Redundancy automatic electric pump control method and system

Abstract

The invention belongs to the technical field of airborne electromechanical control, and discloses a redundancy automatic electric pump control method and system.The control method comprises the steps that airborne state signals, flight control system state signals and hydraulic pressure of each sub hydraulic system in a hydraulic system are collected in real time; and according to the onboard state signal, the flight control system state signal and the hydraulic pressure, an electric pump connected to each hydraulic sub-system is automatically controlled through electric pump control logic. The system comprises an acquisition module, a data scheduling module and a plurality of electric pump control modules, each electric pump control module is connected with an electric pump, and the output end of the acquisition module is connected with the input end of the data scheduling module. Automatic electric pump control logic is designed, energy consumption can be reduced by independently and accurately controlling each electric pump, single-point faults caused by failure of a control module are avoided, and flight safety is improved.

Description

Technical Field

[0001] The invention belongs to the technical field of airborne electromechanical control and relates to a redundant automatic electric pump control method and system. Background Art

[0002] Multi-engine transport aircraft often have a hydraulic system with a complex structure that includes multiple sub-hydraulic systems. Electric pumps are usually required to provide hydraulic or liquid power to drive and control the aircraft's landing gear, rudder control and other systems. The number of electric pumps in the transport aircraft system is related to the number of engines. For example, three-engine transport aircraft are generally equipped with three electric pumps.

[0003] At present, the control methods of electric pumps for multi-engine transport aircraft include full-time synchronous control and pilot control. The full-time synchronous control method is to start all electric pumps during the ground preparation stage and the flight stage of the aircraft, and shut down the electric pumps after the aircraft finally lands. Although this method does not increase the workload of the pilot during the flight stage, since the flight scenes 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, turning on all electric pumps during the flight consumes a lot of energy for the aircraft. The pilot control method is to hand over the control authority of the electric pump to the pilot, and the pilot decides the use and control of the electric pump according to the mission load requirements. This method saves energy on the aircraft to a certain extent, but since the aircraft needs to provide more systems with liquid power and the time is different, it is completely handed over to the pilot to control. The pilot needs to pay attention to multiple state combinations and control the electric pumps in multiple different time periods, which increases the pilot's workload; and because the pilot has his own flight mission, he often cannot control the electric pump in time, which reduces the efficiency of the pilot's mission execution and increases the possibility of the pilot making mistakes. Summary of the invention

[0004] In order to solve the technical problems of large aircraft energy consumption caused by turning on the electric pump of a multi-engine transport aircraft throughout the whole process, and increasing pilot workload and reducing flight safety caused by manual control by the pilot, the present invention discloses a redundant automatic electric pump control method, which includes 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. Automatically control the electric pump connected to each of the sub-hydraulic systems through electric pump control logic according to the onboard status signal, the flight control system status signal and the hydraulic pressure.

[0007] In an improved embodiment of the above-mentioned redundancy automatic electric pump control method, the control method further comprises: S1, constructing the electric pump control logic, including:

[0008] S11, setting an on-board state threshold, when the on-board state signal is less than the on-board state threshold, outputting an electric pump shut-down instruction, and when the on-board state signal is greater than or equal to the on-board state threshold, outputting a hydraulic pressure logic judgment instruction;

[0009] 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 electric pump start instruction if the hydraulic pressure is less than or equal to the low-pressure threshold; and outputting an on-board controlled mechanism logic judgment instruction if the hydraulic pressure is greater than the low-pressure threshold;

[0010] S13. 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 an electric pump start instruction; if it is judged that there is no pressure demand, output an electric pump close instruction.

[0011] 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.

[0012] Furthermore, in step S13, judging whether the controlled mechanism needs pressure according to the flight control system state signal includes:

[0013] 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;

[0014] 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;

[0015] S133: When any one or both of the control surface and the landing gear have pressure requirements, determine whether the controlled mechanism needs pressure.

[0016] An embodiment of the present invention also provides a redundant automatic electric pump control system, which includes an acquisition module, a data scheduling module and multiple electric pump control modules, each of the electric pump control modules is connected to an electric pump, and the acquisition module is used to collect on-board status signals, flight control system status signals and the hydraulic pressure of each sub-hydraulic system in the hydraulic system. The output end of the acquisition module is connected to the input end of the data scheduling module.

[0017] The data scheduling module is connected to each of the electric pump control modules, and the electric pump control module uses electric pump control logic to output an electric pump control signal based on the onboard status signal, the flight control system status signal and the hydraulic pressure extracted from the data scheduling module.

[0018] Furthermore, the electric pump control module includes a logic judgment module and an electric pump control instruction output module, the input end of the logic judgment module is connected to the data scheduling module, and the output end of the logic judgment module is connected to the electric pump via the electric pump control instruction output module.

[0019] Furthermore, there are 2 to 4 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.

[0020] Furthermore, the 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.

[0021] The electric pump control method and system of the present invention, by designing automatic electric pump control logic, can independently control multiple electric pumps when electric pumps are needed according to the application scenario of the aircraft, and can avoid single point failure caused by control module failure to improve flight safety. Specifically, it has the following advantages:

[0022] 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;

[0023] 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;

[0024] 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;

[0025] 4. 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

[0026] 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.

