Electro-hydraulic synchronous control jack for airplane

Abstract

The utility model relates to the technical field of related manufacturing of aviation support equipment, in particular to an electric hydraulic synchronous control jack for an airplane, which comprises a tripod, an actuator cylinder component is fixed in the middle of the tripod, the actuator cylinder component stretches out and draws back to realize the jacking and landing of the airplane, and at least three groups of jacks are required to be used for jacking the airplane. One group of jacks are used for jacking the fuselage, the other two groups of jacks are used for jacking the two groups of wings, an electric control box is further mounted on the triangular frame, and in the jacking process, synchronous starting of the pre-jacked actuator cylinder assemblies in the multiple groups of jacks is achieved through a synchronous jacking button arranged on the electric control box. An actuator cylinder assembly in one jack making contact with a machine body can operate at a fixed speed, the actuator cylinder assemblies in the other two jacks keep the height difference before operation, and the speed of the actuator cylinder assemblies is adjusted through a PID control system arranged in an electric control box to follow the jack with the fixed speed.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation support equipment manufacturing, and specifically refers to an aircraft electric-hydraulic synchronous control jack. Background Technique

[0002] The jack can be used for horizontal measurement, weighing, disassembly and assembly, retraction and extension of the landing gear of the aircraft under normal circumstances, and jacking up the aircraft during the correction and adjustment of the installation position of airborne equipment.

[0003] At present, there are various forms of lifting and operating methods for aircraft jacks. One is to reciprocate and shake a manual pump by manpower to realize the lifting and lowering of the jack, and the other is to drive by an electric motor for lifting and lowering. The output of the jacking capacity is through a hydraulic system and a mechanical transmission system.

[0004] Manual jacking is applicable to the jacking operation process of aircraft with smaller tonnage, and the required hydraulic oil volume is not much. However, for large-tonnage large transport aircraft, manual jacking will increase the work intensity and reduce the work efficiency. At the same time, the jack with an electric mechanical transmission method is limited by the lowest jacking height, and many transmission structures are difficult to design and implement, or even if implemented, the volume and size of the jack will be very large and the weight will be very heavy.

[0005] Synchronous control can be achieved by the cooperation of a mechanical wire-pulling sensor and a hydraulic system, or by the cooperation of a laser displacement sensor and a hydraulic system. The mechanical wire-pulling sensor is restricted by space, rope wear, regular inspection and maintenance, and environmental factors, which restricts its application and causes inconvenience in use.

[0006] Based on this, this solution provides an aircraft electric-hydraulic synchronous control jack with high synchronous accuracy, high jacking efficiency, small space volume and light weight of the jack. Content of the Utility Model

[0007] The utility model aims to at least solve the problems of large volume and low work efficiency of the jack in the prior art.

[0008] This solution provides an aircraft electric-hydraulic synchronous control jack, which is achieved by the following specific technical means: including a tripod, the tripod assembly is used to stably and reliably support the weight of the aircraft, and is in the form of a stable tripod. A plurality of groups of walking wheels are installed on the periphery of the tripod, and the walking wheels realize the overall movement and walking; a actuator assembly is fixed in the middle of the tripod, and the actuator assembly performs telescopic actions to realize the jacking and landing of the aircraft. The actuator assembly is a multi-stage hydraulic cylinder. At least three groups of jacks are required for aircraft jacking. One group jacks up the fuselage, and the other two groups jack up the two wings.

[0009] An electric control box is also installed on the tripod, and the electric control box is electrically connected to the actuator assembly. During use, the electric control box is used to control each jack to contact the aircraft body for pre-lifting to complete the preparation before the synchronous lifting operation. During the lifting process, the synchronous lifting button set on the electric control box is used to synchronously start the actuator assemblies that have completed pre-lifting among multiple groups of jacks.

[0010] Preferred Technical Solution 1: A laser displacement sensing assembly is installed on the actuator assembly, and the laser displacement sensing assembly continuously detects the displacement amount of the actuator assembly rising.

[0011] Preferred Technical Solution 2: Multiple groups of leveling hydraulic cylinders are also installed on the periphery of the tripod, and the multiple groups of leveling hydraulic cylinders are used to extend and lift the walking wheels off the ground when parked.

