CN114810697B - Wheel holding mechanism hydraulic system - Google Patents
Wheel holding mechanism hydraulic system Download PDFInfo
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- CN114810697B CN114810697B CN202210623705.3A CN202210623705A CN114810697B CN 114810697 B CN114810697 B CN 114810697B CN 202210623705 A CN202210623705 A CN 202210623705A CN 114810697 B CN114810697 B CN 114810697B
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- module
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- oil cylinder
- hydraulic system
- landing gear
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- 238000012544 monitoring process Methods 0.000 claims abstract description 17
- 239000003921 oil Substances 0.000 claims description 85
- 238000006073 displacement reaction Methods 0.000 claims description 9
- 239000010720 hydraulic oil Substances 0.000 claims description 9
- 239000007788 liquid Substances 0.000 claims description 7
- 230000002457 bidirectional effect Effects 0.000 claims description 5
- 238000001816 cooling Methods 0.000 claims description 4
- 230000000593 degrading effect Effects 0.000 claims description 4
- 230000002159 abnormal effect Effects 0.000 claims description 3
- 238000001914 filtration Methods 0.000 claims description 3
- 238000003825 pressing Methods 0.000 claims description 2
- 238000005056 compaction Methods 0.000 claims 2
- 238000005299 abrasion Methods 0.000 abstract description 2
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 230000006835 compression Effects 0.000 description 4
- 238000007906 compression Methods 0.000 description 4
- 238000012423 maintenance Methods 0.000 description 4
- 230000001105 regulatory effect Effects 0.000 description 3
- 230000001276 controlling effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 239000010729 system oil Substances 0.000 description 2
- 230000003749 cleanliness Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012208 gear oil Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Classifications
-
- 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
- F15B11/00—Servomotor systems without provision for follow-up action; Circuits therefor
- F15B11/16—Servomotor systems without provision for follow-up action; Circuits therefor with two or more servomotors
-
- 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
-
- 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
- F15B11/00—Servomotor systems without provision for follow-up action; Circuits therefor
- F15B11/02—Systems essentially incorporating special features for controlling the speed or actuating force of an output member
- F15B11/028—Systems essentially incorporating special features for controlling the speed or actuating force of an output member for controlling the actuating force
-
- 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
- F15B11/00—Servomotor systems without provision for follow-up action; Circuits therefor
- F15B11/02—Systems essentially incorporating special features for controlling the speed or actuating force of an output member
- F15B11/04—Systems essentially incorporating special features for controlling the speed or actuating force of an output member for controlling the speed
-
- 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
-
- 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
- F15B2211/00—Circuits for servomotor systems
- F15B2211/80—Other types of control related to particular problems or conditions
- F15B2211/875—Control measures for coping with failures
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Fluid-Pressure Circuits (AREA)
Abstract
The invention relates to the technical field of hydraulic control systems, in particular to a hydraulic system of a wheel holding mechanism. The aircraft landing gear mainly aims at solving the problems that the existing aircraft landing gear lacks a perfect hydraulic system in use, the output of the aircraft landing gear is unstable, the riding comfort is affected, and the abrasion of the landing gear tires is serious, and the following technical scheme is provided: the system comprises a hydraulic system, an operation monitoring system and a fault feedback system, wherein the output end of the operation monitoring system is connected with the input ends of the hydraulic system and the fault feedback system respectively. The hydraulic control system is stable and accurate in use, effectively stably outputs and uses the oil cylinder, improves the use stability and safety of the aircraft landing gear, prolongs the service life of equipment, monitors the hydraulic system, feeds back faults in time, is beneficial to optimizing the hydraulic system, and is mainly applied to hydraulic control of the aircraft landing gear.
Description
Technical Field
The invention relates to the technical field of hydraulic control systems, in particular to a hydraulic system of a wheel holding mechanism.
