CN119878631A - Hydraulic transmission system protection method and system - Google Patents
Hydraulic transmission system protection method and system Download PDFInfo
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- CN119878631A CN119878631A CN202411957024.6A CN202411957024A CN119878631A CN 119878631 A CN119878631 A CN 119878631A CN 202411957024 A CN202411957024 A CN 202411957024A CN 119878631 A CN119878631 A CN 119878631A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B13/00—Details of servomotor systems ; Valves for servomotor systems
- F15B13/02—Fluid distribution or supply devices characterised by their adaptation to the control of servomotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/22—Operating mechanisms fluid
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B19/00—Testing; Calibrating; Fault detection or monitoring; Simulation or modelling of fluid-pressure systems or apparatus not otherwise provided for
- F15B19/005—Fault detection or monitoring
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B20/00—Safety arrangements for fluid actuator systems; Applications of safety devices in fluid actuator systems; Emergency measures for fluid actuator systems
- F15B20/002—Electrical failure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B20/00—Safety arrangements for fluid actuator systems; Applications of safety devices in fluid actuator systems; Emergency measures for fluid actuator systems
- F15B20/007—Overload
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B21/00—Common features of fluid actuator systems; Fluid-pressure actuator systems or details thereof, not covered by any other group of this subclass
- F15B21/02—Servomotor systems with programme control derived from a store or timing device; Control devices therefor
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid-Pressure Circuits (AREA)
Abstract
The invention belongs to the field of hydraulic transmission system design, and discloses a hydraulic transmission system protection method and system, wherein the protection method comprises the steps of collecting on-board state signals, flight control system state signals and first hydraulic pressure and second hydraulic pressure of each hydraulic pipeline in a hydraulic transmission system in real time; according to the on-board state signal, an electric pump closing instruction and a hydraulic pressure logic judging instruction are output through an on-board state threshold value and a first electric pump control logic, an electric pump connected to a hydraulic pipeline is closed according to the electric pump closing instruction, a flight control system state signal, a first hydraulic pressure and a second hydraulic pressure are obtained according to the hydraulic pressure logic judging instruction, and the electric pump is automatically controlled through a low-pressure threshold value and a pressure safety threshold value by adopting a second electric pump control mechanism and a hydraulic pipeline protection mechanism. The invention can automatically control the opening of each electric pump, protect the hydraulic passage through a plurality of mechanisms and improve the flight safety.
Description
Technical Field
The invention belongs to the field of hydraulic transmission system design, and relates to a hydraulic transmission system protection method and system.
Background
The output of an electric pump in an aircraft system is typically connected to an input of a hydraulic drive system, and the hydraulic magnitude or power is controlled by operation of the electric pump to drive operation of a mechanism connected to the hydraulic drive system. For example, in a hydraulic transmission system of an aircraft, an electric pump control system generally adopts dual redundancy or higher redundancy for control, the working scene and the use frequency of the electric pump are very high, manual control of a pilot is replaced by automatic control at present, but abnormal data sources or abnormal control logic can also occur in the control process, so that the electric pump is continuously and wrongly started or closed, wrong hydraulic power and hydraulic magnitude are provided for the hydraulic transmission system, and the flight safety is influenced after overpressure or undervoltage of the hydraulic transmission system is caused.
Disclosure of Invention
In order to solve the technical problems that when an automatic control hydraulic transmission system is used, an error hydraulic power is provided for the hydraulic transmission system, and the hydraulic pressure is excessively high or low-pressure, so that the normal operation and the safety of a mechanism are affected, and the like, due to the abnormality of a data source or control logic, the invention discloses a hydraulic transmission system protection method, which comprises the following steps:
S2, acquiring state signals on the aircraft, state signals of a flight control system and current hydraulic pressure of each hydraulic pipeline in the hydraulic transmission system in real time, wherein the current hydraulic pressure comprises a first hydraulic pressure and a second hydraulic pressure;
S3, outputting an electric pump closing instruction and a hydraulic pressure logic judging instruction through an on-board state threshold value and a first electric pump control logic according to the on-board state signal, and closing an electric pump connected to the hydraulic pipeline according to the electric pump closing instruction;
s4, acquiring a state signal of the flight control system, the first hydraulic pressure and the second hydraulic pressure according to a hydraulic pressure logic judging instruction, and automatically controlling each electric pump connected to the hydraulic pipeline by adopting a second electric pump control mechanism and a hydraulic pipeline protection mechanism through a low-pressure threshold value and a pressure safety threshold value.
