Electro-hydraulic synchronous control jack for airplane

Abstract

The invention relates to the technical field of aviation support equipment related manufacturing, in particular to an aircraft electric hydraulic synchronous control jack which comprises a triangular support, an actuator cylinder assembly is fixed to the middle of the triangular support, the actuator cylinder assembly stretches out and draws back to achieve jacking and landing of an aircraft, at least three jack sets need to be used for jacking the aircraft, and the jack sets are fixed to the triangular support. 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 invention relates to the technical field of manufacturing related to aviation support equipment, and in particular to an aircraft electric hydraulic synchronous control jack. Background Art

[0002] The jack can be used to lift the aircraft during normal operations such as horizontal measurement, weighing, disassembly and assembly, retraction and extension of the landing gear, and correction and adjustment of the installation position of airborne equipment.

[0003] At present, there are many forms of aircraft jack lifting and lowering operations. One is to lift the jack by reciprocatingly shaking a manual pump by manpower, and the other is to lift it by motor drive. The output of the lifting capacity is through a hydraulic system and a mechanical transmission system.

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

[0005] Synchronous control can be achieved by combining mechanical wire sensors with hydraulic systems or by combining laser displacement sensors with hydraulic systems. Mechanical wire sensors are subject to space limitations, rope wear, regular inspection and maintenance, and environmental factors, which can restrict their use and cause inconvenience.

[0006] Based on this, the present invention provides an aircraft electric hydraulic synchronous control jack with high synchronization accuracy, high lifting efficiency, small jack space volume and light weight. Summary of the invention

[0007] The present invention aims to at least solve the problems of large volume and low working efficiency of the jack in the prior art.

[0008] The present invention 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 a tripod stable form. The peripheral side of the tripod is equipped with multiple sets of running wheels, and the running wheels realize the overall movement and walking; an actuator cylinder assembly is fixed in the middle of the tripod, and the actuator cylinder assembly performs telescopic action to realize the lifting and landing of the aircraft. The actuator cylinder assembly is a multi-stage hydraulic cylinder. The aircraft lifting needs to use at least three sets of jacks, one set is used to lift the fuselage, and the other two sets are used to lift the two sets of wings;

[0009] An electrical control box is also installed on the tripod, and the electrical control box is electrically connected to the actuator assembly. When in use, the electrical control box controls each jack to contact the top pad of the aircraft body for pre-jacking, thereby completing the preparation before the synchronous jacking operation. During the jacking process, the synchronous jacking button provided on the electrical control box is used to realize the synchronous start of the actuator assemblies that have completed the pre-jacking in multiple groups of jacks.

[0010] Preferred technical solution 1: A laser displacement sensor assembly is installed on the actuator assembly, and the laser displacement sensor assembly detects the displacement of the actuator assembly in real time.

[0011] Optimal technical solution 2: A plurality of sets of leveling hydraulic cylinders are installed on the periphery of the tripod, and the plurality of sets of leveling hydraulic cylinders are used to extend and lift the traveling wheels off the ground when parked.

[0012] Preferred technical solution three: A leveler is installed on the tripod, and the leveler is used to detect the horizontality of the tripod and is used in conjunction with a leveling hydraulic cylinder.

[0013] Preferred technical solution four: A hydraulic oil tank is also installed on the tripod, and the hydraulic oil tank is connected to the leveling hydraulic cylinder and the actuator assembly to supply hydraulic oil thereto; at the same time, a hydraulic operating box connected to the hydraulic oil tank is also installed on the tripod, and the flow of hydraulic oil is controlled by the hydraulic operating box. The hydraulic operating box is electrically connected to the electrical control box, and the hydraulic operating box is controlled by the electrical control box.

[0014] Optimal technical solution five: A support plate is fixed to the telescopic end at the bottom of the leveling hydraulic cylinder, and the support plate enables the jack to be stably engaged with the ground.

[0015] Preferred technical solution six: A traction rod is hingedly connected to one side of the tripod, and the traction rod can pull the jack.

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

[0017] 1. It can realize the lifting and lowering functions of large transport aircraft, is driven by an electric hydraulic system, and has the function of synchronous lifting;

[0018] 2. High synchronization accuracy, high lifting efficiency, small jack space volume and light weight. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The accompanying 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 of the present invention. In the accompanying drawings:

[0020] Figure 1 This is a schematic diagram of the overall structure of this scheme;

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

[0022] Figure 3 This is a schematic diagram of the structure of this scheme; Figure 4 This is the operation flow chart of this program.