Background
The landing gear is the only part for supporting the whole aircraft, so that the landing gear is an integral part of the aircraft, the running state of the oil cylinder is controlled by the aircraft landing gear through the hydraulic system, the shrinkage use and adjustment of the aircraft landing gear are ensured, and the pressure and flow of the hydraulic system are greatly improved. Therefore, the patent CN209479960U proposes an aircraft landing gear retraction hydraulic system, and in the scheme, the oil supply pressure of the system can be regulated by regulating a pressure regulating valve, so that the pressure requirement required by the test is met; the unloading valve is arranged, the set pressure of the unloading valve is higher than the rated working pressure of the system, and the system is protected from overhigh pressure; the system oil return pipeline is provided with a cooler, the cooling of the oil liquid is realized through the cooler, the temperature requirement of a working medium is met, and filters are added on an inlet pipeline, an outlet pipeline and the system oil return pipeline of the oil pump so as to ensure the cleanliness of the oil liquid; the system uses a pressure transmitter and a temperature sensor to be matched with a secondary meter to respectively display the oil supply pressure and the oil tank temperature of the system, and the secondary meter is used for ensuring the retraction and the extension of the undercarriage of the aircraft; the hydraulic system is used for simplifying the operation flow, is quick and convenient to use, if the hydraulic system has only a single operation mode in use, the hydraulic system is extremely easy to cause control failure when the operation mode is failed, thereby causing danger, and when the landing gear is used, only the landing gear oil cylinder is accurately controlled to be stable, the aircraft can be more stable, the abrasion of the landing gear tyre is reduced, the service life of equipment is prolonged, and the existing aircraft landing gear is lack of a perfect hydraulic system in use; in view of this, we propose a wheel holding mechanism hydraulic system.
Disclosure of Invention
The invention aims to solve the problems that the prior aircraft landing gear in the background technology lacks a perfect hydraulic system, the output of the aircraft landing gear is unstable, the riding comfort is affected and the tire of the landing gear is seriously worn, and provides a wheel holding mechanism hydraulic system.
The technical scheme of the invention is as follows: the hydraulic system of the wheel holding mechanism comprises a hydraulic system, an operation monitoring system and a fault feedback system, wherein the output end of the operation monitoring system is respectively connected with the input ends of the hydraulic system and the fault feedback system, the hydraulic system comprises an automatic oil source loop module, a semi-automatic/manual loop module, a clamping lifting hydraulic valve group module, a connecting pipeline module, a control box and a cable module, and the output ends of the semi-automatic/manual loop module and the clamping lifting hydraulic valve group module are respectively connected with a left lifting oil cylinder module, a right lifting oil cylinder module, a left rotating oil cylinder module, a right clamping oil cylinder module and a left pressing oil cylinder module;
The operation monitoring system is used for monitoring the operation condition of the hydraulic system and transmitting an abnormal fault part to the fault feedback system, the fault feedback system is used for receiving fault information and judging whether the information is faulty or not, and if the information is correct fault information, the fault information is uploaded to the hydraulic system;
the connecting pipeline module is used for connecting pipelines among the modules, and the control box and the cable module are used for controlling the operation of the hydraulic system and storing fault information in a backup mode.
Preferably, the automatic oil source loop module is used for providing hydraulic oil with required pressure and flow for each module in the hydraulic system and is used for realizing stable output of the pressure oil of the hydraulic system and accurate control of pressure and displacement.
Preferably, the hydraulic oil treatment comprises precise filtration, hydraulic preheating, oil return cooling, monitoring of the liquid level and the temperature of the oil tank and alarming, and the maximum pressure of the control system is as follows: pmax=21.0 MPa, hydraulic system maximum flow: qmax=50.00l/min, hydraulic oil temperature: +30 to +70℃.
Preferably, the semi-automatic/manual loop module is started to be used when the automatic oil source loop module fails to work, is used for degrading the using function, loosening the front landing gear tyre of the aircraft, and is used for descending the left lifting oil cylinder and the right lifting oil cylinder, loosening and extending the clamping oil cylinder, opening the rotating oil cylinder and unlocking the compacting oil cylinder.
