Comprehensive control method and system for work of electric pump

Abstract

The invention belongs to the field of electromechanical control, relates to an electric pump work control technology, and discloses an electric pump work comprehensive control method and system.The work comprehensive control method comprises the steps that onboard state signals, flight control system state signals and hydraulic pressure of each sub hydraulic system in a hydraulic system are collected in real time; starting and stopping of an electric pump connected to the hydraulic sub-system are controlled through a first electric pump control logic and an anti-error working mechanism according to the onboard state signal; and according to the flight control system state signal, the hydraulic pressure and other electric pump control instructions, the electric pump connected to each sub hydraulic system is automatically controlled through second electric pump control logic, an anti-error working mechanism and a time-staggered working mechanism. The working accuracy of the electric pump can be ensured, meanwhile, system damage caused by simultaneous starting of the electric pump is avoided, and the system safety is improved.

Description

Technical Field

[0001] The present invention belongs to the field of electromechanical control, and relates to an electric pump operation control technology, and in particular to an electric pump operation comprehensive control method and system. Background Art

[0002] Electric pumps usually provide hydraulic or liquid power to the hydraulic system according to instructions. For complex equipment, redundant hydraulic systems are usually designed to ensure their normal operation. For example, in transport aircraft, double-redundant, triple-redundant or even quadruple-redundant complex hydraulic systems are usually designed according to the transport volume of the transport aircraft, and an electric pump is installed on each redundant hydraulic system for control, so as to ensure the correct operation of the landing gear, rudder control and other mechanisms on the transport aircraft.

[0003] Due to the high complexity of the hydraulic system, whether the electric pump that controls it can operate correctly becomes the key. If the data source that controls the electric pump is abnormal or the control logic is abnormal, erroneous control instructions will be output, which will affect the normal function of the hydraulic system, making it difficult to ensure the correct execution of the mechanisms on transport aircraft, thereby affecting flight safety.

[0004] Furthermore, at present, all electric pumps are controlled to start up all the time during the flight preparation stage and the flight process, which will increase the energy consumption of the aircraft and increase the operating cost. At the same time, all electric pumps will be started at the same time, which will affect the service life of the electric pumps. What is more serious is that when multiple electric pumps are started at the same time, if there are no corresponding protection measures, it is easy to have excessive transient current, resulting in unstable power supply or damage to the electric pumps, which will also affect flight safety. Summary of the invention

[0005] In order to improve the accuracy of electric pump control and avoid technical problems such as incorrect control affecting the normal operation of the equipment and causing safety hazards, the present invention discloses a comprehensive control method for electric pump operation, which includes the following steps:

[0006] S4, real-time collection of onboard status signals, flight control system status signals and hydraulic pressure of each sub-hydraulic system in the hydraulic system;

[0007] S5, according to the on-board status signal, outputting an electric pump shut-down instruction and starting an anti-error working instruction or outputting a hydraulic pressure logic judgment instruction through the on-board status threshold and the first electric pump control logic, obtaining the remaining electric pump control instructions according to the starting anti-error working instruction, and shutting down the electric pump connected to the sub-hydraulic system through the anti-error working mechanism through the electric pump shut-down instruction and the remaining electric pump control instructions;

[0008] S6. 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 by adopting the second electric pump control logic, the error prevention working mechanism and the staggered working mechanism through the low pressure threshold.

[0009] Furthermore, the method further comprises:

[0010] S11, setting the on-board state threshold, outputting an electric pump shut-down instruction and a start-up error prevention work instruction when the on-board state signal is less than the on-board state threshold, and starting the error prevention work mechanism according to the start-up error prevention work instruction to shut down the electric pump;

[0011] S12: When the on-board status signal is greater than or equal to the on-board status threshold, output a hydraulic pressure logic judgment instruction to construct the first electric pump control logic.

