CN110626493B - Electric retraction control system based on large aircraft landing gear - Google Patents
Electric retraction control system based on large aircraft landing gear Download PDFInfo
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- CN110626493B CN110626493B CN201911045396.0A CN201911045396A CN110626493B CN 110626493 B CN110626493 B CN 110626493B CN 201911045396 A CN201911045396 A CN 201911045396A CN 110626493 B CN110626493 B CN 110626493B
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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
- B64C25/24—Operating mechanisms electric
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Abstract
The invention discloses an electric retraction control system based on a large aircraft undercarriage, which comprises a test device and an undercarriage mechanism, wherein a plurality of position sensors are arranged on the undercarriage mechanism, the test device comprises a cabinet body, a control panel is arranged on the cabinet body, an electric control system and a hydraulic system are arranged in the cabinet body, the electric control system respectively receives a retraction control signal, a control switch signal and a position signal of the undercarriage mechanism position sensor from the control panel, sends an electromagnetic valve driving signal to the hydraulic system after the retraction control signal, the control switch signal and the position signal are subjected to signal processing, and drives the undercarriage mechanism by the hydraulic system to control the retraction operation of the undercarriage mechanism. The invention has good mobility and convenient use and maintenance, can realize the logic of a complex undercarriage retraction system of the airplane, and can meet the requirement of simulating a large airplane to carry out the assembly and debugging work of the undercarriage of the airplane on the ground.
Description
[ technical field ] A method for producing a semiconductor device
The invention relates to the technical field of aircraft assembly and debugging, in particular to an electric retraction control system based on a large aircraft landing gear.
[ background of the invention ]
In the structural design of the undercarriage control system of the traditional airplane, the undercarriage control system is normally configured to normally retract and emergently release, the normal control is mechanical or electrical single redundancy, the failure rate is high, the undercarriage is emergently released by adopting cold air, and once the undercarriage cannot be emergently released, a pilot cannot normally retract the undercarriage.
In addition, the landing gear of the large amphibious aircraft has the characteristics of heavy weight, large structural size, high installation precision, more adjustment technical requirements, complex retraction and extension system principle and functions and the like, so that the technical difficulties of large workload, long time period, high technical difficulty and the like exist during the on-machine installation and debugging of the landing gear, and the assembly and debugging work of the landing gear becomes an important link in the assembly technology of the large aircraft.
[ summary of the invention ]
The invention mainly aims to provide an electric retraction control system based on a large-scale aircraft landing gear, which has good mobility and convenient use and maintenance and can realize the logic of a complex landing gear retraction system of the aircraft.
In order to achieve the main purpose, the electric retraction control system based on the large aircraft landing gear comprises a test device and a landing gear mechanism, wherein a plurality of position sensors are mounted on the landing gear mechanism; the electric control system respectively receives a retraction control signal, a control switch signal and a position signal of a position sensor of the undercarriage mechanism from the control panel, the retraction control signal, the control switch signal and the position signal are processed and then sent to the hydraulic system, the hydraulic system drives the undercarriage mechanism to control retraction operation of the undercarriage mechanism, and the control panel comprises an integrated industrial personal computer liquid crystal display, a master control switch and instrument display, a nose undercarriage control and a main undercarriage control.
The electric control system comprises a first retraction control unit, a second retraction control unit and a PLC (programmable logic controller), wherein the first retraction control unit and the second retraction control unit respectively collect position signals of all position sensors on the landing gear mechanism and display the position signal information on the control panel, and the PLC receives the retraction control signals and the control switch signals sent by the control panel and outputs electromagnetic valve driving signals to the hydraulic system.
According to a further scheme, the hydraulic system comprises a hydraulic source, an oil outlet pipe of the hydraulic source is connected with a manual pump, a first oil filter, a pressure sensor and a flow sensor, and an oil outlet of the manual pump is respectively provided with a main undercarriage retraction control unit, a nose undercarriage retraction unit and a nose undercarriage cabin door retraction unit.