Further, the method further comprises:
And S11, setting the on-board state threshold, outputting an electric pump closing instruction when the on-board state signal is smaller than the on-board state threshold, and outputting a hydraulic pressure logic judging instruction when the on-board state signal is larger than or equal to the on-board state threshold to construct the first electric pump control logic.
Still further, the method further comprises:
S12, giving the low pressure threshold and the pressure safety threshold, acquiring the first hydraulic pressure according to the hydraulic pressure logic judging instruction, comparing the first hydraulic pressure with the low pressure threshold, outputting a starting hydraulic pipeline protecting instruction if the first hydraulic pressure is smaller than or equal to the low pressure threshold, and starting and controlling the electric pump connected to the hydraulic pipeline according to the starting hydraulic pipeline protecting instruction through the second hydraulic pressure, the pressure safety threshold and the hydraulic pipeline protecting mechanism;
The control logic comprises a control logic module, a control logic module and a control logic module, wherein the control logic module is used for acquiring a flight control system state signal according to an on-board controlled mechanism logic judging instruction, judging whether the controlled mechanism needs pressure according to the flight control system state signal, outputting a starting hydraulic pipeline protection instruction if the pressure needs, starting and controlling the electric pump connected to the hydraulic pipeline according to the starting hydraulic pipeline protection instruction through the second hydraulic pressure, the pressure safety threshold and the hydraulic pipeline protection mechanism, and outputting an electric pump closing instruction if the pressure needs are judged to be absent, and constructing the second electric pump control logic.
Still further, the method further comprises:
S13, acquiring the second hydraulic pressure according to the starting hydraulic pipeline protection instruction, comparing the second hydraulic pressure with the pressure safety threshold, outputting an instruction for shutting down the electric pump, an electric pump prohibition start mark and an overpressure alarm signal to the second electric pump control logic if the second hydraulic pressure is greater than or equal to the pressure safety threshold, and outputting an electric pump start mark to the second electric pump control logic if the second hydraulic pressure is less than the pressure safety threshold, so as to construct the hydraulic pipeline protection mechanism.
Preferably, the method further comprises:
And S14, starting timing after outputting the hydraulic pipeline protection starting instruction, and starting an overtime emergency mechanism when the second electric pump control logic does not receive the electric pump start prohibition mark or the electric pump start mark output by the hydraulic pipeline protection mechanism within a set time period, and controlling the electric pump to start by adopting the electric pump start instruction output by the second electric pump control logic according to the overtime emergency mechanism.
Further, the flight control system status signals include landing gear signals and control surface status signals, the on-board status signals include ground speed signals, and the controlled mechanism includes landing gear and control surface.
Further, in step S12, determining whether the controlled mechanism requires pressure according to the flight control system status signal includes:
S121, judging whether the undercarriage has pressure requirements according to the undercarriage signals, and judging that the undercarriage has pressure requirements if the undercarriage signals are the retraction signals or the extension signals;
S122, judging whether the control surface has pressure requirements according to the control surface state signal, and judging that the control surface has pressure requirements if the control surface state signal is a control surface position signal change;
and S123, when any one or both of the control surface and the landing gear have pressure requirements, judging that the controlled mechanism needs pressure.
The embodiment of the invention also provides a hydraulic transmission system protection system, which comprises an acquisition module, a data scheduling module, a monitoring module and a plurality of electric pump control modules, wherein each electric pump control module is respectively connected with an electric pump, and the output end of the acquisition module is connected with the input ends of the data scheduling module and the monitoring module;
The data scheduling module and the monitoring module are connected with each electric pump control module, the electric pump control modules adopt first electric pump control logic and second electric pump control logic to output electric pump control signals and starting hydraulic pipeline protection instructions according to on-board state signals, flight control system state signals and first hydraulic pressure of the hydraulic pipelines extracted from the data scheduling module, and the monitoring module extracts second hydraulic pressure of the hydraulic pipelines according to the starting hydraulic pipeline protection instructions and outputs electric pump start marks or electric pump start prohibition marks to the electric pump control modules through the second hydraulic pressure and pressure safety thresholds.
Further, the protection system further comprises a power supply module, wherein the input end of the power supply module is connected with an onboard power supply, the output end of the power supply module is connected with the acquisition module, the data scheduling module, the monitoring module and each electric pump control module, and the power supply module supplies power for the acquisition module, the data scheduling module, the monitoring module and the electric pump control module.