[0023] Among them, 1. tripod, 2. actuator assembly, 3. walking wheel, 4. electrical control box, 5. laser displacement sensor assembly, 51. reflector, 52. laser displacement sensor, 6. leveling hydraulic cylinder, 61. support plate, 7. leveler, 8. hydraulic oil tank, 9. hydraulic operation box, 10. traction rod, 11. safety nut. DETAILED DESCRIPTION

[0024] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments; based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0025] See also Figure 1-Figure 2 , an aircraft electro-hydraulic synchronous control jack, comprising a tripod 1, wherein the tripod assembly is used to stably and reliably support the weight of the aircraft, and is a tripod-stabilized form;

[0026] An actuator assembly 2 is fixed in the middle of the tripod 1. The top of the actuator assembly 2 performs telescopic movements to realize the lifting and landing of the aircraft. The actuator assembly 2 is a multi-stage hydraulic cylinder. At least three sets of hydraulic jacks are required for lifting the aircraft. One set is used to lift the fuselage, and the other two sets are used to lift the two sets of wings.

[0027] The tripod 1 is provided with a plurality of sets of running wheels 3 on its circumference, and the running wheels 3 enable the overall movement.

[0028] The tripod 1 is also equipped with an electrical control box 4 (using the existing technology), which is electrically connected to the actuator assembly 2. The electrical control box 4 contains an operation panel, a driver, a contactor, a PLC, etc., to realize the lifting, lowering and synchronous lifting control of the actuator assembly 2; the tripod 1 is also equipped with a hydraulic oil tank 8 (using the existing technology), which is connected to the actuator assembly 2. The hydraulic oil tank 8 is used as a hydraulic source to supply hydraulic oil thereto; at the same time, the tripod 1 is also equipped with a hydraulic operation box 9 (using the existing technology) connected to the hydraulic oil tank 8. The hydraulic operation box 9 contains a motor pump group, a load-sensitive proportional multi-way valve, a pressure sensor, a flow sensor, etc. to realize the operation of the hydraulic system, and the flow of hydraulic oil is controlled by 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;

[0029] The actuating cylinder assembly 2 is provided with a laser displacement sensor assembly 5 , which detects the displacement of the actuating cylinder assembly 2 in real time.

[0030] See also Figure 1-Figure 2 , the aircraft electric hydraulic synchronous control jack, the tripod 1 is also equipped with multiple sets of leveling hydraulic cylinders 6 around the side, the leveling hydraulic cylinders 6 are preferably manual hydraulic cylinders, the bottom telescopic end of the leveling hydraulic cylinder 6 is fixed with a support plate 61, the setting of the support plate 61 realizes its stable engagement with the ground, the multiple sets of leveling hydraulic cylinders 6 are used to extend when parking to lift the walking wheels 3 off the ground and adjust the level of the tripod 1, the tripod 1 is installed with a leveler 7, the leveler 7 is used to detect the levelness of the tripod 1, and the extension amount of the multiple sets of leveling hydraulic cylinders 6 is controlled according to the data fed back by the leveler 7, and the level of the tripod 1 needs to be adjusted before pre-top.

[0031] See also Figure 3-Figure 4 , aircraft electric hydraulic synchronous control jack, the laser displacement sensor assembly 5 includes a reflector 51 fixed on the top of the actuator assembly 2 and a laser displacement sensor 52 fixed on the bottom of the actuator 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 actuator assembly 2, 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, the hydraulic operation box 9 receives the displacement signal and amplifies it through the amplifier to control the opening degree of the load-sensitive proportional multi-way valve, and the two form a closed-loop feedback control;

[0032] The synchronous lifting technology controls the opening degree of the load-sensitive proportional multi-way valve in the hydraulic operating box 9, and the laser displacement sensor 52 detects the displacement of the actuator assembly 2 in real time. The two form a closed-loop feedback control to achieve synchronous lifting.

[0033] Before use, it is necessary to confirm that the laser beam of the laser displacement sensor 52 is irradiated on the reflector 51;

[0034] When in use, first independently control the top of the actuator assembly 2 in each jack to contact the top pad of the aircraft body for pre-jacking, completing the preparation before the synchronous jacking operation;

[0035] During the lifting process, the synchronous lifting button set on the electrical control box 4 is used to realize the synchronous start of the actuator assemblies 2 that have completed the pre-lifting in multiple groups of jacks. The actuator assembly 2 in one of the jacks in contact with the fuselage will run at a fixed speed, and the actuator assemblies 2 in the other two jacks will maintain the height difference before the operation, and adjust their own speed to follow the fixed speed jack through the built-in PID control system of the electrical control box 4;

[0036] The actuator assembly 2 is a manual self-locking multi-stage hydraulic cylinder (using the existing technology), that is, the two adjacent cylinder sleeves in the actuator assembly 2 are locked by a safety nut 11, that is, the safety nut 11 passes through the bottom side of the outer group of cylinder sleeves and even the inner group of cylinder sleeves. When the actuator assembly 2 is lifted to the required height, the lifting is stopped. During the lifting, the safety nut 11 always maintains a safe distance with the inner group of cylinder sleeves. After the lifting is stopped, the safety nut 11 is rotated to the bottom of the corresponding cylinder sleeve to ensure that the actuator assembly 2 does not fall;

[0037] Before synchronous descent, loosen the safety nut 11, and control the moving cylinder assembly 2 of the three jacks to perform synchronous descent operation through the synchronous descent button of the electrical control box 4.

