal is output through the anti-error working mechanism and the staggered start mechanism according to the electric pump start instruction and the electric pump control result, including: judging the consistency of the electric pump start instruction and the electric pump control result, if the judgment is consistent, the electric pump is turned on through the staggered start mechanism according to the electric pump start instruction, and if the judgment is inconsistent, an alarm signal is output.

[0017] Furthermore, in the above step S4, the constructed second control logic architecture is adopted to automatically start and stop the electric pump provided on each of the sub-hydraulic systems in the second group 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:

[0018] S41, constructing a second control logic architecture including an overpressure protection mechanism and a staggered start mechanism;

[0019] S42, extracting the onboard status signal, outputting an electric pump shut-down instruction when the onboard status signal is less than the onboard status threshold, and shutting down the electric pump according to the electric pump shut-down instruction;

[0020] S43, when the onboard status signal is greater than or equal to the onboard status threshold, obtaining an electric pump start instruction or an onboard controlled mechanism logic judgment instruction according to the first hydraulic pressure and the low pressure threshold, obtaining the second hydraulic pressure according to the electric pump start instruction, and starting the electric pump or outputting an alarm signal through the anti-overpressure protection mechanism and the staggered start mechanism according to the second hydraulic pressure and the hydraulic safety threshold;

[0021] S44. Acquire the flight control system status signal according to the logic judgment instruction of the controlled mechanism on the aircraft, and judge whether the controlled mechanism needs pressure according to the flight control system status signal; if it is judged that there is a pressure demand, output the electric pump start instruction, obtain the second hydraulic pressure according to the electric pump start instruction, and start the electric pump or output an alarm signal through the anti-overpressure protection mechanism and the staggered start mechanism according to the second hydraulic pressure and the hydraulic safety threshold; if it is judged that there is no pressure demand, turn off the electric pump.

[0022] Furthermore, in the above step S43 and step S44, the second hydraulic pressure is obtained according to the electric pump start instruction, and the electric pump is started or an alarm signal is output through the anti-overpressure protection mechanism and the staggered start mechanism according to the second hydraulic pressure and the hydraulic safety threshold, including:

[0023] Acquire the second hydraulic pressure according to the electric pump start instruction, compare the second hydraulic pressure with the hydraulic safety threshold, and output the electric pump shutdown instruction, the start termination flag and the overpressure alarm signal if the second hydraulic pressure is greater than or equal to the hydraulic safety threshold;

[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 instruction and the start flag.

[0025] Furthermore, the above method also includes:

[0026] respectively defining a priority order for starting the electric pumps connected to all the sub-hydraulic systems in the first group and the second group, giving a data waiting time corresponding to each priority level in the priority order, and identifying 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 counting starts according to the start signal of the priority level before the priority level and the priority level start counter. When the count value reaches the data waiting time corresponding to the priority level and the start signal of the priority level before the priority level is received, the electric pump start instruction is output to construct the staggered start mechanism.

[0028] Furthermore, the flight control system status signal includes a landing gear signal and a control surface status signal, the onboard status signal includes a ground speed signal, and the onboard controlled mechanism includes a landing gear and a control surface.

[0029] Furthermore, in the above step S34 and step S44, judging whether the controlled mechanism needs pressure according to the flight control system state signal includes:

[0030] Determining whether the landing gear has a pressure requirement according to the landing gear signal, and if the landing gear signal is a retracting signal or a lowering signal, determining that the landing gear has a pressure requirement;

[0031] Determine whether the rudder surface has a pressure requirement according to the rudder surface state signal, and if the rudder surface state signal is a rudder surface position change signal, determine that the rudder surface has a pressure requirement;

[0032] When any one or both of the control surface and the landing gear have pressure requirements, it is determined that the controlled mechanism needs pressure.

[0033] An embodiment of the present invention further provides a heterogeneous control system for a hydraulic mechanism of a large transport aircraft, comprising a grouping module, a control logic building module, a first control unit and a second control unit.