Further, the hydraulic transmission system is provided with at least two hydraulic pipelines, the electric pump control modules are at least two, each electric pump control module is connected with one hydraulic pipeline in the hydraulic transmission system through one electric pump respectively, and the acquisition module is connected with the hydraulic pipeline through two acquisition channels.
Compared with the prior art, the beneficial effects that above-mentioned at least one technical scheme that this description embodiment adopted can reach include at least:
1. By automatically controlling the electric pump on the hydraulic pipeline, the pilot does not need to use a great deal of energy for controlling related work of the electric pump in the task execution process, so that the workload of the pilot is obviously reduced;
2. The automatic control device has the advantages that the opening and closing of the electric pump are automatically controlled according to different aircraft states, the situation that the electric pump needs to be opened in the whole course is avoided, the energy consumption of the aircraft is obviously reduced, the energy utilization efficiency is improved, the situation that the hydraulic transmission system is damaged by overpressure in the hydraulic pipeline is avoided, and the flight safety is improved;
3. The hydraulic transmission system is designed with two-stage protection, the state of each hydraulic pipeline is continuously and independently monitored through the design monitoring module, overpressure warning information can be output to the electric pump control module when the safety risk of overlarge pressure of the hydraulic pipeline occurs, when the internal fault of the electric pump control module is caused by a data source or logic abnormality, the electric pump can be timely closed, otherwise, if more serious conditions such as the driving hardware fault of the control module occur, the monitoring module can be used as a second defense line to directly shut off the corresponding electric pump, and the protection effect is enhanced;
4. the safety design of configuring the electric pump control module for each hydraulic pipeline in the protection system avoids the problems of control failure and damage to the hydraulic transmission system caused by single fault, and enhances the safety of the aircraft;
5. The overtime emergency mechanism is designed on the basis of the hydraulic pipeline protection mechanism, so that the electric pump can be ensured to be normally started under the extreme condition that the electric pump control module fails to receive the indication signal of the monitoring module, and the integrity and safety of the airplane function are ensured.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flow chart of a hydraulic drive system protection method disclosed in an embodiment of the present invention;
FIG. 2 is an algorithm flow of a hydraulic line protection mechanism disclosed in an embodiment of the present invention;
FIG. 3 is a flowchart of an algorithm after a second electric pump control output starts a hydraulic line protection command according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of a hydraulic drive system protection system according to an embodiment of the present disclosure;
The device comprises a1, an acquisition module; 2, a data scheduling module, 3, a monitoring module, 4, an electric pump control module and 5, a power supply module.
Detailed Description
Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the following disclosure, which describes the embodiments of the present application with reference to specific examples. It will be apparent that the described embodiments are only some, but not all, embodiments of the application. The application may be practiced or carried out in other embodiments that depart from the specific details, and the details of the present description may be modified or varied from the spirit and scope of the present application. It should be noted that the following embodiments and features of the embodiments may be combined with each other without conflict. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
The embodiment of the invention discloses a hydraulic transmission system protection method, which is shown in fig. 1 and 2, and comprises the following steps:
S2, acquiring state signals on the aircraft, state signals of a flight control system and current hydraulic pressure of each hydraulic pipeline in the hydraulic transmission system in real time, wherein the current hydraulic pressure comprises a first hydraulic pressure and a second hydraulic pressure;
S3, outputting an electric pump closing instruction and a hydraulic pressure logic judging instruction through an on-board state threshold value and a first electric pump control logic according to the on-board state signal, and closing an electric pump connected to the hydraulic pipeline according to the electric pump closing instruction;
s4, acquiring a state signal of the flight control system, the first hydraulic pressure and the second hydraulic pressure according to a hydraulic pressure logic judging instruction, and automatically controlling each electric pump connected to the hydraulic pipeline by adopting a second electric pump control mechanism and a hydraulic pipeline protection mechanism through a low-pressure threshold value and a pressure safety threshold value.
Further, referring to fig. 1 and 2, the method further includes:
And S11, setting the on-board state threshold, outputting an electric pump closing instruction when the on-board state signal is smaller than the on-board state threshold, and outputting a hydraulic pressure logic judging instruction when the on-board state signal is larger than or equal to the on-board state threshold to construct the first electric pump control logic.