According to a further scheme, the main undercarriage retraction control unit comprises a main undercarriage retraction electromagnetic valve, a main lifting uplock actuator cylinder, two main lifting downshifts, a main lifting retraction actuator cylinder and two-position two-way electromagnetic valves are arranged on a pipeline of the main undercarriage retraction electromagnetic valve, the main lifting uplock actuator cylinder is connected with the main lifting retraction actuator cylinder, and the two-position two-way electromagnetic valves are respectively connected with the two main lifting downshifts.
The pipeline of the main lifting/releasing actuator cylinder is sequentially provided with a bidirectional hydraulic lock, two one-way throttle valves and two-position two-way electromagnetic valves; and a two-position two-way electromagnetic valve is also arranged on the pipeline of the main starting upper lock actuating cylinder.
The main undercarriage control unit comprises a main undercarriage control unit, a main undercarriage control unit and a main timing electromagnetic valve, wherein the main undercarriage control unit comprises a main timing electromagnetic valve and a main timing electromagnetic valve.
According to a further scheme, the nose landing gear retracting unit comprises a nose landing gear retracting electromagnetic valve, and a front lifting lower lock actuator cylinder, a front lifting upper lock actuator cylinder, two-position two-way electromagnetic valves, two one-way throttle valves, a two-way hydraulic lock and a front lifting retracting actuator cylinder are sequentially arranged on a pipeline of the nose landing gear retracting electromagnetic valve.
The pipeline at the front lower lock actuator cylinder is also provided with a two-position two-way electromagnetic valve, and the pipeline at the front upper lock actuator cylinder is also provided with a two-position two-way electromagnetic valve.
The front landing gear cabin door folding and unfolding unit comprises a front landing gear cabin door folding and unfolding electromagnetic valve, and a front lifting cabin door uplock actuator cylinder, two-position two-way electromagnetic valves, four one-way throttle valves and two front lifting cabin door folding and unfolding actuator cylinders are sequentially arranged on a pipeline of the front landing gear cabin door folding and unfolding electromagnetic valve.
In a further scheme, a two-position two-way electromagnetic valve is further arranged on a pipeline of the forecabin door upper lock actuating cylinder.
Therefore, the electric retraction control system provided by the invention can meet the requirements that after the nose landing gear and the main landing gear of the large amphibious aircraft are installed on the airframe structure, the single landing gear and the door of the nose landing gear are retracted and extended so as to check the movement condition and the locking condition of the landing gear.
Meanwhile, the test equipment can realize manual and automatic retraction drive control of a single undercarriage, can realize locking of any point in the retraction process of the undercarriage, can detect and display the state of a sensor of an undercarriage system, and can ensure that the logic of the operation of the automatic retraction process simulates an undercarriage system on an airplane so as to keep consistent with the logic of the retraction control of the airplane.
[ description of the drawings ]
FIG. 1 is a schematic structural diagram of an embodiment of an electric retraction control system based on a large aircraft landing gear.
FIG. 2 is a schematic diagram of an embodiment of the electric retraction control system based on a large aircraft landing gear.
FIG. 3 is a schematic diagram of a hydraulic system in an embodiment of the electric retraction control system for a large aircraft landing gear according to the present invention.
[ detailed description ] A
In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention.
Referring to fig. 1 to 3, the electric retraction control system based on the landing gear of the large aircraft, which is applied to the large amphibious aircraft, comprises a test device and a landing gear mechanism, wherein a plurality of position sensors 50 are mounted on the landing gear mechanism, the test device comprises a cabinet body 80, a control panel 56 is arranged on the cabinet body 80, an electric control system and a hydraulic system 58 are arranged in the cabinet body, the electric control system is connected with each position sensor 50 of the landing gear mechanism through a signal line, and the hydraulic system 58 is connected with the landing gear mechanism through a landing gear hydraulic interface. Wherein, the cabinet body of the test equipment of this embodiment can be improved on the basis of integration industrial computer.