Preferably, the clamping and lifting hydraulic valve group module is used for lifting or lowering, clamping or loosening, opening or holding tightly or unlocking the front landing gear tyre of the aircraft.
Preferably, the left and right lifting oil cylinder modules comprise plug-in type proportional overflow valves and pressure sensors, the plug-in type proportional overflow valves are used for setting pressure for the oil cylinders, the pressure sensors are used for feeding back the pressure, and the left and right lifting oil cylinder modules are used for lifting or descending the front landing gear tires of the aircraft and are single-acting oil cylinders.
Preferably, the left and right rotary oil cylinder module is used for clamping or loosening the front landing gear tyre of the aircraft, the left and right rotary oil cylinder module comprises a plug-in type proportional overflow valve, a bidirectional hydraulic control one-way valve and a left and right pressure sensor, the left and right rotary oil cylinder module is a double-acting oil cylinder, and the left and right pressure sensor is used for feeding back real-time clamping force.
Preferably, the left and right clamping cylinder modules are used for opening or holding the front landing gear tires of the aircraft, the left and right clamping cylinder modules are double-acting cylinders, the left and right clamping cylinder modules further comprise unidirectional hydraulic control check valves, plug-in type proportional overflow valves, left and right linear displacement sensors and left and right pressure sensors, the unidirectional hydraulic control check valves are used for pressure maintaining and locking, and the left and right linear displacement sensors are used for measuring the sizes of the front landing gear tires.
Preferably, the left and right compression cylinder modules are used for compressing or unlocking the front landing gear tires of the aircraft and are single-acting cylinders of rear springs, and the left and right compression cylinder modules further comprise unidirectional hydraulic control check valves and plug-in type proportional overflow valves.
Preferably, the bidirectional hydraulic control one-way valve and the unidirectional hydraulic control one-way valve are both arranged in a rod cavity of the oil cylinder.
Compared with the prior art, the invention has the following beneficial technical effects:
1. The hydraulic system uses liquid as a medium, the pressure generated by the hydraulic system is used for transferring energy, the automatic oil source loop module supplies energy through the chassis, the chassis gear pump is used for converting mechanical energy into hydraulic energy, the execution cylinder is used for converting hydraulic energy into mechanical energy, in the process of converting hydraulic energy into mechanical energy, the electromagnetic reversing valve is used for realizing the regulation of the action and the direction of the execution cylinder, the electromagnetic reversing valve and the proportional overflow valve are used for realizing the regulation of the movement speed, the control of the force and the position control of the throttle valve, and the hydraulic cylinder is used for realizing the position maintenance of the hydraulic cylinder, so that the stable output and the position maintenance of the front landing gear of the airplane are realized, the stability of the movement of the airplane is improved, and the riding comfort is improved;
2. The invention also uses the semi-automatic/manual loop module to degrade the use function when the automatic oil source loop module fails, ensures the release of the front landing gear tyre of the aircraft, ensures the normal movement of the aircraft, detects the whole hydraulic system by the operation detection system, and feeds back the failure to the hydraulic system after the failure is determined by the failure feedback system, so that the hydraulic system acquires the failure defect, is used for providing support for the optimization of the hydraulic system, and ensures the continuous perfection of the hydraulic system;
3. in conclusion, the hydraulic control system is stable and accurate in use, the oil cylinder is effectively and stably output and used, the stability and safety of the use of the landing gear of the aircraft are improved, the service life of equipment is prolonged, the hydraulic system is monitored, faults are timely fed back, and the hydraulic system is optimized.
Drawings
Fig. 1 is a schematic block diagram of a wheel locking mechanism hydraulic system.
Detailed Description
The technical scheme of the invention is further described below with reference to the attached drawings and specific embodiments.