Still further, referring to fig. 1 and 2, the method further includes:
S12, giving the low pressure threshold and the pressure safety threshold, acquiring the first hydraulic pressure according to the hydraulic pressure logic judging instruction, comparing the first hydraulic pressure with the low pressure threshold, outputting a starting hydraulic pipeline protecting instruction if the first hydraulic pressure is smaller than or equal to the low pressure threshold, and starting and controlling the electric pump connected to the hydraulic pipeline according to the starting hydraulic pipeline protecting instruction through the second hydraulic pressure, the pressure safety threshold and the hydraulic pipeline protecting mechanism;
The control logic comprises a control logic module, a control logic module and a control logic module, wherein the control logic module is used for acquiring a flight control system state signal according to an on-board controlled mechanism logic judging instruction, judging whether the controlled mechanism needs pressure according to the flight control system state signal, outputting a starting hydraulic pipeline protection instruction if the pressure needs, starting and controlling the electric pump connected to the hydraulic pipeline according to the starting hydraulic pipeline protection instruction through the second hydraulic pressure, the pressure safety threshold and the hydraulic pipeline protection mechanism, and outputting an electric pump closing instruction if the pressure needs are judged to be absent, and constructing the second electric pump control logic.
Still further, referring to fig. 1 and 2, the method further includes:
S13, acquiring the second hydraulic pressure according to the starting hydraulic pipeline protection instruction, comparing the second hydraulic pressure with the pressure safety threshold, outputting an instruction for shutting down the electric pump, an electric pump prohibition start mark and an overpressure alarm signal to the second electric pump control logic if the second hydraulic pressure is greater than or equal to the pressure safety threshold, and outputting an electric pump start mark to the second electric pump control logic if the second hydraulic pressure is less than the pressure safety threshold, so as to construct the hydraulic pipeline protection mechanism.
Preferably, the method shown in fig. 3 further comprises:
And S14, starting timing after outputting the hydraulic pipeline protection starting instruction, and starting an overtime emergency mechanism when the second electric pump control logic does not receive the electric pump start prohibition mark or the electric pump start mark output by the hydraulic pipeline protection mechanism within a set time period, and controlling the electric pump to start by adopting the electric pump start instruction output by the second electric pump control logic according to the overtime emergency mechanism.
Further, the flight control system status signals include landing gear signals and control surface status signals, the on-board status signals include ground speed signals, and the controlled mechanism includes landing gear and control surface.
Still further, referring to fig. 1 and 2, in step S12, determining whether the controlled mechanism requires pressure according to the flight control system status signal includes:
S121, judging whether the undercarriage has pressure requirements according to the undercarriage signals, and judging that the undercarriage has pressure requirements if the undercarriage signals are the retraction signals or the extension signals;
S122, judging whether the control surface has pressure requirements according to the control surface state signal, and judging that the control surface has pressure requirements if the control surface state signal is a control surface position signal change;
and S123, when any one or both of the control surface and the landing gear have pressure requirements, judging that the controlled mechanism needs pressure.
Based on the same inventive concept, a hydraulic transmission system protection system is also provided in the embodiments of the present invention, as described in the following embodiments. The hydraulic transmission system protection system is used for realizing the hydraulic transmission system protection method. As used below, the term "unit" or "module" may be a combination of software and/or hardware that implements the intended function. While the means described in the following embodiments are preferably implemented in software, implementation in hardware, or a combination of software and hardware, is also possible and contemplated.
Referring to fig. 4, the protection system includes a collection module 1, a data scheduling module 2, a monitoring module 3 and a plurality of electric pump control modules 4, each electric pump control module 4 is connected with an electric pump, and an output end of the collection module 1 is connected with input ends of the data scheduling module 2 and the monitoring module 3.
The data scheduling module 2 and the monitoring module 3 are connected with each electric pump control module 4, the electric pump control modules 4 adopt first electric pump control logic and second electric pump control logic to output electric pump control signals and starting hydraulic pipeline protection instructions according to on-board state signals, flight control system state signals and first hydraulic pressure of hydraulic pipelines extracted from the data scheduling module 2, and the monitoring module 3 extracts second hydraulic pressure of the hydraulic pipelines according to the starting hydraulic pipeline protection instructions and outputs electric pump start marks or electric pump forbidden start marks to the electric pump control modules 4 through the second hydraulic pressure and pressure safety thresholds.