[0012] Furthermore, the method further comprises:

[0013] S21, 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, outputting a start-up error prevention work instruction and a start-up time-shifting work instruction if the hydraulic pressure is less than or equal to the low-pressure threshold, and controlling the electric pump to start through the error prevention work mechanism and the time-shifting work mechanism according to the start-up error prevention work instruction and the start-up time-shifting work instruction; if the hydraulic pressure is greater than the low-pressure threshold, outputting a logic judgment instruction for the controlled mechanism on the machine;

[0014] S22. Acquire the flight control system status signal according to the onboard controlled mechanism logic judgment instruction, 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 start-up error prevention working instruction and the start-up time-shifting working instruction, and control the electric pump to start through the error prevention working mechanism and the time-shifting working mechanism according to the start-up error prevention working instruction and the start-up time-shifting working instruction; if it is judged that there is no pressure demand, output the start-up error prevention working instruction, acquire the remaining electric pump control instructions according to the start-up error prevention working instruction, and shut down the electric pump connected to the sub-hydraulic system through the error prevention working mechanism through the electric pump shutdown instruction and the remaining electric pump control instructions, and construct the second control logic.

[0015] Furthermore, the comprehensive protection mechanism includes an anti-error operation mechanism and an electric pump startup protection mechanism, and the method further includes:

[0016] S31. Establish an error-proof working mechanism, including:

[0017] S311, sequentially numbering the electric pumps connected to all the sub-hydraulic systems, and establishing an association relationship table for all the electric pumps;

[0018] S312, according to the association relationship table, obtaining the current control information of the associated electric pump as the remaining electric pump control instructions, and performing consistency judgment on the remaining electric pump control instructions and the electric pump start and stop instructions;

[0019] S313: If the judgment result is consistent, the electric pump is controlled according to the current control information; if the judgment result is inconsistent, the control information failure result is reported to establish the error-proof working mechanism.

[0020] S32. Establish a staggered working mechanism, including:

[0021] S321, 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;

[0022] S322. Start counting based on the start signal of the priority level one level above the priority level and the start counter of the priority level. When the count value reaches the data waiting time corresponding to the priority level and the start signal of the priority level one level above the priority level is received, output the electric pump start instruction to construct the electric pump start protection mechanism.

[0023] Furthermore, the onboard control 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.

[0024] Furthermore, in the above step S22, judging whether the controlled mechanism needs pressure according to the flight control system state signal includes:

[0025] 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;

[0026] 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;

[0027] 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.

[0028] The embodiment of the present invention further provides an electric pump integrated control system, the system comprising an acquisition module, a data scheduling module, a comprehensive protection module and a plurality of electric pump control modules, the electric pump control module comprising a first logic judgment module, a second logic judgment module and an electric pump protection module;

[0029] All the electric pump control modules are connected in sequence to form a closed-loop control architecture, each of the electric pump control modules is connected to an electric pump, the output end of the acquisition module is connected to the input end of the data scheduling module and the comprehensive protection module, the data scheduling module and the comprehensive protection module are both connected to each of the electric pump control modules, and the comprehensive protection module includes an anti-error working module and a staggered working module.

[0030] Compared with the prior art, the at least one technical solution adopted in the embodiments of this specification can achieve the following beneficial effects:

[0031] 1. By automating the control of the electric pump, the pilot does not need to spend a lot of energy on controlling the electric pump during the mission execution, which significantly reduces the pilot's workload;

[0032] 2. By adopting the error-proof working mechanism and staggered working mechanism according to different aircraft states to automatically control the opening and closing of the electric pump, the situation of turning on the electric pump throughout the whole process is avoided, which significantly reduces the energy consumption of the aircraft and improves the energy utilization efficiency;

[0033] 3. By designing a staggered working mechanism, the starting 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;

[0034] 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;

[0035] 5. The electric pump protection mechanism designed in the present invention includes a timeout emergency mechanism, which can ensure the normal start-up of the electric pump and ensure the completeness and safety of aircraft functions in extreme cases where the electric pump protection mechanism fails to complete the predetermined function. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] 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.

[0037] Figure 1 It is a flow chart of the comprehensive control method of the electric pump operation disclosed in the embodiment of the present invention;

[0038] Figure 2 A flowchart of comprehensively controlling the operation of the nth electric pump disclosed in an embodiment of the present invention;

[0039] Figure 3 The execution process of the error prevention working mechanism disclosed in the embodiment of the present invention;

[0040] Figure 4 The present invention discloses an execution flow of staggered operation and error-free operation in the integrated control logic disclosed in the embodiment of the present invention. DETAILED DESCRIPTION

[0041] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0042] 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.