[0038] See also Figure 1-Figure 2 , the aircraft electric hydraulic synchronous control jack, one side of the tripod 1 is hingedly connected with a traction rod 10, and the traction rod 10 can tow the jack.

[0039] Three jacks are used together to realize the aircraft support operation;

[0040] Lower the running wheel 3 so that it touches the ground, and use the traction rod 10 to pull the three jacks to the bottom of the corresponding aircraft support respectively;

[0041] The hydraulic cylinder 6 is extended by the hydraulic operation box 9, the travel wheel 3 is raised, the support plate 61 is lowered, and the leveler 7 is observed to adjust the hydraulic cylinder 6 to a level so that the jack is stably supported on the ground;

[0042] Start the system and confirm that the laser beam of the laser displacement sensor 52 is irradiated on the reflector 51;

[0043] The electrical control box 4 controls the top of each actuator assembly 2 to contact the top pad of the aircraft body (pre-top), completing the preparation before the synchronous jacking operation;

[0044] Synchronous lifting: through the synchronous lifting button of the electrical control box 4, the three actuator assemblies 2 are controlled to perform synchronous lifting operations. During the lifting process, one of the actuator assemblies 2 will run at a fixed speed, and the other two actuator assemblies 2 will maintain the height difference before operation, and adjust their own speed through PID to follow the fixed speed jack;

[0045] The laser displacement sensor 52 detects the displacement of the actuator in real time, 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;

[0046] When the actuator assembly 2 is lifted to the required height, the lifting is stopped and the safety nut 11 is rotated to the bottom of the corresponding actuator;

[0047] Before synchronous descent, loosen the safety nut 11, and control the actuator assemblies 2 in the three jacks to perform synchronous descent operation through the synchronous descent button of the electrical control box 4.

[0048] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft electro-hydraulic synchronous control jack, comprising a tripod (1), an actuator assembly (2) being fixed in the middle of the tripod (1), characterized in that: The actuator assembly (2) is a multi-stage hydraulic cylinder. At least three sets of jacks are required to lift the aircraft. An electrical control box (4) is also installed on the tripod (1). The electrical control box (4) is electrically connected to the actuator assembly (2). The synchronous lifting button provided on the electrical control box (4) is used to synchronize the start of the actuator assemblies (2) in the multiple sets of jacks that have completed pre-lifting. The actuator assembly (2) in one of the jacks in contact with the fuselage will run at a fixed speed, while the actuator assemblies (2) in the other two jacks will maintain the height difference before running, and adjust their own speed to follow the fixed speed jack through the built-in PID control system of the electrical control box (4).

2. The aircraft electro-hydraulic synchronous control jack according to claim 1, characterized in that: A laser displacement sensor assembly (5) is installed on the actuator assembly (2), and the laser displacement sensor assembly (5) detects the displacement of the actuator assembly (2) in real time.

3. The aircraft electro-hydraulic synchronous control jack according to claim 1, characterized in that: A plurality of groups of leveling hydraulic cylinders (6) are also installed on the peripheral side of the tripod (1).

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

5. The aircraft electro-hydraulic synchronous control jack according to claim 2, characterized in that: The laser displacement sensor assembly (5) comprises a reflector (51) fixed at the top end of the actuator cylinder assembly (2) and a laser displacement sensor (52) fixed at the bottom end of the actuator 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. An aircraft electro-hydraulic synchronous control jack according to claim 1 or 3, characterized in that: A plurality of sets of running wheels (3) are installed on the peripheral side of the tripod (1).

7. The aircraft electro-hydraulic synchronous control jack according to claim 6, characterized in that: A traction rod (10) is hingedly connected to one side of the tripod (1).

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

9. The aircraft electro-hydraulic synchronous control jack according to claim 3, characterized in that: The tripod (1) is also provided with a hydraulic oil tank (8), which is connected to the leveling hydraulic cylinder (6) and the actuator assembly (2). The tripod (1) is also provided with a hydraulic operating box (9) connected to the hydraulic oil tank (8), which is electrically connected to the electrical control box (4).

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