[0012] Preferred Technical Solution 3: A level is installed on the tripod, and the level is used to detect the levelness of the tripod and is used in cooperation with the leveling hydraulic cylinders.

[0013] Preferred Technical Solution 4: A hydraulic oil tank is also installed on the tripod, and the hydraulic oil tank is connected to the leveling hydraulic cylinders and the actuator assembly to supply hydraulic oil to them; at the same time, a hydraulic operation box connected to the hydraulic oil tank is also installed on the tripod, and the flow of hydraulic oil is controlled through the hydraulic operation box. The hydraulic operation box is electrically connected to the electric control box, and the hydraulic operation box is controlled through the electric control box.

[0014] Preferred Technical Solution 5: A support disc is fixed to the bottom telescopic end of the leveling hydraulic cylinder, and the support disc enables the jack to stably engage with the ground.

[0015] Preferred Technical Solution 6: A towing bar is hingedly connected to one side of the tripod, and the towing bar can tow the jack.

[0016] Adopting the above structure enables this solution to have the following beneficial effects:

[0017] 1. The lifting and lowering functions of a large transport aircraft can be realized, driven by an electro-hydraulic system, and at the same time, it has the function of synchronous lifting and lowering;

[0018] 2. High synchronous accuracy, high lifting efficiency, small space volume and light weight of the jack. Description of the Drawings

[0019] The drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation to the present invention. In the drawings:

[0020] Figure 1 is the overall structural schematic diagram of this solution;

[0021] Figure 2 This is the extended state diagram of the actuator assembly of this solution;

[0022] Figure 3 This is the structural schematic diagram of this solution;

[0023] Figure 4 This is the operation flowchart of this solution.

[0024] Among them, 1. Tripod, 2. Actuator assembly, 3. Traveling wheels, 4. Electrical control box, 5. Laser displacement sensing assembly, 51. Reflector, 52. Laser displacement sensor, 6. Leveling hydraulic cylinder, 61. Support plate, 7. Level, 8. Hydraulic oil tank, 9. Hydraulic operation box, 10. Towing bar, 11. Safety nut. Specific implementation manners

[0025] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments; based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.

[0026] Please refer to Figure 1 - Figure 2 , the aircraft electric hydraulic synchronous control jack, including a tripod 1. The tripod assembly is used to stably and reliably support the weight of the aircraft, and is in a stable form of the tripod;

[0027] An actuator assembly 2 is fixed in the middle of the tripod 1. The top of the actuator assembly 2 performs telescopic actions to realize the jacking and landing of the aircraft. The actuator assembly 2 is a multi-stage hydraulic cylinder. At least three groups of jacks are required for aircraft jacking. One group jacks the fuselage, and the other two groups jack the two wings;

[0028] A plurality of groups of traveling wheels 3 are installed on the periphery of the tripod 1, and the traveling wheels 3 realize the overall movement and walking;

[0029] An electrical control box 4 (using existing technology) is also installed on the tripod 1. The electrical control box 4 is electrically connected to the actuating cylinder assembly 2. Inside the electrical control box 4, there are an operation panel, a driver, a contactor, a PLC, etc., to realize the lifting, lowering and synchronous lifting control of the actuating cylinder assembly 2. A hydraulic oil tank 8 (using existing technology) is also installed on the tripod 1. The hydraulic oil tank 8 is connected to the actuating cylinder assembly 2. The hydraulic oil tank 8 serves as a hydraulic source to supply hydraulic oil to it. At the same time, a hydraulic operation box 9 (using existing technology) connected to the hydraulic oil tank 8 is also installed on the tripod 1. Inside the hydraulic operation box 9, there are a motor pump group, a load-sensing proportional multi-way valve, a pressure sensor, a flow sensor, etc., to realize the operation of the hydraulic system and control the flow of hydraulic oil through the hydraulic operation box 9. The hydraulic operation box 9 is electrically connected to the electrical control box 4, and the hydraulic operation box 9 is controlled by the electrical control box 4.

[0030] A laser displacement sensing assembly 5 is installed on the actuating cylinder assembly 2. The laser displacement sensing assembly 5 detects the displacement of the actuating cylinder assembly 2 rising in real time.