[0043] The present invention discloses a comprehensive control method for an electric pump. Figure 1 and Figure 2 As shown, the method comprises the following steps:

[0044] S4, real-time collection of onboard status signals, flight control system status signals and hydraulic pressure of each sub-hydraulic system in the hydraulic system;

[0045] S5, according to the on-board status signal, outputting an electric pump shut-down instruction and starting an anti-error working instruction or outputting a hydraulic pressure logic judgment instruction through the on-board status threshold and the first electric pump control logic, obtaining the remaining electric pump control instructions according to the starting anti-error working instruction, and shutting down the electric pump connected to the sub-hydraulic system through the anti-error working mechanism through the electric pump shut-down instruction and the remaining electric pump control instructions;

[0046] S6. 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 by adopting the second electric pump control logic, the error prevention working mechanism and the staggered working mechanism through the low pressure threshold.

[0047] Further, see Figure 1 and Figure 2 As shown, the method also includes:

[0048] S11, setting the on-board state threshold, outputting an electric pump shut-down instruction and a start-up error prevention work instruction when the on-board state signal is less than the on-board state threshold, and starting the error prevention work mechanism according to the start-up error prevention work instruction to shut down the electric pump;

[0049] S12: When the on-board status signal is greater than or equal to the on-board status threshold, output a hydraulic pressure logic judgment instruction to construct the first electric pump control logic.

[0050] Further, see Figure 2 As shown, the method also includes:

[0051] S21, 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, outputting a start-up error prevention work instruction and a start-up time-shifting work instruction if the hydraulic pressure is less than or equal to the low-pressure threshold, and controlling the electric pump to start through the error prevention work mechanism and the time-shifting work mechanism according to the start-up error prevention work instruction and the start-up time-shifting work instruction; if the hydraulic pressure is greater than the low-pressure threshold, outputting a logic judgment instruction for the controlled mechanism on the machine;

[0052] S22. Acquire the flight control system status signal according to the onboard controlled mechanism logic judgment instruction, 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 start-up error prevention working instruction and the start-up time-shifting working instruction, and control the electric pump to start through the error prevention working mechanism and the time-shifting working mechanism according to the start-up error prevention working instruction and the start-up time-shifting working instruction; if it is judged that there is no pressure demand, output the start-up error prevention working instruction, acquire the remaining electric pump control instructions according to the start-up error prevention working instruction, and shut down the electric pump connected to the sub-hydraulic system through the error prevention working mechanism through the electric pump shutdown instruction and the remaining electric pump control instructions, and construct the second control logic.

[0053] Further, see Figure 3 and Figure 4 As shown, the comprehensive protection mechanism includes an anti-error operation mechanism and an electric pump start-up protection mechanism, and the method further includes:

[0054] S31. Build an error-proof working mechanism, see Figure 3 and Figure 4 As shown, specifically including:

[0055] S311, sequentially numbering the electric pumps connected to all the sub-hydraulic systems, and establishing an association relationship table for all the electric pumps;

[0056] S312, according to the association relationship table, obtaining the current control information of the associated electric pump as the remaining electric pump control instructions, and performing consistency judgment on the remaining electric pump control instructions and the electric pump start and stop instructions;

[0057] S313: If the judgment result is consistent, the electric pump is controlled according to the current control information; if the judgment result is inconsistent, the control information failure result is reported to establish the error-proof working mechanism.

[0058] S32. Establish a staggered working mechanism, including:

[0059] S321, 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;

[0060] S322. Start counting based on the start signal of the priority level one level above the priority level and the start counter of the priority level. When the count value reaches the data waiting time corresponding to the priority level and the start signal of the priority level one level above the priority level is received, output the electric pump start instruction to construct the electric pump start protection mechanism.