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

[0035] The control logic construction module is used to construct a first control logic architecture and a second control logic architecture through multiple on-board state thresholds, low pressure thresholds, hydraulic safety thresholds, and sub-hydraulic system relationship tables;

[0036] The first control unit is used to adopt the constructed first control logic architecture to automatically start and stop the electric pump provided on each of the sub-hydraulic systems in the first group according to the onboard state threshold, the low pressure threshold, the 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;

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

[0038] Furthermore, the first control unit and the second control unit both 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 anti-error working module and a staggered start module; the control modules of the second control unit include a staggered start module and an anti-overpressure protection module.

[0039] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above technical solutions adopted in the embodiments of this specification include at least:

[0040] 1. By using different control architectures to automatically control the electric pumps of the two sub-hydraulic systems, the pilots do not need to spend a lot of energy on controlling the electric pumps during the mission, which significantly reduces the pilot's workload. On the other hand, it can ensure that when one control architecture is abnormal, the electric pump can be controlled by another control architecture to ensure the normal operation of the hydraulic system and further improve flight safety.

[0041] 2. Automatically control the opening and closing of electric pumps based on the aircraft status collected in real time, thus avoiding the risk of excessive energy consumption and overpressure damage to the hydraulic system caused by the need to start all electric pumps throughout the entire process;

[0042] 3. Through the design of heterogeneous integrated control systems, the functions of the automatic control system are distributed in two different physical entities, which can support the installation of 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 and bird strikes. At the same time, it can also avoid the problem of complete loss of system functions due to common mode failures;

[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 abnormalities in a single control module through a joint decision-making mechanism of the control modules, and implement additional protection for the electric pump, which significantly enhances the safety and stability of the system, increases the service life of the electric pump, and thereby enhances the safety of the aircraft; the second control unit periodically monitors the status of the hydraulic transmission system by designing an anti-overpressure protection module with an independent input source, and when a serious fault in the control module causes the electric pump to be erroneously turned on, the corresponding electric pump is turned off with a 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 anti-overpressure protection module is turned on, the start-up of the electric pump is time-controlled according to pre-defined priorities and rules, thereby protecting the electric pump and the onboard power supply. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0045] Figure 1 It is a flow chart of a method for controlling a hydraulic mechanism heterogeneity of a large transport aircraft disclosed in an embodiment of the present invention;

[0046] Figure 2 A flowchart of controlling the electric pump of the first group of sub-hydraulic systems through the first control logic architecture disclosed in an embodiment of the present invention;

[0047] Figure 3 A flow chart of an error prevention working mechanism in a first control logic architecture disclosed in an embodiment of the present invention;

[0048] Figure 4A flow chart of an anti-error working mechanism and a staggered start-up mechanism in a first control logic architecture disclosed in an embodiment of the present invention;

[0049] Figure 5 A flow chart of controlling the electric pump of the second group of sub-hydraulic systems through the second control logic architecture disclosed in an embodiment of the present invention;

[0050] Figure 6 A flow chart of an overpressure protection mechanism in a second control logic architecture disclosed in an embodiment of the present invention;

[0051] Figure 7 A flow chart of an overpressure protection mechanism and a staggered start mechanism in a second control logic architecture disclosed in an embodiment of the present invention;

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

[0053] Fig. 9 A schematic diagram of a first control unit and a second control unit disclosed in an embodiment of the present invention;

[0054] Fig.10 A schematic diagram of a computer device disclosed in an embodiment of the present invention;

[0055] Among them, 801, grouping module; 802, control logic building module; 803, first control unit; 804, second control unit; 1, acquisition module; 2, data scheduling module; 3, control module; 31, anti-error working module; 32, staggered start module; 33, anti-overpressure protection module; 101, memory; 102, processor. DETAILED DESCRIPTION

[0056] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0057] The following describes the implementation methods of the present application through specific specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that the following embodiments and the features of the embodiments can be combined with each other in the absence of conflict. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0058] The present invention discloses a method for controlling a hydraulic mechanism heterogeneity of a large transport aircraft. The hydraulic system includes a plurality of sub-hydraulic systems, each of which is provided with an electric pump. The method controls each of the electric pumps. Figure 1 As shown, the method includes:

