Electric pump control method and system based on protection mechanism

Abstract

The invention belongs to the field of aviation equipment, and discloses an electric pump control method and system based on a protection mechanism, and the control method comprises the steps: collecting an onboard state signal, a flight control system state signal and the hydraulic pressure of each sub hydraulic system in a hydraulic system in real time; according to the onboard state signal, an electric pump closing instruction and a hydraulic pressure logic judgment instruction are output through first electric pump control logic, and an electric pump connected to the sub hydraulic system is closed according to the electric pump closing instruction; a flight control system state signal and hydraulic pressure are obtained according to the hydraulic pressure logic judgment instruction, and an electric pump connected to each hydraulic sub-system is automatically controlled through second electric pump control logic and electric pump protection logic. By designing the automatic electric pump control logic and the electric pump protection logic, the electric pump damage caused by excessive transient current due to simultaneous starting of all the electric pumps can be avoided, and the flight safety is improved.

Description

Technical Field

[0001] The present invention belongs to the field of aviation equipment, relates to hydraulic system control technology, and specifically relates to an electric pump control method and system based on a protection mechanism. Background Art

[0002] Transport category aircraft have a redundant hydraulic system that is controlled by multiple electric pumps to provide hydraulic or fluid power, where the number of electric pumps usually corresponds one-to-one to the subsystems in the hydraulic system.

[0003] At present, the traditional control method of electric pumps on transport aircraft is to run all electric pumps simultaneously during the ground preparation stage and the flight stage, and shut down all electric pumps at the same time after landing. On the one hand, this control method is because the flight scenarios and time in which the electric pumps are actually needed account for a relatively low proportion of the entire flight stage, and the electric pumps are large energy-consuming components on the aircraft. Running them simultaneously will greatly increase the energy consumption of the aircraft. On the other hand, when all electric pumps are running simultaneously throughout the entire process, it is often easy to have excessive transient current, resulting in unstable power supply or damage to the electric pumps. Summary of the invention

[0004] In order to solve the technical problems of increasing aircraft energy consumption caused by running all electric pumps at the same time and causing unstable onboard power supply or damage to the electric pump due to excessive transient current, the present invention discloses an electric pump control method based on a protection mechanism, the electric pump control method comprising the following steps:

[0005] S2, real-time collection of onboard status signals, flight control system status signals and hydraulic pressure of each sub-hydraulic system in the hydraulic system;

[0006] S3, according to the on-board status signal, outputting an electric pump shut-down instruction and a hydraulic pressure logic judgment instruction through the first electric pump control logic, and shutting down the electric pump connected to the sub-hydraulic system according to the electric pump shut-down instruction;

[0007] S4. Acquire the flight control system status signal and the hydraulic pressure according to the hydraulic pressure logic judgment instruction, and automatically control the electric pump connected to each of the sub-hydraulic systems through the second electric pump control logic and the electric pump protection logic.

[0008] In an improved embodiment of the above-mentioned redundancy automatic electric pump control method, the control method further comprises:

[0009] S11. Set an on-board status threshold. When the on-board status signal is less than the on-board status threshold, output an electric pump shutdown instruction. When the on-board status signal is less than or equal to the on-board status threshold, output a hydraulic pressure logic judgment instruction to construct the first electric pump control logic.

[0010] In an improved embodiment of the above-mentioned redundancy automatic electric pump control method, the control method further comprises:

[0011] S12, given a low-pressure threshold, obtaining the hydraulic pressure according to the hydraulic pressure logic judgment instruction, comparing the hydraulic pressure with the low-pressure threshold, and outputting an instruction to start the electric pump protection mechanism if the hydraulic pressure is less than or equal to the low-pressure threshold, and starting and controlling the electric pump connected to the sub-hydraulic system through the electric pump protection logic according to the electric pump protection mechanism instruction; if the hydraulic pressure is greater than the low-pressure threshold, outputting an on-board controlled mechanism logic judgment instruction;

[0012] S13. Acquire the flight control system status signal according to the onboard controlled mechanism logic judgment instruction, judge whether the controlled mechanism needs pressure according to the flight control system status signal, and output the instruction to start the electric pump protection mechanism if it is judged that there is a pressure demand, and start and control the electric pump connected to the sub-hydraulic system through the electric pump protection logic according to the electric pump protection mechanism instruction; if it is judged that there is no pressure demand, output the electric pump shutdown instruction to construct the second electric pump control logic.