[0061] Further, see Figure 4 As shown in the figure, the staggered working mechanism is constructed, and also includes:

[0062] S323. When the start signal of the previous priority level is not received and the counter count value exceeds the data waiting time, the timeout emergency mechanism is started and the synchronization failure information is reported. At the same time, the electric pump is turned on or off according to the electric pump control information output by the first electric pump control logic and the second electric pump control logic.

[0063] Specifically, the process of preventing the electric pump from erroneous operation control is as follows Figure 4 As shown, the following process is included:

[0064] (1) Identify the predefined loop second logic unit object, define the order of electric pumps as electric pump 1, electric pump 2, electric pump 3, ..., electric pump n, and the corresponding electric pump control modules can be named control module 1, control module 2, control module 3, ..., control module n. If the current control module is m (m is less than or equal to n-1), the second logic unit object is electric pump m+1; if the current control module is m (m is equal to n), the second logic unit object is electric pump 1. The logic of the association table is shown in Table 1 below.

[0065] Table 1: Define loop control logic rules

[0066] Comprehensive control logic First control logic Second control logic Control Object AND Logic Control module 1 Control module 2 Electric pump 1 AND Logic Control module 2 Control module 3 Electric pump 2 AND Logic ... ... ... AND Logic Control module n-1 Control module Electric pump n-1 AND Logic Control module Control module 1 Electric pump

[0067] (2) according to the communication protocol agreed within the system, start the recognition of the control logic result of the second logic unit and start the timing at the first start;

[0068] (3) Determine whether the second logic unit control logic result determination signal is received, according to Figure 4 As shown, dual-channel synchronous data, when any one channel of data is received, it is determined that the start signal has been received;

[0069] (4) If the second logic unit control logic result determination signal is received, jump to (5); if the second logic unit control logic result determination signal is not received, jump to (8);

[0070] (5) Perform consistency determination based on the determination result of the control logic module: if the determination result is consistent, jump to (7); if the determination result is inconsistent, jump to (6);

[0071] (6) Start reporting of logical fault status and report inconsistent judgment conclusions;

[0072] (7) Determine whether the consistent control logic result is start: if the consistent control logic result is start, jump to start the electric pump; if the consistent control logic result is not start, jump to shut down the electric pump;

[0073] (8) Determine whether the synchronization waiting time has been exceeded: if the synchronization waiting time has been exceeded, jump to (9); if the synchronization waiting time has not been exceeded, jump to (3);

[0074] (9) Determine whether the logic of this control module is started: if the result of this control logic is started, jump to start the electric pump; if the result of this control logic is not started, jump to shut down the electric pump.

[0075] Furthermore, the onboard control 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.

[0076] Furthermore, in the above step S22, see Figure 2 As shown, judging whether the controlled mechanism needs pressure according to the flight control system state signal includes:

[0077] 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;

[0078] 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;

[0079] 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.

[0080] The embodiment of the present invention further provides an electric pump integrated control system, the system comprising an acquisition module, a data scheduling module, a comprehensive protection module and a plurality of electric pump control modules, the electric pump control module comprising a first logic judgment module, a second logic judgment module and an electric pump protection module;

[0081] All the electric pump control modules are connected in sequence to form a closed-loop control architecture, each of the electric pump control modules is connected to an electric pump, the output end of the acquisition module is connected to the input end of the data scheduling module and the comprehensive protection module, the data scheduling module and the comprehensive protection module are both connected to each of the electric pump control modules, and the comprehensive protection module includes an anti-error working module and a staggered working module.

[0082] Furthermore, the 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.

[0083] 1. By automating the control of the electric pump, the pilot does not need to spend a lot of energy on controlling the electric pump during the mission execution, which significantly reduces the pilot's workload;

[0084] 2. By adopting the error-proof working mechanism and staggered working mechanism according to different aircraft states to automatically control the opening and closing of the electric pump, the situation of turning on the electric pump throughout the whole process is avoided, which significantly reduces the energy consumption of the aircraft and improves the energy utilization efficiency;

[0085] 3. By designing the working protection mechanism of the electric pump, the starting sequence of the electric pump when it is needed on the aircraft is optimized, avoiding the problems of reducing the aircraft power supply and damaging 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;

[0086] 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;

[0087] 5. The electric pump protection mechanism designed in the present invention includes a timeout emergency mechanism, which can ensure the normal start-up of the electric pump and ensure the completeness and safety of aircraft functions in extreme cases where the electric pump protection mechanism fails to complete the predetermined function.