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

[0060] S2, collecting on-board status signals, flight control system status signals, and the first hydraulic pressure and the second hydraulic pressure of each of the sub-hydraulic systems in real time;

[0061] S3, using the constructed first control logic architecture, according to the onboard state threshold, the low pressure threshold, the 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, automatically controlling the start and stop of the electric pump provided on each of the sub-hydraulic systems in the first group;

[0062] S4. Adopting the constructed second control logic architecture, the electric pump provided on each of the sub-hydraulic systems in the second group is automatically started and stopped according to the on-board status threshold, the low pressure threshold, the hydraulic safety threshold, the on-board status signal, the first hydraulic pressure and the second hydraulic pressure of each of the sub-hydraulic systems in the second group.

[0063] Further, in the above step S3, see Figure 2 , Figure 3 and Figure 4 As shown, the first control logic architecture is constructed, and the electric pump provided on each of the sub-hydraulic systems in the first group is automatically started and stopped according to the on-board state threshold, the low pressure threshold, 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, including:

[0064] S31, constructing a first control logic architecture including an anti-error working mechanism and a staggered start mechanism, and establishing a sub-hydraulic system relationship table of all the sub-hydraulic systems in the first group;

[0065] S32, extracting the on-board status signal, outputting an electric pump shut-down instruction when the on-board status signal is less than the on-board status threshold, shutting down the electric pump or outputting an alarm signal based on the error prevention working mechanism and the sub-hydraulic system relationship table according to the electric pump shut-down instruction and the electric pump control result of the sub-hydraulic system associated with the controlled sub-hydraulic system;

[0066] S33, when the on-board status signal is greater than or equal to the on-board status threshold, obtaining an electric pump start instruction or an on-board controlled mechanism logic judgment instruction according to the first hydraulic pressure and the low-pressure threshold, and starting the electric pump or outputting an alarm signal through the anti-error working mechanism and the staggered start mechanism according to the electric pump start instruction and the electric pump control result;

[0067] S34. Acquire the flight control system status signal according to the logic judgment instruction of the controlled mechanism on the aircraft, and judge whether the controlled mechanism needs pressure according to the flight control system status signal; if it is judged that there is a pressure demand, output the electric pump start instruction, and according to the electric pump start instruction and the electric pump control result, turn on the electric pump or output an alarm signal through the anti-error working mechanism and the staggered start mechanism; if it is judged that there is no pressure demand, turn off the electric pump based on the anti-error working mechanism.

[0068] Further, in the above step S32, see Figure 3 and Figure 4 As shown, according to the electric pump shut-down instruction 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 anti-error working mechanism and the sub-hydraulic system relationship table, including: judging the consistency of the electric pump shut-down instruction and the electric pump control result, if the judgment is consistent, shutting down the electric pump according to the electric pump shut-down instruction, if the judgment is inconsistent, outputting an alarm signal.

[0069] In the above steps S33 and S34, see Figure 3 and Figure 4 As shown, the electric pump is started or an alarm signal is output according to the electric pump start-up instruction and the electric pump control result through the anti-error working mechanism and the staggered start-up mechanism, including: judging the consistency of the electric pump start-up instruction and the electric pump control result, if the judgment is consistent, the electric pump is started according to the electric pump start-up instruction through the staggered start-up mechanism, if the judgment is inconsistent, an alarm signal is output.