[0013] In an improved embodiment of the above-mentioned redundancy automatic electric pump control method, the control method further includes: S14, constructing electric pump protection logic, including:

[0014] S141, defining a priority order for starting the electric pumps connected to all the sub-hydraulic systems, giving a data waiting time corresponding to each priority level in the priority order, and identifying the priority level of the electric pumps connected to the sub-hydraulic systems corresponding to the hydraulic pressure according to the priority order;

[0015] S142. Start counting based on the start signal of the previous priority level of 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 previous priority level of the priority level is received, output the electric pump start instruction to construct the electric pump protection logic.

[0016] 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 controlled mechanism includes a landing gear and a control surface.

[0017] Furthermore, in step S13, judging whether the controlled mechanism needs pressure according to the flight control system state signal includes:

[0018] S131, judging 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, judging that the landing gear has a pressure requirement;

[0019] S132, judging whether the rudder surface has a pressure demand according to the rudder surface state signal, and if the rudder surface state signal is a rudder surface position change signal, judging that the rudder surface has a pressure demand;

[0020] S133: When any one or both of the control surface and the landing gear have pressure requirements, determine whether the controlled mechanism needs pressure.

[0021] The embodiment of the present invention further provides an electric pump control system based on a protection mechanism, the electric pump control system comprises a collection module, a data scheduling module and a plurality of electric pump control modules, each of the electric pump control modules is respectively connected to an electric pump, the collection module is used to collect an onboard status signal, a flight control system status signal and the hydraulic pressure of each sub-hydraulic system in the hydraulic system, and the output end of the collection module is connected to the input end of the data scheduling module;

[0022] The data scheduling module is connected to each of the electric pump control modules. The electric pump control module uses the first electric pump control logic, the second electric pump control logic and the electric pump protection logic to output the electric pump control signal according to the onboard status signal, the flight control system status signal and the hydraulic pressure extracted from the data scheduling module.

[0023] Furthermore, the electric pump control module includes a first logic judgment module, a second logic judgment module, an electric pump protection logic judgment module, and an electric pump control instruction output module. The input ends of the first logic judgment module and the second logic judgment module are both connected to the data scheduling module, and the output ends of the first logic judgment module and the second logic judgment module are both connected to the electric pump via the electric pump control instruction output module; the input end of the electric pump protection logic judgment module is connected to the second logic judgment module, and the output end is connected to the electric pump control instruction output module.

[0024] Furthermore, the electric pump control system also includes a power supply module, the input end of the power supply module is connected to the onboard power supply, and the output end is connected to the acquisition module, the data scheduling module and each of the electric pump control modules, and the power supply module supplies power to the acquisition module, the data scheduling module and the electric pump control module.

[0025] Furthermore, there are at least two sub-hydraulic systems in the hydraulic system, and there are at least two electric pump control modules, and each of the electric pump control modules is connected to one of the sub-hydraulic systems in the hydraulic system via one of the electric pumps.