In this embodiment, the electrical control system receives the retraction control signal, the control switch signal and the position signal of the landing gear mechanism position sensor 50 from the control panel 56, respectively, and sends the electromagnetic valve driving signal to the hydraulic system 58 after the retraction control signal, the control switch signal and the position signal are processed, and the hydraulic system 58 drives the landing gear mechanism to control the retraction operation, wherein the control panel 56 includes an integrated industrial personal computer liquid crystal display 561, a main control switch and instrument display 562, a front landing gear control 563 and a main landing gear control 564.
Specifically, the test equipment of this embodiment adopts machine, electricity, liquid integrated design, integrates hydraulic system and electrical control system in a portable rack, and the wheel adopts solid rubber tire. According to the system function division, the panel is divided into four parts: an integrated industrial personal computer liquid crystal display 561, a master control switch and instrument display 562, a nose landing gear control 563 and a main landing gear control 564. The hydraulic and electric control principle of the test system is consistent with that of the airplane, and the maintainability and the economical efficiency of the test equipment are considered at the same time. Meanwhile, the test equipment is provided with a sensor signal input interface and an undercarriage hydraulic interface which are analyzed by an undercarriage retraction control unit PDCU on the test equipment, a control panel 56 is integrated on a front panel of the test equipment, the sensor signal is displayed through an integrated industrial personal computer and a programmable logic controller PLC, the retraction process is controlled, the undercarriage can be automatically retracted and retracted for inspection, the undercarriage can be manually retracted and retracted for inspection, and the undercarriage can be suspended at any position of the retraction track of the undercarriage.
In this embodiment, the electrical control system includes a power supply 53, a first retraction control unit 51, a second retraction control unit 52, and a PLC controller 55, where the first retraction control unit 51 and the second retraction control unit 52 respectively collect position signals of each position sensor 50 on the landing gear mechanism, and display the position signal information on a control panel 56, and the PLC controller 55 receives the retraction control signal and the control switch signal sent by the control panel 56, and outputs an electromagnetic valve driving signal to the hydraulic system 58. The first retraction control unit 51 and the second retraction control unit 52 are both retraction control units PDCUs.
The electrical control system mainly inputs control instructions and sensor signals to the PLC 55, the PLC 55 outputs and controls each electromagnetic valve in the hydraulic system 58 through the undercarriage retraction logic principle, logically controls the retraction of the undercarriage and the cabin door and the state display of the sensor, and prevents the jumping operation or the misoperation through the logic control of the PLC 55.
Therefore, the electric control system mainly comprises a power supply 53, a PLC 55, a retraction control unit and the like, and the test equipment is realized by adopting two modes of a control panel 56 and an integrated industrial personal computer and can independently perform operation and signal display. The electrical control system mainly adopts a PLC 55 to replace an airplane retraction control system to control the retraction process, the PLC 55 receives a retraction control handle signal, a process control switch signal and a position signal, and sends an electromagnetic valve driving signal to each electromagnetic valve of the hydraulic system 58 after signal processing, so that the functions of retraction control, indication, alarm and the like of the undercarriage are completed.
In practical application, the landing gear is controlled in two ways: automatic control and manual control. The control mode is selected and switched on the control panel 56.
For example, in an automatic control mode, the solenoid valve can be controlled by the PLC controller 55 to coordinate the unlocking and locking sequence of the uplock and the sublock and the retraction sequence of the retraction actuator. In the adjustment process of the landing gear and the cabin door, the electromagnetic valve is controlled to be powered off through the operation interface, the landing gear stays at any position of the retraction track of the landing gear, and the landing gear can be finely adjusted by matching with the manual pump 101 of the hydraulic system 58.