Further, the protection system further comprises a power supply module 5, the input end of the power supply module 5 is connected with an on-board power supply, the output end of the power supply module 5 is connected with the acquisition module 1, the data scheduling module 2, the monitoring module 3 and each electric pump control module 4, and the power supply module 5 supplies power for the acquisition module 1, the data scheduling module 2, the monitoring module 3 and the electric pump control modules 4.
Further, there are at least two hydraulic pipelines in the hydraulic transmission system, there are at least two electric pump control modules 4, each electric pump control module 4 is connected with one hydraulic pipeline in the hydraulic transmission system through one electric pump, and the acquisition module is connected with the hydraulic pipeline through two acquisition channels.
1. By automatically controlling the electric pump on the hydraulic pipeline, the pilot does not need to use a great deal of energy for controlling related work of the electric pump in the task execution process, so that the workload of the pilot is obviously reduced;
2. The automatic control device has the advantages that the opening and closing of the electric pump are automatically controlled according to different aircraft states, the situation that the electric pump needs to be opened in the whole course is avoided, the energy consumption of the aircraft is obviously reduced, the energy utilization efficiency is improved, the situation that the hydraulic transmission system is damaged by overpressure in the hydraulic pipeline is avoided, and the flight safety is improved;
3. The hydraulic transmission system is designed with two-stage protection, the state of each hydraulic pipeline is continuously and independently monitored through the design monitoring module, overpressure warning information can be output to the electric pump control module when the safety risk of overlarge pressure of the hydraulic pipeline occurs, when the internal fault of the electric pump control module is caused by a data source or logic abnormality, the electric pump can be timely closed, otherwise, if more serious conditions such as the driving hardware fault of the control module occur, the monitoring module can be used as a second defense line to directly shut off the corresponding electric pump, and the protection effect is enhanced;
4. the safety design of configuring the electric pump control module for each hydraulic pipeline in the protection system avoids the problems of control failure and damage to the hydraulic transmission system caused by single fault, and enhances the safety of the aircraft;
5. The overtime emergency mechanism is designed on the basis of the hydraulic pipeline protection mechanism, so that the electric pump can be ensured to be normally started under the extreme condition that the electric pump control module fails to receive the indication signal of the monitoring module, and the integrity and safety of the airplane function are ensured.
It will be apparent to those skilled in the art that the foregoing is merely a preferred embodiment of the present invention and is not intended to limit the invention, and that various modifications and variations can be made to the embodiment of the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A method of hydraulic drive system protection, the method comprising:
acquiring state signals on the aircraft, state signals of a flight control system and current hydraulic pressure of each hydraulic pipeline in a hydraulic transmission system in real time, wherein the current hydraulic pressure comprises a first hydraulic pressure and a second hydraulic pressure;
Outputting an electric pump closing instruction and a hydraulic pressure logic judging instruction through an on-board state threshold value and a first electric pump control logic according to the on-board state signal, and closing an electric pump connected to the hydraulic pipeline according to the electric pump closing instruction;
And acquiring the state signal of the flight control system, the first hydraulic pressure and the second hydraulic pressure according to the hydraulic pressure logic judging instruction, and automatically controlling the electric pump connected to each hydraulic pipeline by adopting a second electric pump control mechanism and a hydraulic pipeline protection mechanism through a low-pressure threshold value and a pressure safety threshold value.
2. The hydraulic drive system protection method of claim 1, further comprising:
And setting the on-board state threshold, outputting an electric pump closing instruction when the on-board state signal is smaller than the on-board state threshold, and outputting a hydraulic pressure logic judging instruction when the on-board state signal is larger than or equal to the on-board state threshold to construct the first electric pump control logic.
3. The hydraulic drive system protection method of claim 2, further comprising:
Giving the low pressure threshold and the pressure safety threshold, acquiring the first hydraulic pressure according to the hydraulic pressure logic judging instruction, comparing the first hydraulic pressure with the low pressure threshold, outputting a starting hydraulic pipeline protecting instruction if the first hydraulic pressure is smaller than or equal to the low pressure threshold, and starting and controlling the electric pump connected to the hydraulic pipeline according to the starting hydraulic pipeline protecting instruction through the second hydraulic pressure, the pressure safety threshold and the hydraulic pipeline protecting mechanism;
The control logic comprises a control logic module, a control logic module and a control logic module, wherein the control logic module is used for acquiring a flight control system state signal according to an on-board controlled mechanism logic judging instruction, judging whether the controlled mechanism needs pressure according to the flight control system state signal, outputting a starting hydraulic pipeline protection instruction if the pressure needs, starting and controlling the electric pump connected to the hydraulic pipeline according to the starting hydraulic pipeline protection instruction through the second hydraulic pressure, the pressure safety threshold and the hydraulic pipeline protection mechanism, and outputting an electric pump closing instruction if the pressure needs are judged to be absent, and constructing the second electric pump control logic.