[0088] 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 integrated control methods for the operation of an electric pump is implemented.

[0089] Specifically, the computer device may be a computer terminal, a server or a similar computing device.

[0090] 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 integrated control methods for the operation of an electric pump.

[0091] 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.

[0092] 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.

[0093] 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 comprehensive control method for an electric pump, characterized in that: The method comprises: 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 start-up error prevention working instruction or a hydraulic pressure logic judgment instruction are output through an on-board status threshold and a first electric pump control logic, and the remaining electric pump control instructions are obtained according to the start-up error prevention working instruction, and the electric pump connected to the sub-hydraulic system is shut down through the electric pump shut-down instruction and the remaining electric pump control instructions through an error prevention working mechanism; The flight control system status signal and the hydraulic pressure are obtained according to the hydraulic pressure logic judgment instruction, and the electric pump connected to each sub-hydraulic system is automatically controlled by adopting the second electric pump control logic, anti-error working mechanism and staggered working mechanism through the low pressure threshold.

2. The electric pump operation comprehensive control method according to claim 1, characterized in that: The method further comprises: The on-board state threshold is set, and when the on-board state signal is less than the on-board state threshold, an electric pump shut-down instruction and an error prevention start-up instruction are output, and the error prevention mechanism is started according to the error prevention start-up instruction to shut down the electric pump; When the on-board status signal is greater 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 operation comprehensive control method according to claim 2, characterized in that: The 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, and if the hydraulic pressure is less than or equal to the low-pressure threshold, a start-up error prevention work instruction and a start-up time-shifting work instruction are output, and the electric pump is controlled to start through the error prevention work mechanism and the time-shifting work mechanism according to the start-up error prevention work instruction and the start-up time-shifting work instruction; if the hydraulic pressure is greater than the low-pressure threshold, a logic judgment instruction of the controlled mechanism on the machine 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, a start-up anti-error working instruction and a start-time mismatch working instruction are output, and the electric pump is controlled to be turned on through the anti-error working mechanism and the time mismatch working mechanism according to the start-up anti-error working instruction and the start-time mismatch working instruction; if it is judged that there is no pressure demand, a start-up anti-error working instruction is output, and the remaining electric pump control instructions are obtained according to the start-up anti-error working instruction, and the electric pump connected to the sub-hydraulic system is turned off through the anti-error working mechanism through the electric pump closing instruction and the remaining electric pump control instructions, so as to construct the second control logic.

4. The electric pump operation comprehensive control method according to claim 3, characterized in that: The method further comprises: Sequentially numbering the electric pumps connected to all the sub-hydraulic systems and establishing an association table of all the electric pumps; According to the association relationship table, the current control information of the associated electric pump is obtained as the remaining electric pump control instructions, and consistency judgment is performed on the remaining electric pump control instructions and the electric pump start and stop instructions; If the judgment result is consistent, the electric pump is controlled according to the current control information; if the judgment result is inconsistent, the control information failure result is reported to construct the error-proof working mechanism.

5. The electric pump operation comprehensive control method according to claim 4, characterized in that: The 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 staggered working mechanism.

6. The electric pump operation comprehensive control method according to any one of claims 3 to 5, characterized in that: The onboard control 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.

7. The electric pump operation comprehensive control method according to claim 6, 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.

8. An integrated control system for an electric pump, characterized in that: The system includes an acquisition module, a data scheduling module, a comprehensive protection module and a plurality of electric pump control modules, wherein the electric pump control module includes a first logic judgment module, a second logic judgment module and an electric pump protection module; All the electric pump control modules are connected in sequence to form a closed-loop control architecture, each of the electric pump control modules is connected to an electric pump, the output end of the acquisition module is connected to the input end of the data scheduling module and the comprehensive protection module, the data scheduling module and the comprehensive protection module are both connected to each of the electric pump control modules, and the comprehensive protection module includes an anti-error working module and a staggered working module.

Images