[0031] Please refer to Figure 1 - Figure 2 , the aircraft electric hydraulic synchronous control jack. Multiple groups of leveling hydraulic cylinders 6 are also installed on the periphery of the tripod 1. The leveling hydraulic cylinders 6 are preferably manual hydraulic cylinders. A support plate 61 is fixed to the bottom telescopic end of the leveling hydraulic cylinder 6. The setting of the support plate 61 realizes its stable connection with the ground. Multiple groups of leveling hydraulic cylinders 6 are used to extend when parked to lift the traveling wheels 3 off the ground and adjust the level of the tripod 1. A level 7 is installed on the tripod 1. The level 7 is used to detect the levelness of the tripod 1 and control the extension amount of multiple groups of leveling hydraulic cylinders 6 according to the data fed back by the level 7. The level of the tripod 1 needs to be adjusted before pre-lifting.

[0032] Please refer to Figure 3 - Figure 4 , the aircraft electric hydraulic synchronous control jack. The laser displacement sensing assembly 5 includes a reflector 51 fixed to the top end of the actuating cylinder assembly 2 and a laser displacement sensor 52 fixed to the bottom end of the actuating cylinder assembly 2. The laser displacement sensor 52 is used to detect the distance between the reflector 51 and the laser displacement sensor 52, so as to realize the real-time detection of the displacement of the actuating cylinder assembly 2 rising. The laser displacement sensor 52 is connected to the electrical control box 4. The displacement detected by the laser displacement sensor 52 is fed back to the hydraulic operation box 9 through the electrical control box 4. After receiving the displacement signal, the hydraulic operation box 9 amplifies it through an amplifier and uses it to control the opening degree of the load-sensing proportional multi-way valve, and the two form a closed-loop feedback control;

[0033] Synchronous lifting technology. By controlling the opening degree of the load-sensing proportional multi-way valve in the hydraulic operation box 9, the laser displacement sensor 52 detects the displacement of the actuating cylinder assembly 2 rising in real time, and the two form a closed-loop feedback control to realize synchronous lifting.

[0034] Before use, it is necessary to confirm that the laser beam of the laser displacement sensor 52 irradiates on the reflector 51;

[0035] During use, first independently control the top of the actuator assembly 2 in each jack to contact the aircraft body top pad for pre-lifting to complete the preparation before the synchronous lifting operation;

[0036] During the lifting process, the synchronous start of the actuator assemblies 2 that have completed pre-lifting in multiple groups of jacks is realized through the synchronous lifting button set on the electric control box 4. The actuator assembly 2 in one jack in contact with the fuselage will run at a fixed speed, and the actuator assemblies 2 in the other two jacks maintain the height difference before operation, and adjust their own speeds to follow the fixed-speed jack through the PID control system built in the electric control box 4;

[0037] The actuator assembly 2 is a manually self-locking multi-stage hydraulic cylinder (using existing technology), that is, the adjacent two-stage cylinder sleeves in the actuator assembly 2 are locked by the safety nut 11. That is, the safety nut 11 passes through the outer set of cylinder sleeves and even the bottom side of the inner set of cylinder sleeves. When the actuator assembly 2 is lifted to the required height, stop lifting. During the lifting period, the safety nut 11 always maintains a safe distance from the inner set of cylinder sleeves. After stopping lifting, rotate the safety nut 11 to the bottom of the corresponding cylinder sleeve to ensure that the actuator assembly 2 will not descend;

[0038] Before synchronous lowering, loosen the safety nut 11, and control the movement cylinder assemblies 2 in the three jacks to perform synchronous lowering operations through the synchronous lowering button on the electric control box 4.

[0039] Please refer to Figure 1 - Figure 2 , the aircraft electric hydraulic synchronous control jack, one side of the tripod 1 is hinged with a towing rod 10, and the towing rod 10 can tow the jack.