[0070] Further, in the above step S4, see Figure 5 , Figure 6 and Figure 7 As shown, the constructed second control logic architecture is adopted to automatically start and stop the electric pump provided on each of the sub-hydraulic systems in the second group 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:

[0071] S41, constructing a second control logic architecture including an overpressure protection mechanism and a staggered start mechanism;

[0072] S42, extracting the onboard status signal, outputting an electric pump shut-down instruction when the onboard status signal is less than the onboard status threshold, and shutting down the electric pump according to the electric pump shut-down instruction;

[0073] S43, when the onboard status signal is greater than or equal to the onboard status threshold, obtaining an electric pump start instruction or an onboard controlled mechanism logic judgment instruction according to the first hydraulic pressure and the low pressure threshold, obtaining the second hydraulic pressure according to the electric pump start instruction, and starting the electric pump or outputting an alarm signal through the anti-overpressure protection mechanism and the staggered start mechanism according to the second hydraulic pressure and the hydraulic safety threshold;

[0074] S44. Acquire the flight control system status signal according to the logic judgment instruction of the controlled mechanism on the aircraft, and judge whether the controlled mechanism needs pressure according to the flight control system status signal; if it is judged that there is a pressure demand, output the electric pump start instruction, obtain the second hydraulic pressure according to the electric pump start instruction, and start the electric pump or output an alarm signal through the anti-overpressure protection mechanism and the staggered start mechanism according to the second hydraulic pressure and the hydraulic safety threshold; if it is judged that there is no pressure demand, turn off the electric pump.

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

[0076] Acquire the second hydraulic pressure according to the electric pump start instruction, compare the second hydraulic pressure with the hydraulic safety threshold, and output the electric pump shutdown instruction, the start termination flag and the overpressure alarm signal if the second hydraulic pressure is greater than or equal to the hydraulic safety threshold;

[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 instruction and the start flag.

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

[0079] respectively defining a priority order for starting the electric pumps connected to all the sub-hydraulic systems in the first group and the second group, giving a data waiting time corresponding to each priority level in the priority order, and identifying 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 counting starts according to the start signal of the priority level before the priority level and the priority level start counter. When the count value reaches the data waiting time corresponding to the priority level and the start signal of the priority level before the priority level is received, the electric pump start instruction is output to construct the staggered start mechanism.

[0081] Furthermore, the flight control system status signal includes a landing gear signal and a control surface status signal, the onboard status signal includes a ground speed signal, and the onboard controlled mechanism includes a landing gear and a control surface.

[0082] Furthermore, in the above steps S34 and S44, see Figure 2 and Figure 5 As shown, judging whether the controlled mechanism needs pressure according to the flight control system state signal includes:

[0083] Determining whether the landing gear has a pressure requirement according to the landing gear signal, and if the landing gear signal is a retracting signal or a lowering signal, determining that the landing gear has a pressure requirement;

[0084] Determine whether the rudder surface has a pressure requirement according to the rudder surface state signal, and if the rudder surface state signal is a rudder surface position change signal, determine that the rudder surface has a pressure requirement;

[0085] When any one or both of the control surface and the landing gear have pressure requirements, it is determined that the controlled mechanism needs pressure.

[0086] Based on the same inventive concept, an embodiment of the present invention also provides a hydraulic mechanism heterogeneous control system for a large transport aircraft, as described in the following embodiments. Since the principle of solving the problem by the hydraulic mechanism heterogeneous control system for a large transport aircraft is similar to the hydraulic mechanism heterogeneous control method for a large transport aircraft disclosed in the above embodiments, the implementation of the hydraulic mechanism heterogeneous control system for a large transport aircraft can refer to the implementation of the hydraulic mechanism heterogeneous control method for a large transport aircraft, and the repeated parts will not be repeated. As used below, the term "unit" or "module" can be a combination of software and / or hardware that implements a predetermined function. Although the device described in the following embodiments is preferably implemented in software, the implementation of hardware, or a combination of software and hardware, is also possible and conceived.

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

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

[0089] The control logic construction module 802 is used to construct a first control logic architecture and a first control logic architecture through multiple on-board state thresholds, low pressure thresholds, hydraulic safety thresholds, and sub-hydraulic system relationship tables;

[0090] The first control unit 803 is used to adopt the constructed first control logic architecture to automatically start and stop the electric pump provided on each of the sub-hydraulic systems in the first group according to the onboard state threshold, the low pressure threshold, the 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;

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

[0092] Further, see Fig. 9 As shown, the first control unit 801 and the second control unit 802 both include an acquisition module 1, a data scheduling module 2 and multiple control modules 3, and 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, and the control module 3 of the first control unit 801 includes an anti-error working 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 anti-overpressure protection module 33.