[0026] The electric pump control method and system of the present invention can control multiple electric pumps when electric pumps are needed according to the application scenario of the aircraft by designing automatic electric pump control logic and electric pump protection logic, and can also avoid single point failures and improve flight safety. Specifically, it has the following advantages:

[0027] 1. By automating the control of the electric pump, the pilot does not need to spend a lot of energy on the control of the electric pump during the mission execution, which significantly reduces the pilot's workload;

[0028] 2. By using the electric pump control logic to automatically control the opening and closing of the electric pump according to different aircraft states, the electric pump is avoided from being turned on throughout the entire process, which significantly reduces aircraft energy consumption and improves energy utilization efficiency;

[0029] 3. By designing the electric pump protection logic, the start-up sequence of the electric pump when it is needed on board is optimized, avoiding problems such as reduced aircraft power supply and damage to the electric pump caused by starting the electric pumps at the same time, thereby improving the aircraft power supply safety and the service life of the electric pump;

[0030] 4. The design of the control system for multiple electric pump control modules can achieve independent and accurate control of each electric pump to avoid single point failure caused by control module failure, with high security and improved flight safety;

[0031] 5. The electric pump protection mechanism designed by the present invention includes an overtime emergency mechanism, which can ensure the normal start-up of the electric pump in the extreme case where the electric pump protection mechanism fails to complete the predetermined function, thereby ensuring the completeness and safety of the aircraft functions;

[0032] 6. The control system of the present invention has good maintainability through modular design and can be modified and maintained accordingly at a relatively low cost according to changes in application scenarios. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] 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.

[0034] Figure 1A flowchart of an electric pump control method based on a protection mechanism is disclosed in an embodiment of the present invention;

[0035] Figure 2 It is an execution diagram of the electric pump control module disclosed in the embodiment of the present invention;

[0036] Figure 3 It is an execution diagram of the electric pump protection logic disclosed in the embodiment of the present invention;

[0037] Figure 4 It is a structural diagram of an electric pump control system based on a protection mechanism disclosed in an embodiment of the present invention;

[0038] Among them, 101, acquisition module; 102, data scheduling module; 103, electric pump control module; 104, power supply module; 1, first sub-hydraulic system; 2, second sub-hydraulic system; 3, third sub-hydraulic system; 11, first electric pump; 12, second electric pump; 13, third electric pump; 111, first hydraulic pressure; 121, second hydraulic pressure; 131, third hydraulic pressure. DETAILED DESCRIPTION

[0039] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0040] 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.

[0041] The embodiment of the present invention discloses a method for controlling an electric pump based on a protection mechanism, see Figure 1 and Figure 2 As shown, the electric pump control method includes the following steps:

[0042] S2, real-time collection of onboard status signals, flight control system status signals and hydraulic pressure of each sub-hydraulic system in the hydraulic system;

[0043] S3, according to the on-board status signal, outputting an electric pump shut-down instruction and a hydraulic pressure logic judgment instruction through the first electric pump control logic, and shutting down the electric pump connected to the sub-hydraulic system according to the electric pump shut-down instruction;

[0044] S4. Acquire the flight control system status signal and the hydraulic pressure according to the hydraulic pressure logic judgment instruction, and automatically control the electric pump connected to each of the sub-hydraulic systems through the second electric pump control logic and the electric pump protection logic.

[0045] In an improved embodiment of the above-mentioned redundancy automatic electric pump control method, see Figure 2 As shown, the control method also includes:

[0046] S11. Set an on-board status threshold. When the on-board status signal is less than the on-board status threshold, output an electric pump shutdown instruction. When the on-board status signal is less than or equal to the on-board status threshold, output a hydraulic pressure logic judgment instruction to construct the first electric pump control logic.

[0047] In an improved embodiment of the above-mentioned redundancy automatic electric pump control method, see Figure 2 As shown, the control method also includes:

[0048] S12, given a low-pressure threshold, obtaining the hydraulic pressure according to the hydraulic pressure logic judgment instruction, comparing the hydraulic pressure with the low-pressure threshold, and outputting an instruction to start the electric pump protection mechanism if the hydraulic pressure is less than or equal to the low-pressure threshold, and starting and controlling the electric pump connected to the sub-hydraulic system through the electric pump protection logic according to the electric pump protection mechanism instruction; if the hydraulic pressure is greater than the low-pressure threshold, outputting an on-board controlled mechanism logic judgment instruction;

[0049] S13. Acquire the flight control system status signal according to the onboard controlled mechanism logic judgment instruction, judge whether the controlled mechanism needs pressure according to the flight control system status signal, and output the instruction to start the electric pump protection mechanism if it is judged that there is a pressure demand, and start and control the electric pump connected to the sub-hydraulic system through the electric pump protection logic according to the electric pump protection mechanism instruction; if it is judged that there is no pressure demand, output the electric pump shutdown instruction to construct the second electric pump control logic.