Wherein the automatic control comprises three operations: the landing gear retraction operation method comprises the following steps of a) landing gear retraction operation, b) landing gear lowering operation and c) under an automatic control mode, the landing gear can be manually intervened in the landing gear retraction process, and the landing gear can be stopped at any position.
If the landing gear is in a manual control mode, the on/off of the electromagnetic valves for releasing and releasing the landing gears can be manually controlled, and the actions of unlocking, releasing, locking and the like are realized. The independent pressure supply and disconnection of each branch (an upper lock path, a lower lock path, a retraction action cylinder path and the like) of the undercarriage can be realized. During the retraction of the landing gear, manual intervention is possible, the landing gear is stopped at any position, and fine adjustment of the landing gear can be achieved by means of the manual pump 101 of the hydraulic system 58.
The integrated industrial personal computer can display the states of the undercarriage position sensor and the pressure and flow sensors and check the signal change process in the retraction and release processes. The electric control system adopts an integrated industrial personal computer as an input and output interface of the system and the installation of a secondary instrument, so that the system interface is concise, the display information is rich and clear, and the test operation and the system state monitoring are convenient.
Meanwhile, a digital instrument is arranged on the panel of the equipment to display pressure and flow, and an indicator light displays the signal state of each sensor.
In this embodiment, the hydraulic system 58 includes a hydraulic source 100, an oil outlet pipe of the hydraulic source 100 is connected with a manual pump 101, a first oil filter 46, an accumulator 45, a pressure sensor 43, a flow sensor 44, and a check valve 42, and an oil outlet of the manual pump 101 is respectively provided with a main landing gear retraction control unit, a nose landing gear retraction unit, and a nose landing gear door retraction unit. The hydraulic system 58 in the embodiment is mainly used for simulating the aircraft hydraulic system 58 to complete the retraction control of the landing gear and the cabin door and the locking function of any point of spatial movement.
The main landing gear retraction control unit comprises a main landing gear retraction electromagnetic valve 1, a main lifting uplock actuator cylinder 4, two main lifting sublock actuator cylinders (such as a main lifting sublock actuator cylinder 15 and a main lifting sublock actuator cylinder 16), a main lifting retraction actuator cylinder 12 and two-position two-way electromagnetic valves (such as a two-position two-way electromagnetic valve 29 and a two-position two-way electromagnetic valve 30) are arranged on a pipeline of the main landing gear retraction electromagnetic valve 1, the main lifting uplock actuator cylinder 4 is connected with the main lifting retraction actuator cylinder 12, and the two-position two-way electromagnetic valves are respectively connected with the two main lifting sublock actuator cylinders.
The pipeline of the main lifting/releasing actuating cylinder 12 is also provided with a bidirectional hydraulic lock 38, two one-way throttle valves (such as the one-way throttle valve 10 and the one-way throttle valve 11) and two-position two-way electromagnetic valves (such as the two-position two-way electromagnetic valve 27 and the two-position two-way electromagnetic valve 28); a two-position two-way electromagnetic valve 26 is also arranged on the pipeline of the main starting upper lock actuating cylinder 4.
The main undercarriage retraction control unit further comprises two main timing solenoid valves (such as a main timing solenoid valve 5 and a main timing solenoid valve 6), and the two main timing solenoid valves are respectively connected with the main undercarriage retraction solenoid valve 1.
The nose landing gear retraction unit comprises a nose landing gear retraction electromagnetic valve 2, and a nose lifting lower lock actuator cylinder 8, a nose lifting upper lock actuator cylinder 7, two-position two-way electromagnetic valves (such as a two-position two-way electromagnetic valve 33 and a two-position two-way electromagnetic valve 34), two one-way throttle valves (such as a one-way throttle valve 17 and a one-way throttle valve 18), a two-way hydraulic lock 39 and a nose lifting retraction actuator cylinder 19 are sequentially arranged on a pipeline of the nose landing gear retraction electromagnetic valve 2.