[0093] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above technical solutions adopted in the embodiments of this specification include at least:

[0094] 1. By using different control architectures to automatically control the electric pumps of the two sub-hydraulic systems, the pilots do not need to spend a lot of energy on controlling the electric pumps during the mission, which significantly reduces the pilot's workload. On the other hand, it can ensure that when one control architecture is abnormal, the electric pump can be controlled by another control architecture to ensure the normal operation of the hydraulic system and further improve flight safety.

[0095] 2. Automatically control the opening and closing of electric pumps based on the aircraft status collected in real time, thus avoiding the risk of excessive energy consumption and overpressure damage to the hydraulic system caused by the need to start all electric pumps throughout the entire process;

[0096] 3. Through the design of heterogeneous integrated control systems, the functions of the automatic control system are distributed in two different physical entities, which can support the installation of 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 and bird strikes. At the same time, it can also avoid the problem of complete loss of system functions due to common mode failures;

[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 abnormalities in a single control module through a joint decision-making mechanism of the control modules, and implement additional protection for the electric pump, which significantly enhances the safety and stability of the system, increases the service life of the electric pump, and thereby enhances the safety of the aircraft; the second control unit periodically monitors the status of the hydraulic transmission system by designing an anti-overpressure protection module with an independent input source, and when a serious fault in the control module causes the electric pump to be erroneously turned on, the corresponding electric pump is turned off with a 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 anti-overpressure protection module is turned on, the start-up of the electric pump is time-controlled according to pre-defined priorities and rules, thereby protecting the electric pump and the onboard power supply.

[0098] In this embodiment, a computer device is provided, such as Fig.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, any of the above-mentioned heterogeneous control methods for the hydraulic mechanism of large transport aircraft is implemented.

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

[0100] In this embodiment, a computer-readable storage medium is provided, wherein the computer-readable storage medium stores a computer program for executing any of the above-mentioned methods for heterogeneous control of hydraulic mechanisms of large transport aircraft.

[0101] Specifically, computer-readable storage media include permanent and non-permanent, removable and non-removable media that can store information by 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 technology, compact disk read-only memory (CD-ROM), digital versatile disk (DVD) or other optical storage, magnetic cassettes, tape disk storage or other magnetic storage devices or any other non-transmission media that can be used to store information that can be accessed by a computing device. As defined herein, computer-readable storage media does not include transitory 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-mentioned embodiments of the present invention can be implemented by a general computing device, they can be concentrated on a single computing device, or distributed on a network composed of multiple computing devices, and optionally, they can be implemented by a program code executable by a computing device, so that they can be stored in a storage device and executed by the computing device, and in some cases, the steps shown or described can be executed in a different order from that here, or they can be made into individual integrated circuit modules, or multiple modules or steps therein can be made into a single integrated circuit module for implementation. In this way, the embodiments of the present invention are not limited to any specific combination of hardware and software.

[0103] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the embodiments of the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for controlling a hydraulic mechanism of a large transport aircraft, wherein the hydraulic system includes a plurality of sub-hydraulic systems, each of which is provided with an electric pump, characterized in that: The method controls each of the electric pumps, and the method comprises: Divide all the sub-hydraulic systems into two groups, each group including at least one sub-hydraulic system; Collecting in real time the onboard status signal, the flight control system status signal and the first hydraulic pressure and the second hydraulic pressure of each of the sub-hydraulic systems; Using the constructed first control logic architecture, the electric pump provided on each of the sub-hydraulic systems in the first group is automatically started and stopped according to the onboard state threshold, the low pressure threshold, the 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; By adopting the constructed second control logic architecture, the start and stop automatic control is performed on the electric pump provided on each of the sub-hydraulic systems in the second group according to the on-board status threshold, the low pressure threshold, the hydraulic safety threshold, the on-board status signal, the first hydraulic pressure and the second hydraulic pressure of each of the sub-hydraulic systems in the second group.