[0050] In an improved embodiment of the above-mentioned redundancy automatic electric pump control method, see Figure 2 and Figure 3 As shown, the control method further includes: S14, constructing electric pump protection logic, including:

[0051] S141, defining a priority order for starting the electric pumps connected to all the sub-hydraulic systems, giving a data waiting time corresponding to each priority level in the priority order, and identifying the priority level of the electric pumps connected to the sub-hydraulic systems corresponding to the hydraulic pressure according to the priority order;

[0052] S142, starting counting according to the start signal of the priority level one level above 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 one level above the priority level is received, outputting an electric pump start instruction to construct the electric pump protection logic;

[0053] Further, see Figure 3 As shown, the electric pump protection logic is constructed in step S14, and also includes:

[0054] S143: When the start signal of the upper priority level is not received and the count value of the counter exceeds the data waiting time, the timeout emergency mechanism is started and synchronization failure information is reported.

[0055] 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 controlled mechanism includes a landing gear and a control surface.

[0056] Furthermore, in step S13, judging whether the controlled mechanism needs pressure according to the flight control system state signal includes:

[0057] S131, judging 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, judging that the landing gear has a pressure requirement;

[0058] S132, judging whether the rudder surface has a pressure demand according to the rudder surface state signal, and if the rudder surface state signal is a rudder surface position change signal, judging that the rudder surface has a pressure demand;

[0059] S133: When any one or both of the control surface and the landing gear have pressure requirements, determine whether the controlled mechanism needs pressure.

[0060] Based on the same inventive concept, an electric pump control system based on a protection mechanism is also provided in an embodiment of the present invention, as described in the following embodiments. Since the principle of solving the problem by the electric pump control system based on the protection mechanism is similar to the above-mentioned implementation of the disclosed electric pump control method based on the protection mechanism, the implementation of the electric pump control system based on the protection mechanism can refer to the implementation of the electric pump control method based on the protection mechanism, 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.

[0061] Figure 4 is a structural block diagram of an electric pump control system based on a protection mechanism disclosed in an embodiment of the present invention, such as Figure 4 As shown, the electric pump control includes an acquisition module 101, a data scheduling module 102 and multiple electric pump control modules 103, each of the electric pump control modules 103 is respectively connected to an electric pump, the acquisition module 101 is used to collect onboard status signals, flight control system status signals and the hydraulic pressure of each sub-hydraulic system in the hydraulic system, and the output end of the acquisition module 101 is connected to the input end of the data scheduling module 102.

[0062] The data scheduling module 102 is connected to each of the electric pump control modules 103. The electric pump control module 103 outputs an electric pump control signal using the first electric pump control logic, the second electric pump control logic and the electric pump protection logic according to the onboard status signal, the flight control system status signal and the hydraulic pressure extracted from the data scheduling module 102.

[0063] Furthermore, there are at least two sub-hydraulic systems in the hydraulic system, and at least two electric pump control modules, each of which is connected to one of the sub-hydraulic systems in the hydraulic system via one of the electric pumps. Specifically, the hydraulic system can be a complex system with double redundancy, triple redundancy, quadruple redundancy or even high redundancy, and there are 2 to 4 corresponding electric pump control modules 103, each of which is connected to one of the sub-hydraulic systems in the hydraulic system via one of the electric pumps. For example, Figure 1As shown, when the hydraulic system is a triple-redundant system, there are three sub-hydraulic systems, namely, the first sub-hydraulic system 1, the second sub-hydraulic system 2 and the third sub-hydraulic system 3. The corresponding electric pumps include a first electric pump 11 connected to the first sub-hydraulic system 1, a second electric pump 12 connected to the second sub-hydraulic system 2 and a third electric pump 13 connected to the third sub-hydraulic system 3. The corresponding hydraulic pressures include a first hydraulic pressure 111 of the first sub-hydraulic system 1, a second hydraulic pressure 121 of the second sub-hydraulic system 2 and a third hydraulic pressure 131 of the third sub-hydraulic system 3.