Examples
As shown in fig. 1, the hydraulic system of the wheel holding mechanism provided by the invention comprises a hydraulic system, an operation monitoring system and a fault feedback system, wherein the output end of the operation monitoring system is respectively connected with the input ends of the hydraulic system and the fault feedback system, the hydraulic system comprises an automatic oil source loop module, a semi-automatic/manual loop module, a clamping lifting hydraulic valve group module, a connecting pipeline module, a control box and a cable module, the automatic oil source loop module is used for providing hydraulic oil with required pressure and flow for each module in the hydraulic system, the hydraulic oil processing comprises precise filtration, hydraulic preheating, return oil cooling, monitoring and alarming of the liquid level and the temperature of an oil tank, and the control system is used for realizing the precise output, the pressure and the displacement control of the pressure oil of the hydraulic system: pmax=21.0 MPa, hydraulic system maximum flow: qmax=50.00l/min, hydraulic oil temperature: the output ends of the +30 ℃ to +70 ℃ semi-automatic/manual loop module and the clamping lifting hydraulic valve group module are respectively connected with a left lifting oil cylinder module, a right rotating oil cylinder module, a left clamping oil cylinder module and a right clamping oil cylinder module;
the operation monitoring system is used for monitoring the operation condition of the hydraulic system and transmitting the abnormal fault part to the fault feedback system, the fault feedback system is used for receiving fault information and judging whether the information is faulty or not, and if the information is correct fault information, the fault information is uploaded to the hydraulic system;
the connecting pipeline module is used for connecting pipelines among the modules, and the control box and the cable module are used for controlling the operation of the hydraulic system and backing up and storing fault information;
The semi-automatic/manual loop module is started to be used when the automatic oil source loop module fails to work, is used for degrading the use function, loosening the front landing gear tyre of the aircraft, and is used for descending the left and right lifting cylinders, loosening and extending the clamping cylinders, opening the rotating cylinders and unlocking the compacting cylinders; the clamping and lifting hydraulic valve group module is used for lifting or descending, clamping or loosening, opening or holding, compacting or unlocking the front landing gear tyre of the aircraft; the left lifting oil cylinder module and the right lifting oil cylinder module are used for lifting or lowering the front landing gear tyre of the aircraft and are single-acting oil cylinders; the left-right rotating oil cylinder module is used for clamping or loosening the front landing gear tyre of the aircraft and comprises a plug-in type proportional overflow valve, a bidirectional hydraulic control one-way valve and a left-right pressure sensor, the left-right rotating oil cylinder module is a double-acting oil cylinder, and the left-right pressure sensor is used for feeding back the real-time clamping force; the left and right clamping cylinder modules are used for opening or holding the front landing gear tires of the aircraft, the left and right clamping cylinder modules are double-acting cylinders, the left and right clamping cylinder modules further comprise one-way hydraulic control one-way valves, plug-in proportional overflow valves, left and right linear displacement sensors and left and right pressure sensors, the one-way hydraulic control one-way valves are used for pressure maintaining and locking, and the left and right linear displacement sensors are used for measuring the sizes of the front landing gear tires; the left and right compression oil cylinder modules are used for compressing or unlocking the front landing gear tires of the aircraft and are single-acting oil cylinders of rear springs, and the left and right compression oil cylinder modules also comprise one-way hydraulic control one-way valves and plug-in type proportional overflow valves; the bidirectional hydraulic control one-way valve and the unidirectional hydraulic control one-way valve are both arranged in a rod cavity of the oil cylinder.