2. The method for controlling the hydraulic mechanism heterogeneity of a large transport aircraft according to claim 1, characterized in that: The first control logic architecture is adopted to automatically start and stop the electric pump provided on each of the sub-hydraulic systems in the first group according to the onboard state threshold, the low pressure threshold, the 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, including: Constructing a first control logic architecture including an anti-error working mechanism and a staggered start mechanism, and establishing a sub-hydraulic system relationship table for all the sub-hydraulic systems in the first group; Extracting the on-board status signal, outputting an electric pump shut-down instruction when the on-board status signal is less than the on-board status threshold, shutting down the electric pump or outputting an alarm signal based on the error prevention working mechanism and the sub-hydraulic system relationship table according to the electric pump shut-down instruction and the electric pump control result of the sub-hydraulic system associated with the controlled sub-hydraulic system; When the on-board status signal is greater than or equal to the on-board status threshold, an electric pump start instruction or an on-board controlled mechanism logic judgment instruction is obtained according to the first hydraulic pressure and the low-pressure threshold, and the electric pump is started or an alarm signal is output through the anti-error working mechanism and the staggered start mechanism according to the electric pump start instruction and the electric pump control result; The flight control system status signal is obtained according to the logic judgment instruction of the controlled mechanism on the aircraft, and whether the controlled mechanism needs pressure is judged according to the flight control system status signal; if it is judged that there is a pressure demand, an electric pump start instruction is output, and the electric pump is turned on or an alarm signal is output through the anti-error working mechanism and the staggered start mechanism according to the electric pump start instruction and the electric pump control result; if it is judged that there is no pressure demand, the electric pump is turned off based on the anti-error working mechanism.

3. The method for controlling the hydraulic mechanism heterogeneity of a large transport aircraft according to claim 2, characterized in that: According to the electric pump shut-down instruction and the electric pump control result of the sub-hydraulic system associated with the controlled sub-hydraulic system, shutting down the electric pump or outputting an alarm signal based on the error prevention working mechanism and the sub-hydraulic system relationship table includes: Performing consistency judgment on the electric pump shut-down instruction and the electric pump control result, if the judgment is consistent, shutting down the electric pump according to the electric pump shut-down instruction, and if the judgment is inconsistent, outputting an alarm signal; The electric pump is started or an alarm signal is output according to the electric pump start-up instruction and the electric pump control result through the anti-error working mechanism and the staggered start-up mechanism, including: judging the consistency of the electric pump start-up instruction and the electric pump control result, if the judgment is consistent, the electric pump is started according to the electric pump start-up instruction through the staggered start-up mechanism, if the judgment is inconsistent, an alarm signal is output.

4. The method for controlling the hydraulic mechanism heterogeneity of a large transport aircraft according to claim 1, characterized in that: The constructed second control logic architecture is adopted to automatically start and stop the electric pump provided on each of the sub-hydraulic systems in the second group 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: Construct a second control logic architecture including an overpressure protection mechanism and a staggered start mechanism; Extracting the onboard status signal, outputting an electric pump shut-down instruction when the onboard status signal is less than the onboard status threshold, and shutting down the electric pump according to the electric pump shut-down instruction; When the on-board status signal is greater than or equal to the on-board status threshold, an electric pump start instruction or an on-board controlled mechanism logic 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 start instruction, and the electric pump is started or an alarm signal is output through the anti-overpressure protection mechanism and the staggered start mechanism according to the second hydraulic pressure and the hydraulic safety threshold; The flight control system status signal is obtained according to the logic judgment instruction of the controlled mechanism on the aircraft, and whether the controlled mechanism needs pressure is determined according to the flight control system status signal; if it is determined that there is a pressure demand, an electric pump start instruction is output, and the second hydraulic pressure is obtained according to the electric pump start instruction, and the electric pump is turned on or an alarm signal is output through the anti-overpressure protection mechanism and the staggered start mechanism according to the second hydraulic pressure and the hydraulic safety threshold; if it is determined that there is no pressure demand, the electric pump is turned off.