A two-position two-way electromagnetic valve 32 is further arranged on a pipeline at the position of the front lifting lower lock actuator cylinder 8, and a two-position two-way electromagnetic valve 31 is further arranged at the position of the front lifting upper lock actuator cylinder 7.
The nose landing gear door retraction unit comprises a nose landing gear door retraction electromagnetic valve 3, and a front takeoff door uplock actuator cylinder 9, two-position two-way electromagnetic valves (such as a two-position two-way electromagnetic valve 36 and a two-position two-way electromagnetic valve 37), four one-way throttle valves (such as a one-way throttle valve 20, a one-way throttle valve 21, a one-way throttle valve 22 and a one-way throttle valve 23) and two front takeoff door retraction actuator cylinders (such as a front takeoff door retraction actuator cylinder 24 and a front takeoff door retraction actuator cylinder 25) are sequentially arranged on a pipeline of the nose landing gear door retraction electromagnetic valve 3. Wherein, the pipeline of the fore-hoisting cabin door upper lock actuating cylinder 9 is also provided with a two-position two-way electromagnetic valve 35.
Specifically, whether the undercarriage can be retracted or not is judged through PDCU logical operation, when the condition is met, a rated voltage is supplied to an undercarriage retraction electromagnetic valve at first, the undercarriage retraction electromagnetic valve is controlled to be reversed, hydraulic oil can enter a hydraulic system 58 through an undercarriage retraction pipeline, the hydraulic oil firstly flows through an undercarriage down lock, the down lock is opened, after the down lock is opened, an undercarriage retraction actuator cylinder is contracted, the undercarriage is controlled to be retracted, after the undercarriage is retracted in place, an undercarriage uplock is automatically locked, a locking signal is transmitted to a retraction control unit PDCU through an uplock approaching position sensor, after the retraction control unit PDCU receives the locking signals of all uplock sensors, the signal is displayed on a control panel 56, a user cuts off the undercarriage retraction electromagnetic valve voltage through the control panel 56, the undercarriage electromagnetic valve is retracted to a neutral position, and the pressure of the hydraulic system 58 is cut off; and meanwhile, supplying a rated voltage to the undercarriage cabin door retraction electromagnetic valve, controlling the cabin door retraction electromagnetic valve to change direction, enabling hydraulic oil to enter the cabin door retraction system, retracting the undercarriage cabin door retraction actuator cylinder to close the undercarriage cabin door, cutting off the voltage of the undercarriage cabin door retraction electromagnetic valve when the undercarriage cabin door closing sensor receives a closing signal, enabling the undercarriage retraction electromagnetic valve to return to a neutral position, and completing the whole undercarriage retraction process. The normal landing gear lowering process is also similar to the landing gear retraction and extension process.
When the test equipment of the embodiment is used for carrying out the undercarriage test on the nose landing gear of an airplane, firstly, a test object is determined, the test equipment is pulled to a proper position, corresponding sensor test cables and other connecting cables are connected through marks on a cable head, oil pipelines of the equipment are connected through oil pipes, and oil ports which are not used are plugged through plugs.
Then, confirming that all switches of the control panel 56 on the console are placed in the corresponding initial positions, the "AC220V" power cord is used to connect the AC220V power source to the "AC220V" power outlet on the left side of the test rig. The 'main power supply' switch is switched on, the power lamp is lightened, the 'DC 28V' voltmeter displays 28V, and the 'DC 24V' indicator lamp is lightened. And (4) the pressure meter and the flow meter are normally powered, the power switch is turned on, the test equipment is started, and the test software is operated.
The lower part of the left side of a control panel of the test equipment is provided with 17 oil way port connectors, the test equipment is connected with all the actuating cylinders through aviation conical surface connectors HB474 degrees and is divided into two areas, one area is used for connecting all the actuating cylinders of a front landing gear, and the other area is used for connecting all the actuating cylinders of a left (right) main landing gear.