The hydraulic system in the embodiment uses liquid as a medium, the pressure generated by the hydraulic system is used for transmitting energy, an automatic oil source loop module supplies energy through a chassis, a chassis gear pump is used for converting mechanical energy into hydraulic energy, an execution cylinder is used for converting hydraulic energy into mechanical energy, in the process of converting hydraulic energy into mechanical energy, an electromagnetic reversing valve is used for realizing the adjustment of the action and the direction of the execution cylinder, an electromagnetic reversing valve and a proportional overflow valve are used for realizing the adjustment of the movement speed, the control of the force and the position control of a throttle valve, a hydraulic control one-way valve is used for realizing the position maintenance of a hydraulic cylinder, so that the stable output and the position maintenance of a front landing gear of an airplane are realized, therefore, the stability of the movement of the aircraft is improved, the riding comfort is improved, the semi-automatic/manual loop module is used for degrading the use function when the automatic oil source loop module fails, the release of the front landing gear tyre of the aircraft is ensured, the aircraft can move, the normal movement of the aircraft is ensured, the whole hydraulic system is detected through the operation detection system, the fault is determined through the fault feedback system and then fed back to the hydraulic system, the fault defect is known by the hydraulic system, and the hydraulic system is used for providing support for the optimization of the hydraulic system, so that the hydraulic system is continuously perfected.
The above-described embodiment is only one preferred embodiment of the present invention, and many alternative modifications and combinations of the above-described embodiments can be made by those skilled in the art based on the technical solutions of the present invention and the related teachings of the above-described embodiments.
Claims (2)
1. The utility model provides a wheel embracing mechanism hydraulic system, includes hydraulic system, operation monitoring system and fault feedback system, its characterized in that: the output end of the operation monitoring system is respectively connected with the input ends of the hydraulic system and the fault feedback system, the hydraulic system comprises an automatic oil source loop module, a semi-automatic/manual loop module, a clamping lifting hydraulic valve group module, a connecting pipeline module, a control box and a cable module, and the output ends of the semi-automatic/manual loop module and the clamping lifting hydraulic valve group module are respectively connected with a left lifting oil cylinder module, a right lifting oil cylinder module, a left rotating oil cylinder module, a right clamping oil cylinder module and a left pressing oil cylinder module;
The operation monitoring system is used for monitoring the operation condition of the hydraulic system and transmitting an abnormal fault part to the fault feedback system, the fault feedback system is used for receiving fault information and judging whether the information is faulty or not, and if the information is correct fault information, the fault information is uploaded to the hydraulic system;
The connecting pipeline module is used for connecting pipelines among the modules, and the control box and the cable module are used for controlling the operation of the hydraulic system and backing up and storing fault information;
The automatic oil source loop module is used for providing hydraulic oil with required pressure and flow for each module in the hydraulic system and realizing stable output of the pressure oil of the hydraulic system and accurate control of pressure and displacement;
The hydraulic oil treatment comprises precise filtration, hydraulic preheating, oil return cooling, monitoring of the liquid level and the temperature of an oil tank and alarming, and the maximum pressure of the hydraulic system is as follows: pmax=21.0 MPa, hydraulic system maximum flow: qmax=50.00l/min, hydraulic oil temperature: +30 to +70 ℃;
the semi-automatic/manual loop module is started to be used when the automatic oil source loop module fails to work, is used for degrading the using function, loosening the front landing gear tyre of the aircraft, and is used for descending the left lifting oil cylinder and the right lifting oil cylinder, loosening and extending the clamping oil cylinder, opening the rotating oil cylinder and unlocking the compacting oil cylinder;
The clamping lifting hydraulic valve group module is used for lifting or descending, clamping or loosening, opening or holding tightly or unlocking the front landing gear tyre of the aircraft;
The left lifting oil cylinder module and the right lifting oil cylinder module comprise plug-in type proportional overflow valves and pressure sensors, wherein the plug-in type proportional overflow valves are used for setting pressure for the oil cylinders, the pressure sensors are used for feeding back the pressure, and the left lifting oil cylinder module and the right lifting oil cylinder module are used for lifting or descending the front landing gear tires of the aircraft and are single-acting oil cylinders;
The left and right rotating oil cylinder module is used for clamping or loosening the front landing gear tyre of the aircraft and comprises a plug-in type proportional overflow valve, a bidirectional hydraulic control one-way valve and a left and right pressure sensor, the left and right rotating oil cylinder module is a double-acting oil cylinder, and the left and right pressure sensor is used for feeding back the real-time clamping force;
The left and right clamping cylinder modules are used for opening or holding the front landing gear tires of the aircraft, the left and right clamping cylinder modules are double-acting cylinders, the left and right clamping cylinder modules further comprise unidirectional hydraulic control one-way valves, plug-in type proportional overflow valves, left and right linear displacement sensors and left and right pressure sensors, the unidirectional hydraulic control one-way valves are used for pressure maintaining and locking, and the left and right linear displacement sensors are used for measuring the sizes of the front landing gear tires;
The left and right compaction oil cylinder modules are used for compacting or unlocking the front landing gear tires of the aircraft and are single-acting oil cylinders of rear springs, and the left and right compaction oil cylinder modules further comprise unidirectional hydraulic control one-way valves and plug-in type proportional overflow valves.
