阅读说明：本技术 基于大型飞机起落架的电动收放控制系统 (Electric retraction control system based on large aircraft landing gear ) 是由 冯宇 何晓刚 郭雁 于 2019-10-30 设计创作，主要内容包括：本发明公开一种基于大型飞机起落架的电动收放控制系统,该系统包括试验设备以及起落架机构,起落架机构上安装有若干个位置传感器,试验设备包括柜体,柜体上设置有控制面板,柜体内设置有电气控制系统以及液压系统,电气控制系统分别接收来自控制面板的收放控制信号、控制开关信号以及起落架机构位置传感器的位置信号,并将收放控制信号、控制开关信号、位置信号经过信号处理后发送电磁阀驱动信号至液压系统,由液压系统驱动起落架机构以控制其收放操作。本发明移动性好,使用维护方便,可以实现飞机复杂起落架收放系统逻辑,能够满足模拟大型飞机在地面进行飞机起落架的装配调试工作。(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.)

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 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.

2. The electric retraction control system according to claim 1, wherein:

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 the retraction control signals and the control switch signals sent by the control panel and outputs electromagnetic valve driving signals to the hydraulic system.

3. The electric retraction control system according to claim 1, wherein:

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.

4. The electric retraction control system according to claim 3, 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 sublock 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 sublock actuator cylinders.

5. The electric retraction control system according to claim 4, wherein:

the pipeline of the main lifting/retracting 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 up upper lock actuating cylinder.

6. The electric retraction control system according to claim 5, 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.

7. The electric retraction control system according to claim 3, wherein:

the nose landing gear retraction unit comprises a nose landing gear retraction electromagnetic valve, and a nose lifting lower lock actuator cylinder, a nose lifting upper lock actuator cylinder, two-position two-way electromagnetic valves, two one-way throttle valves, a two-way hydraulic lock and a nose lifting retraction actuator cylinder are sequentially arranged on a pipeline of the nose landing gear retraction electromagnetic valve.

8. The electric retraction control system according to claim 7, 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.

9. The electric retraction control system according to claim 3, wherein:

the front landing gear cabin door retraction unit comprises a front landing gear cabin door retraction 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 retraction actuator cylinders are sequentially arranged on a pipeline of the front landing gear cabin door retraction electromagnetic valve.

10. The electric retraction control system according to claim 9, 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.

[ 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 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 in 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 aircraft landing gear, which has good mobility and convenient use and maintenance and can realize the logic of a complicated 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 up upper lock actuating cylinder.

According to a further scheme, 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.

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 actuating cylinder is also provided with a two-position two-way electromagnetic valve, and the pipeline at the front upper lock actuating cylinder is also provided with a two-position two-way electromagnetic valve.

According to a further scheme, 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 of the landing gear of the large aircraft according to the present invention.

[ detailed description ] embodiments

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further 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. The cabinet body of the test equipment of the embodiment can be improved on the basis of an integrated industrial personal 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, processes the retraction control signal, the control switch signal and the position signal, and sends the electromagnetic valve driving signal to the hydraulic system 58, 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 master control switch and instrument display 562, a nose 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 principles on the test system are consistent with those of the airplane, and the maintainability and the economical efficiency of test equipment are considered. 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 (programmable logic controller) 55 to replace an airplane retraction control system to control the retraction process, and the PLC 55 receives a retraction control handle signal, a process control switch signal and a position signal, processes the signals and sends electromagnetic valve driving signals to each electromagnetic valve of the hydraulic system 58 to complete the functions of retraction control, indication, alarm and the like of the undercarriage.

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: a) the landing gear retraction operation, b) the landing gear lowering operation, and c) in the automatic control mode, the landing gear can be manually intervened to stop at any position in the landing gear retraction process.

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 this embodiment is mainly used for simulating the aircraft hydraulic system 58 to complete the retraction control and any spatial movement point locking functions of the landing gear and the cabin door.

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); the main starting up lock cylinder 4 is also provided with a two-position two-way electromagnetic valve 26 on the pipeline.

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 arranged on a pipeline at the position of the front lifting lower lock actuating cylinder 8, and a two-position two-way electromagnetic valve 31 is arranged at the position of the front lifting upper lock actuating 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 landing gear can be retracted or not is judged through PDCU logical operation, when the condition is met, a rated voltage is supplied to a landing gear retracting electromagnetic valve to control the landing gear retracting electromagnetic valve to reverse, hydraulic oil can enter a hydraulic system 58 through a landing gear retracting pipeline, the hydraulic oil firstly flows through a landing gear down lock to unlock the down lock, after the down lock is unlocked, a landing gear retracting actuator cylinder contracts to control the landing gear to retract, after the landing gear retracts to the right position, an landing gear up lock automatically locks and transmits a locking signal to a retracting control unit PDCU through an up lock near position sensor, after the retracting control unit PDCU receives the locking signals of all the up lock sensors, the signal is displayed on a control panel 56, a user cuts off the voltage of the landing gear retracting electromagnetic valve through the control panel 56, and the landing gear electromagnetic valve retracts to the neutral position, the pressure of the hydraulic system 58 is shut 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 this embodiment carries out the undercarriage test to the nose landing gear of aircraft, at first, confirm the test object, pull test equipment to suitable position, through the mark on the cable head, connect corresponding each sensor test cable and other connecting cables, connect each oil circuit pipeline of equipment with oil pipe, the hydraulic fluid port that does not use is blocked up with the end cap.

Then, confirming that all switches of the control panel 56 on the console are placed in the corresponding initial positions, the "AC 220V" power cord is used to connect the AC220V power source with the "AC 220V" power outlet on the left side of the test rig. The "mains" switch is turned on and the power lamp is lit, "DC 28V" voltmeter shows 28V, and "DC 24V" indicator light is lit. 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 any insubstantial modifications made by using the design concept also fall within the protection scope of the present invention.