The lower part of the right side of the control panel of the test equipment is provided with 2 oil way port connectors for oil inlet and oil return of the test equipment, and the test equipment is connected with the hydraulic system 58 through YXF-137 and YXF-138.
Therefore, the electric retraction control system provided by the invention can meet the requirements that after the nose landing gear and the main landing gear of the large amphibious aircraft are installed on the airframe structure, the single landing gear and the door of the nose landing gear are retracted and extended so as to check the movement condition and the locking condition of the landing gear.
Meanwhile, the test equipment can realize manual and automatic retraction drive control of a single undercarriage, can realize locking of any point in the retraction process of the undercarriage, can detect and display the state of a sensor of an undercarriage system, and can ensure that the logic of the operation of the automatic retraction process simulates an undercarriage system on an airplane so as to keep consistent with the logic of the retraction control of the airplane.
It should be noted that the above is only a preferred embodiment of the present invention, but the design concept of the present invention is not limited thereto, and insubstantial modifications of the present invention using the design concept also fall within the protection scope of the present invention.
Claims (8)
1. Electronic control system that receive and releases based on large-scale aircraft undercarriage, including test equipment and undercarriage mechanism, install a plurality of position sensor in the undercarriage mechanism, test equipment includes the cabinet body, be provided with control panel, its characterized in that on the cabinet body:
an electrical control system and a hydraulic system are arranged in the cabinet body, the electrical control system is connected with each position sensor of the undercarriage mechanism through a signal line, and the hydraulic system is connected with the undercarriage mechanism through an undercarriage hydraulic interface;
the electric control system receives a retraction control signal, a control switch signal and a position signal of a position sensor of the undercarriage mechanism from the control panel respectively, the retraction control signal, the control switch signal and the position signal are processed and then sent to the hydraulic system, and the hydraulic system drives the undercarriage mechanism to control the retraction operation of the undercarriage mechanism, wherein the control panel comprises an integrated industrial personal computer liquid crystal display, a master control switch and instrument display, a nose undercarriage control and a main undercarriage control;
the electric control system comprises a first retraction control unit, a second retraction control unit and a PLC (programmable logic controller), wherein the first retraction control unit and the second retraction control unit respectively collect position signals of all position sensors on the landing gear mechanism and display position signal information on the control panel, and the PLC receives retraction control signals and control switch signals sent by the control panel and outputs electromagnetic valve driving signals to the hydraulic system;
the hydraulic system comprises a hydraulic source, an oil outlet pipe of the hydraulic source is connected with a manual pump, a first oil filter, a pressure sensor and a flow sensor, and a main undercarriage retraction control unit, a nose undercarriage retraction unit and a nose undercarriage cabin door retraction unit are respectively installed at an oil outlet of the manual pump.
2. The electric retraction control system according to claim 1, wherein:
the main landing gear retraction control unit comprises a main landing gear retraction electromagnetic valve, a main lifting uplock actuator cylinder, two main lifting downshift lock actuator cylinders, a main lifting retraction actuator cylinder and two-position two-way electromagnetic valves are arranged on a pipeline of the main landing gear retraction electromagnetic valve, the main lifting uplock actuator cylinder is connected with the main lifting retraction actuator cylinder, and the two-position two-way electromagnetic valves are respectively connected with the two main lifting downshift lock actuator cylinders.
3. The electric retraction control system according to claim 2, wherein:
the pipeline of the main hoisting retractable actuating cylinder is sequentially provided with a bidirectional hydraulic lock, two one-way throttle valves and two-position two-way electromagnetic valves;
and a two-position two-way electromagnetic valve is also arranged on the pipeline of the main starting up upper lock actuating cylinder.
4. The electric retraction control system according to claim 3, wherein:
the main undercarriage retraction control unit further comprises two main timing electromagnetic valves, and the two main timing electromagnetic valves are respectively connected with the main undercarriage retraction electromagnetic valves.