2. The wheel holding mechanism hydraulic system of claim 1, wherein the two-way pilot operated check valve and the one-way pilot operated check valve are both mounted inside a rod cavity of the cylinder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210623705.3A CN114810697B (en) | 2022-06-02 | 2022-06-02 | Wheel holding mechanism hydraulic system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210623705.3A CN114810697B (en) | 2022-06-02 | 2022-06-02 | Wheel holding mechanism hydraulic system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114810697A CN114810697A (en) | 2022-07-29 |
| CN114810697B true CN114810697B (en) | 2024-05-14 |
Family
ID=82520207
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210623705.3A Active CN114810697B (en) | 2022-06-02 | 2022-06-02 | Wheel holding mechanism hydraulic system |
Country Status (1)
| Country | Link |
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| CN (1) | CN114810697B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105377696A (en) * | 2013-06-14 | 2016-03-02 | 庞巴迪公司 | Apparatus and method for controlling landing gear |
| CN205327437U (en) * | 2015-12-30 | 2016-06-22 | 提坦科技（上海）有限公司 | Embrace automatic deviation control system of wheel |
| CN105782148A (en) * | 2016-04-01 | 2016-07-20 | 哈尔滨飞机工业集团有限责任公司 | Undercarriage rising and landing control hydraulic device for helicopter |
| CN112339995A (en) * | 2020-10-29 | 2021-02-09 | 中电科芜湖通用航空产业技术研究院有限公司 | Hydraulic retractable landing gear mechanism |
| CN112733277A (en) * | 2021-03-30 | 2021-04-30 | 江苏普旭科技股份有限公司 | Simulation method and system for simulation of aircraft landing gear |
| CN113791621A (en) * | 2021-09-15 | 2021-12-14 | 北京航空航天大学 | Method and system for docking automatic driving tractor and airplane |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6448403B2 (en) * | 2015-02-17 | 2019-01-09 | 住友精密工業株式会社 | Electric hydraulic actuator system for lifting and lowering aircraft legs |
-
2022
- 2022-06-02 CN CN202210623705.3A patent/CN114810697B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105377696A (en) * | 2013-06-14 | 2016-03-02 | 庞巴迪公司 | Apparatus and method for controlling landing gear |
| CN205327437U (en) * | 2015-12-30 | 2016-06-22 | 提坦科技（上海）有限公司 | Embrace automatic deviation control system of wheel |
| CN105782148A (en) * | 2016-04-01 | 2016-07-20 | 哈尔滨飞机工业集团有限责任公司 | Undercarriage rising and landing control hydraulic device for helicopter |
| CN112339995A (en) * | 2020-10-29 | 2021-02-09 | 中电科芜湖通用航空产业技术研究院有限公司 | Hydraulic retractable landing gear mechanism |
| CN112733277A (en) * | 2021-03-30 | 2021-04-30 | 江苏普旭科技股份有限公司 | Simulation method and system for simulation of aircraft landing gear |
| CN113791621A (en) * | 2021-09-15 | 2021-12-14 | 北京航空航天大学 | Method and system for docking automatic driving tractor and airplane |
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| Publication number | Publication date |
|---|---|
| CN114810697A (en) | 2022-07-29 |
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