5. The method for controlling the hydraulic mechanism heterogeneity of a large transport aircraft according to claim 4, characterized in that: Acquiring the second hydraulic pressure according to the electric pump start instruction, and starting the electric pump or outputting an alarm signal through the anti-overpressure protection mechanism and the staggered start mechanism according to the second hydraulic pressure and the hydraulic safety threshold, including: Acquire the second hydraulic pressure according to the electric pump start instruction, compare the second hydraulic pressure with the hydraulic safety threshold, and output the electric pump shutdown instruction, the start termination flag and the overpressure alarm signal if the second hydraulic pressure is greater than or equal to the hydraulic safety threshold; 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 instruction and the start flag.

6. The method for controlling a hydraulic mechanism heterogeneity of a large transport aircraft according to any one of claims 1 to 5, characterized in that: The method further comprises: respectively defining a priority order for starting the electric pumps connected to all the sub-hydraulic systems in the first group and the second group, giving a data waiting time corresponding to each priority level in the priority order, and identifying the priority level of the electric pump connected to the sub-hydraulic system corresponding to the first hydraulic pressure according to the priority order; The counting starts according to the start signal of the priority level before the priority level and the priority level start counter. When the count value reaches the data waiting time corresponding to the priority level and the start signal of the priority level before the priority level is received, the electric pump start instruction is output to construct the staggered start mechanism.

7. The method for controlling a hydraulic mechanism heterogeneity of a large transport aircraft according to any one of claims 1 to 5, characterized in that: The flight control system status signal includes a landing gear signal and a control surface status signal, the onboard status signal includes a ground speed signal, and the onboard controlled mechanism includes a landing gear and a control surface.

8. The method for controlling the hydraulic mechanism heterogeneity of a large transport aircraft according to claim 7, characterized in that: Judging whether the controlled mechanism needs pressure according to the flight control system state signal includes: Determining whether the landing gear has a pressure requirement according to the landing gear signal, and if the landing gear signal is a retracting signal or a lowering signal, determining that the landing gear has a pressure requirement; Determine whether the rudder surface has a pressure requirement according to the rudder surface state signal, and if the rudder surface state signal is a rudder surface position change signal, determine that the rudder surface has a pressure requirement; When any one or both of the control surface and the landing gear have pressure requirements, it is determined that the controlled mechanism needs pressure.

9. A hydraulic mechanism heterogeneous control system for a large transport aircraft, characterized in that: include: a grouping module, the grouping module being used to divide all the sub-hydraulic systems into two groups, each group including at least one sub-hydraulic system; a control logic building module, the control logic building module being used to build a first control logic architecture and a first control logic architecture through a plurality of onboard state thresholds, low pressure thresholds, hydraulic safety thresholds, and sub-hydraulic system relationship tables; a first control unit, the first control unit being configured to automatically start and stop the electric pump provided on each of the sub-hydraulic systems in the first group according to an onboard state threshold, a low pressure threshold, a sub-hydraulic system relationship table, the onboard state signal, a flight control system state signal, and the first hydraulic pressure of the two associated sub-hydraulic systems, using a constructed first control logic architecture; The second control unit is used to adopt a constructed second control logic architecture to automatically start and stop the electric pump provided on each of the sub-hydraulic systems in the second group according to the on-board status threshold, the low pressure threshold, the hydraulic safety threshold, the on-board status signal, the first hydraulic pressure and the second hydraulic pressure of each of the sub-hydraulic systems in the second group.

10. The hydraulic mechanism heterogeneous control system for a large transport aircraft according to claim 9, characterized in that: The first control unit and the second control unit both 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 anti-error working module and a staggered start module; the control modules of the second control unit include a staggered start module and an anti-overpressure protection module.

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