[0040] The three jacks are used in cooperation to realize the jacking operation of the aircraft;

[0041] Lower the traveling wheels 3 to make the traveling wheels 3 land on the ground, and use the towing rod 10 to tow the three jacks to the positions below the corresponding aircraft supports respectively;

[0042] Control the leveling hydraulic cylinder 6 to extend through the hydraulic operation box 9, raise the traveling wheels 3, lower the support disc 61, observe the level 7, and level the leveling hydraulic cylinder 6 to make the jacks stably support on the ground;

[0043] Start the system and confirm that the laser beam of the laser displacement sensor 52 irradiates on the reflector 51;

[0044] Control the top of each actuator assembly 2 to contact the aircraft body top pad (pre-lift) through the electric control box 4 to complete the preparation before the synchronous lifting operation;

[0045] Synchronous jacking: Through the synchronous jacking button on the electrical control box 4, control the three actuator assemblies 2 to perform synchronous jacking operations. During the jacking process, one of the actuator assemblies 2 will operate at a fixed speed, and the other two actuator assemblies 2 will maintain the height difference before operation and adjust their own speeds to follow the fixed-speed jack through PID;

[0046] The laser displacement sensor 52 continuously detects the displacement of the actuator rising, and the displacement is fed back to the opening degree of the load-sensitive proportional multi-way valve in the hydraulic operation box 9, and the two form a closed-loop feedback control;

[0047] When the actuator assembly 2 jacks up to the required height, stop jacking and rotate the safety nut 11 to the bottom of the corresponding actuator;

[0048] Before synchronous lowering, loosen the safety nut 11, and through the synchronous lowering button on the electrical control box 4, control the actuator assembly 2 in the three jacks to perform synchronous lowering operations.

[0049] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principle and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft electric-hydraulic synchronous control jack, comprising a tripod (1), wherein an actuating cylinder assembly (2) is fixedly arranged in the middle of the tripod (1), and is characterized in that: The actuating cylinder assembly (2) is a multi-stage hydraulic cylinder. An electrical control box (4) is also installed on the tripod (1). The electrical control box (4) is electrically connected to the actuating cylinder assembly (2). The synchronous lifting button provided on the electrical control box (4) is used to achieve the synchronous start of the actuating cylinder assemblies (2) that have completed pre-lifting among multiple groups of jacks. The actuating cylinder assembly (2) in one jack in contact with the fuselage runs at a fixed speed, and the actuating cylinder assemblies (2) in the other two jacks maintain the height difference before operation, and adjust their own speeds to follow the fixed-speed jack through the PID control system built in the electrical control box (4).

2. The aircraft electric-hydraulic synchronous control jack according to claim 1, characterized in that: A laser displacement sensing assembly (5) is installed on the actuating cylinder assembly (2). The laser displacement sensing assembly (5) detects the displacement of the actuating cylinder assembly (2) rising in real time.

3. An aircraft electric-hydraulic synchronous control jack according to claim 1, characterized in that: Multiple groups of leveling hydraulic cylinders (6) are also installed on the periphery of the tripod (1).

4. The aircraft electric-hydraulic synchronous control jack according to claim 3, characterized in that: A level (7) is installed on the tripod (1). The level (7) is used to detect the levelness of the tripod (1).

5. The aircraft electric-hydraulic synchronous control jack according to claim 2, wherein: The laser displacement sensing assembly (5) includes a reflector (51) fixed to the top end of the actuating cylinder assembly (2) and a laser displacement sensor (52) fixed to the bottom end of the actuating cylinder assembly (2). The laser displacement sensor (52) is used to detect the distance between the reflector (51) and the laser displacement sensor (52).

6. The aircraft electric-hydraulic synchronous control jack according to claim 1 or 3, characterized in that: Multiple groups of walking wheels (3) are installed on the periphery of the tripod (1).

7. An aircraft electric-hydraulic synchronous control jack according to claim 6, characterized in that: A towing bar (10) is hinged to one side of the tripod (1).

8. An aircraft electric-hydraulic synchronous control jack according to claim 1, characterized in that: The actuating cylinder assembly (2) is a manually self-locking multi-stage hydraulic cylinder.

9. The aircraft electric-hydraulic synchronous control jack according to claim 3, characterized in that: A hydraulic oil tank (8) is also installed on the tripod (1). The hydraulic oil tank (8) is connected to the leveling hydraulic cylinders (6) and the actuating cylinder assembly (2). At the same time, a hydraulic operation box (9) connected to the hydraulic oil tank (8) is installed on the tripod (1). The hydraulic operation box (9) is electrically connected to the electrical control box (4).

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