4. A method of protecting a hydraulic drive system according to claim 3, further comprising:
And acquiring the second hydraulic pressure according to the starting hydraulic pipeline protection instruction, comparing the second hydraulic pressure with the pressure safety threshold, outputting an instruction for stopping the electric pump, an electric pump prohibition start mark and an overpressure alarm signal to the second electric pump control logic if the second hydraulic pressure is greater than or equal to the pressure safety threshold, and outputting an electric pump start mark to the second electric pump control logic if the second hydraulic pressure is less than the pressure safety threshold, so as to construct the hydraulic pipeline protection mechanism.
5. The hydraulic transmission system protection method according to claim 4, wherein timing is started after the hydraulic line protection start command is output, and the second electric pump control logic starts a timeout emergency mechanism when the electric pump prohibition start flag or the electric pump start flag output by the hydraulic line protection mechanism is not received within a set time period, and controls the electric pump to start according to the electric pump start command output by the second electric pump control logic by the timeout emergency mechanism.
6. The hydraulic drive system protection method of any one of claims 3-5, wherein the flight control system status signals include landing gear signals and control surface status signals, the on-board status signals include ground speed signals, and the controlled mechanism includes landing gear and control surface.
7. The method of claim 6, wherein determining whether pressure is required by the controlled mechanism based on the flight control system status signal comprises:
judging whether the undercarriage has pressure requirements according to the undercarriage signal, and judging that the undercarriage has pressure requirements if the undercarriage signal is a stowage signal or a down signal;
judging whether the control surface has pressure requirements according to the control surface state signal, and judging that the control surface has pressure requirements if the control surface state signal is a control surface position signal change;
when any one or both of the control surface and the landing gear have pressure requirements, judging that the controlled mechanism needs pressure.
8. The hydraulic transmission system protection system is characterized by comprising an acquisition module, a data scheduling module, a monitoring module and a plurality of electric pump control modules, wherein each electric pump control module is respectively connected with an electric pump, and the output end of the acquisition module is connected with the input ends of the data scheduling module and the monitoring module;
The data scheduling module and the monitoring module are connected with each electric pump control module, the electric pump control modules adopt first electric pump control logic and second electric pump control logic to output electric pump control signals and starting hydraulic pipeline protection instructions according to on-board state signals, flight control system state signals and first hydraulic pressure of the hydraulic pipelines extracted from the data scheduling module, and the monitoring module extracts second hydraulic pressure of the hydraulic pipelines according to the starting hydraulic pipeline protection instructions and outputs electric pump start marks or electric pump start prohibition marks to the electric pump control modules through the second hydraulic pressure and pressure safety thresholds.
9. The hydraulic drive system protection system of claim 8, further comprising a power module having an input connected to an on-board power supply and an output connected to the collection module, the data scheduling module, the monitoring module, and each of the electric pump control modules, the power module powering the collection module, the data scheduling module, the monitoring module, and the electric pump control module.
10. The hydraulic drive system of claim 8, wherein there are at least two hydraulic lines in the hydraulic drive system, there are at least two electric pump control modules, each electric pump control module is connected to one of the hydraulic lines in the hydraulic drive system via one of the electric pumps, and the collection module is connected to the hydraulic lines via two collection paths.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411957024.6A CN119878631A (en) | 2024-12-29 | 2024-12-29 | Hydraulic transmission system protection method and system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411957024.6A CN119878631A (en) | 2024-12-29 | 2024-12-29 | Hydraulic transmission system protection method and system |
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| Publication Number | Publication Date |
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| CN119878631A true CN119878631A (en) | 2025-04-25 |
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| CN202411957024.6A Pending CN119878631A (en) | 2024-12-29 | 2024-12-29 | Hydraulic transmission system protection method and system |
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- 2024-12-29 CN CN202411957024.6A patent/CN119878631A/en active Pending
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