[0027] Figure 1 It is a structural diagram of the redundant automatic electric pump control system disclosed in an embodiment of the present invention;

[0028] Figure 2 It is a control logic execution diagram of an electric pump disclosed in an embodiment of the present invention;

[0029] 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

[0030] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0031] 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.

[0032] The embodiment of the present invention discloses a redundant automatic electric pump control system, see Figure 1 As shown, the control system 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.

[0033] The data scheduling module 102 is connected to each of the electric pump control modules 103 , and the electric pump control module 103 uses electric pump control logic to output an electric pump control signal based on the onboard status signal, the flight control system status signal and the hydraulic pressure extracted from the data scheduling module 102 .

[0034] Specifically, the hydraulic system can be a complex system with double redundancy, triple redundancy, quadruple redundancy or even high redundancy, and the corresponding electric pump control modules 103 also have 2 to 4, and each electric pump control module 103 is connected to one of the sub-hydraulic systems in the hydraulic system via one electric pump. Figure 1 As 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.

[0035] Furthermore, the electric pump control module 103 includes a logic judgment module and an electric pump control instruction output module, the input end of the logic judgment module is connected to the data scheduling module 102, and the output end of the logic judgment module is connected to the electric pump via the electric pump control instruction output module.

[0036] 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.

[0037] Based on the same inventive concept, an embodiment of the present invention further provides a redundancy automatic electric pump control method, which is implemented by the redundancy automatic electric pump control system described in the above embodiment, and the method comprises the following steps:

[0038] 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;

[0039] S3. Automatically control the electric pump connected to each of the sub-hydraulic systems through electric pump control logic according to the onboard status signal, the flight control system status signal and the hydraulic pressure.

[0040] In an improved embodiment of the above-mentioned redundancy automatic electric pump control method, see Figure 2 As shown, the control method further includes: S1, constructing the electric pump control logic, including:

[0041] S11, setting an on-board state threshold, when the on-board state signal is less than the on-board state threshold, outputting an electric pump shut-down instruction, and when the on-board state signal is greater than or equal to the on-board state threshold, outputting a hydraulic pressure logic judgment instruction;

[0042] 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 electric pump start instruction if the hydraulic pressure is less than or equal to the low-pressure threshold; and outputting an on-board controlled mechanism logic judgment instruction if the hydraulic pressure is greater than the low-pressure threshold;

[0043] S13. 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 an electric pump start instruction; if it is judged that there is no pressure demand, output an electric pump close instruction.

[0044] Further, in step S2, 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.

[0045] Furthermore, in step S13, judging whether the controlled mechanism needs pressure according to the flight control system state signal includes:

[0046] 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;

[0047] 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;

[0048] S133: When any one or both of the control surface and the landing gear have pressure requirements, determine whether the controlled mechanism needs pressure.

[0049] The electric pump control method and system of the present invention, by designing automatic electric pump control logic, can independently control multiple electric pumps when electric pumps are needed according to the application scenario of the aircraft, and can avoid single point failures and improve flight safety. Specifically, it has the following advantages:

[0050] 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;

[0051] 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;

[0052] 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;

[0053] 4. 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.

[0054] 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 redundancy automatic electric pump control methods is implemented.

[0055] Specifically, the computer device may be a computer terminal, a server or a similar computing device.

[0056] 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 redundancy automatic electric pump control methods.

[0057] 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.

[0058] 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.

[0059] 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 redundant automatic electric pump control method, characterized in that: The control 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 onboard status signal, the flight control system status signal and the hydraulic pressure, the electric pump connected to each of the sub-hydraulic systems is automatically controlled through the electric pump control logic.

2. The method for controlling a redundant automatic electric pump according to claim 1, characterized in that: The control method further includes constructing the electric pump control logic, including: Setting an on-board state threshold, when the on-board state signal is less than the on-board state threshold, outputting an electric pump shut-down instruction, and when the on-board state signal is greater than or equal to the on-board state threshold, outputting a hydraulic pressure logic judgment instruction; 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, an electric pump start instruction is output; if the hydraulic pressure is greater than the low-pressure threshold, a controlled mechanism logic judgment instruction is output; The flight control system status signal is obtained according to the logic judgment instruction of the 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 opening instruction is output, and if it is judged that there is no pressure demand, an electric pump closing instruction is output.

3. The method for controlling a redundant automatic electric pump according to claim 2, 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.

4. The method for controlling a redundant automatic electric pump according to claim 3, 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.

5. A redundant automatic electric pump control system, characterized in that: The 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, and the electric pump control module uses electric pump control logic to output an electric pump control signal based on the onboard status signal, the flight control system status signal and the hydraulic pressure extracted from the data scheduling module.

6. The redundancy automatic electric pump control system according to claim 5, characterized in that: The electric pump control module includes a logic judgment module and an electric pump control instruction output module. The input end of the logic judgment module is connected to the data scheduling module, and the output end of the logic judgment module is connected to the electric pump via the electric pump control instruction output module.

7. The redundancy automatic electric pump control system according to claim 5, characterized in that: There are 2 to 4 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.

8. The redundancy automatic electric pump control system according to any one of claims 5 to 7, characterized in that: The 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.

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