5. The electric retraction control system according to claim 1, wherein:
the front landing gear retractable unit comprises a front landing gear retractable electromagnetic valve, and a front lifting lower lock actuator cylinder, a front lifting upper lock actuator cylinder, two-position two-way electromagnetic valves, two one-way throttle valves, a two-way hydraulic lock and a front lifting retractable actuator cylinder are sequentially arranged on a pipeline of the front landing gear retractable electromagnetic valve.
6. The electric retraction control system according to claim 5, wherein:
the pipeline of the front lower lock actuating cylinder is also provided with a two-position two-way electromagnetic valve, and the pipeline of the front upper lock actuating cylinder is also provided with a two-position two-way electromagnetic valve.
7. The electric retraction control system according to claim 1, wherein:
the front landing gear cabin door folding and unfolding unit comprises a front landing gear cabin door folding and unfolding electromagnetic valve, and a front lifting cabin door uplock actuator cylinder, two-position two-way electromagnetic valves, four one-way throttle valves and two front lifting cabin door folding and unfolding actuator cylinders are sequentially arranged on a pipeline of the front landing gear cabin door folding and unfolding electromagnetic valve.
8. The electric retraction control system according to claim 7, wherein:
and a two-position two-way electromagnetic valve is also arranged on the pipeline of the fore-lift cabin door upper lock actuating cylinder.
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| CN201911045396.0A CN110626493B (en) | 2019-10-30 | 2019-10-30 | Electric retraction control system based on large aircraft landing gear |
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| CN201911045396.0A CN110626493B (en) | 2019-10-30 | 2019-10-30 | Electric retraction control system based on large aircraft landing gear |
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| CN110626493B true CN110626493B (en) | 2023-04-11 |
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| CN112173085B (en) * | 2020-09-25 | 2023-03-28 | 中国直升机设计研究所 | Hydraulic control system and method for retraction and release of helicopter undercarriage |
| CN113232887B (en) * | 2021-05-19 | 2023-03-14 | 中航西安飞机工业集团股份有限公司 | Mechanical life test bed and test method for retractable switch of undercarriage |
| CN116176832B (en) * | 2023-05-04 | 2023-10-24 | 成都凯天电子股份有限公司 | Method for controlling retraction, extension and extension based on complex undercarriage configuration |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN201220749Y (en) * | 2008-05-28 | 2009-04-15 | 江西洪都航空工业集团有限责任公司 | Hydraulic control system for folding and unfolding undercarriage |
| CN103033380B (en) * | 2012-12-11 | 2015-07-01 | 中国飞机强度研究所 | Landing gear retractable test loading method |
| CN105620732A (en) * | 2014-11-28 | 2016-06-01 | 成都飞机工业（集团）有限责任公司 | Undercarriage extension and retraction system |
| CN105291936A (en) * | 2015-11-23 | 2016-02-03 | 中国航天空气动力技术研究院 | Ground integrated test apparatus for UAV (unmanned aerial vehicle) undercarriages |
| CN106707792B (en) * | 2016-11-18 | 2019-07-19 | 中航飞机起落架有限责任公司 | A kind of comprehensive joint-trial control method of multi-functional undercarriage |
| CN107697273A (en) * | 2017-09-12 | 2018-02-16 | 陕西飞机工业（集团）有限公司 | A kind of control system actively prevented undercarriage and fail to lay down Single Point of Faliure |
| CN208459789U (en) * | 2017-11-06 | 2019-02-01 | 中航通飞华南飞机工业有限公司 | A kind of amphibious aircraft landing gear folding and unfolding ancillary test device of large size |
| US10266253B1 (en) * | 2017-11-10 | 2019-04-23 | The Boeing Company | Methods and apparatus for controlling landing gear shrink |
| CN108757599B (en) * | 2018-04-28 | 2020-04-17 | 北京机械设备研究所 | Hydraulic loading system and loading method for airplane ground test bed |
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