[0064] Furthermore, the electric pump control module 103 includes a first logic judgment module, a second logic judgment module, an electric pump protection logic judgment module, and an electric pump control instruction output module. The input ends of the first logic judgment module and the second logic judgment module are both connected to the data scheduling module 102, and the output ends of the first logic judgment module and the second logic judgment module are both connected to the electric pump via the electric pump control instruction output module; the input end of the electric pump protection logic judgment module is connected to the second logic judgment module, and the output end is connected to the electric pump control instruction output module.

[0065] Furthermore, the control system also includes a power supply module 104, the input end of the power supply module 104 is connected to the onboard power supply, and the output end is connected to the acquisition module 101, the data scheduling module 102 and each of the electric pump control modules 103, and the power supply module 104 supplies power to the acquisition module 101, the data scheduling module 102 and the electric pump control module 103.

[0066] The electric pump control method and system of the present invention can control multiple electric pumps when electric pumps are needed according to the application scenario of the aircraft by designing automatic electric pump control logic and electric pump protection logic, and can also avoid single point failures and improve flight safety. Specifically, it has the following advantages:

[0067] 1. By automating the control of the electric pump, the pilot does not need to spend a lot of energy on the control of the electric pump during the mission execution, which significantly reduces the pilot's workload;

[0068] 2. By using the electric pump control logic to automatically control the opening and closing of the electric pump according to different aircraft states, the electric pump is avoided from being turned on throughout the entire process, which significantly reduces aircraft energy consumption and improves energy utilization efficiency;

[0069] 3. The design of the control system for multiple electric pump control modules can achieve independent and accurate control of each electric pump to avoid single point failure caused by control module failure, with high security and improved flight safety;

[0070] 4. The design of the control system with multiple electric pump control modules can avoid the occurrence of single-point situations, so that the control system will not completely lose the electric pump control function when a single power supply, input information source, control function, etc. fails or fails, which has high security and increases the safety of the aircraft;

[0071] 5. The electric pump protection mechanism designed by the present invention includes an overtime emergency mechanism, which can ensure the normal start-up of the electric pump in the extreme case where the electric pump protection mechanism fails to complete the predetermined function, thereby ensuring the completeness and safety of the aircraft functions;

[0072] 6. The control system of the present invention has good maintainability through modular design and can be modified and maintained accordingly at a relatively low cost according to changes in application scenarios.

[0073] In this embodiment, a computer device is provided, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the computer program, any of the above-mentioned electric pump control methods based on the protection mechanism is implemented.

[0074] Specifically, the computer device may be a computer terminal, a server or a similar computing device.

[0075] 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 electric pump control methods based on the protection mechanism.

[0076] 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, Flash, non-volatile random access memory (NVRAM) or other memory technology, compact disc read-only memory (CD-ROM), digital versatile disc (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.

[0077] 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.

[0078] 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 an electric pump based on a protection mechanism, characterized in that: include: Real-time acquisition of onboard status signals, flight control system status signals and the hydraulic pressure of each sub-hydraulic system in the hydraulic system; According to the on-board status signal, an electric pump shut-down instruction and a hydraulic pressure logic judgment instruction are output through the first electric pump control logic, and the electric pump connected to the sub-hydraulic system is shut down according to the electric pump shut-down instruction; The flight control system state signal and the hydraulic pressure are acquired according to the hydraulic pressure logic judgment instruction, and the electric pump connected to each of the sub-hydraulic systems is automatically controlled through the second electric pump control logic and the electric pump protection logic.

2. The electric pump control method based on the protection mechanism according to claim 1 is characterized in that: The control method further comprises: An on-board status threshold is set. When the on-board status signal is less than the on-board status threshold, an electric pump shutdown instruction is output. When the on-board status signal is less than or equal to the on-board status threshold, a hydraulic pressure logic judgment instruction is output to construct the first electric pump control logic.

3. The electric pump control method based on the protection mechanism according to claim 2 is characterized in that: The control method further comprises: Given a low-pressure threshold, the hydraulic pressure is obtained according to the hydraulic pressure logic judgment instruction, the hydraulic pressure is compared with the low-pressure threshold, if the hydraulic pressure is less than or equal to the low-pressure threshold, an instruction to start the electric pump protection mechanism is output, and the electric pump connected to the sub-hydraulic system is started and controlled through the electric pump protection logic according to the electric pump protection mechanism instruction; if the hydraulic pressure is greater than the low-pressure threshold, an on-board controlled mechanism logic judgment instruction is output; 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 instruction to start the electric pump protection mechanism is output, and the electric pump connected to the sub-hydraulic system is started and controlled through the electric pump protection logic according to the electric pump protection mechanism instruction; if it is judged that there is no pressure demand, an electric pump shutdown instruction is output to construct the second electric pump control logic.

4. The electric pump control method based on the protection mechanism according to claim 3 is characterized in that: The control method further comprises: defining a priority order for starting the electric pumps connected to all the sub-hydraulic systems, giving a data waiting time corresponding to each priority level in the priority order, and identifying the priority level of the electric pumps connected to the sub-hydraulic systems corresponding to the hydraulic pressure according to the priority order; The counting is started 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 electric pump protection logic.

5. The electric pump control method based on the protection mechanism according to claim 3 or 4, 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 controlled mechanism includes a landing gear and a control surface.

6. The electric pump control method based on the protection mechanism according to claim 5 is 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.

7. An electric pump control system based on a protection mechanism, characterized in that: The electric pump control system comprises a collection module, a data scheduling module and a plurality of electric pump control modules, each of the electric pump control modules is respectively connected to an electric pump, the collection module is used to collect onboard status signals, flight control system status signals and the hydraulic pressure of each sub-hydraulic system in the hydraulic system, and the output end of the collection module is connected to the input end of the data scheduling module; The data scheduling module is connected to each of the electric pump control modules. The electric pump control module uses the first electric pump control logic, the second electric pump control logic and the electric pump protection logic to output the electric pump control signal according to the onboard status signal, the flight control system status signal and the hydraulic pressure extracted from the data scheduling module.

8. The electric pump control system based on the protection mechanism according to claim 7 is characterized in that: The electric pump control module includes a first logic judgment module, a second logic judgment module, an electric pump protection logic judgment module, and an electric pump control instruction output module. The input ends of the first logic judgment module and the second logic judgment module are both connected to the data scheduling module, and the output ends of the first logic judgment module and the second logic judgment module are both connected to the electric pump via the electric pump control instruction output module. The input end of the electric pump protection logic judgment module is connected to the second logic judgment module, and the output end is connected to the electric pump control instruction output module.

9. The electric pump control system based on the protection mechanism according to claim 7, characterized in that: The electric pump control system also includes a power supply module, the input end of the power supply module is connected to the onboard power supply, and the output end is connected to the acquisition module, the data scheduling module and each of the electric pump control modules. The power supply module supplies power to the acquisition module, the data scheduling module and the electric pump control module.

10. The electric pump control system based on the protection mechanism according to claim 7, characterized in that: There are at least two sub-hydraulic systems in the hydraulic system, and there are at least two electric pump control modules. Each of the electric pump control modules is connected to one of the sub-hydraulic systems in the hydraulic system via one of the electric pumps.

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