CN218058267U - Electric jacking hydraulic system of airplane - Google Patents
Electric jacking hydraulic system of airplane Download PDFInfo
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- CN218058267U CN218058267U CN202222033932.9U CN202222033932U CN218058267U CN 218058267 U CN218058267 U CN 218058267U CN 202222033932 U CN202222033932 U CN 202222033932U CN 218058267 U CN218058267 U CN 218058267U
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- airplane
- plunger pump
- hydraulic system
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- 239000003921 oil Substances 0.000 claims abstract description 51
- 230000002457 bidirectional effect Effects 0.000 claims abstract description 31
- 239000010720 hydraulic oil Substances 0.000 claims abstract description 16
- 238000001914 filtration Methods 0.000 claims description 5
- 238000013461 design Methods 0.000 claims description 3
- 239000002245 particle Substances 0.000 claims description 3
- 230000003749 cleanliness Effects 0.000 claims 1
- 230000001360 synchronised effect Effects 0.000 abstract description 3
- 238000010521 absorption reaction Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 230000008901 benefit Effects 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000009530 blood pressure measurement Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 241000237983 Trochidae Species 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
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Abstract
The utility model discloses an electric jacking hydraulic system for an airplane, which comprises an oil tank, a bidirectional plunger pump, a driver integrated servo motor, a throttling stop valve, a pressure gauge, a jack and a hydraulic pipeline; the bidirectional plunger pump is used for sucking oil from the oil tank, so that hydraulic oil enters the jack and the jack is controlled to lift; the driver integrated servo motor provides power for the bidirectional plunger pump to control the bidirectional plunger pump to absorb oil; the throttling stop valve is used for fine adjustment to realize slow descending of the airplane jack. The system can simultaneously control 3 jacks to work, realizes the independent lifting control of a single jack or the synchronous lifting control of a plurality of jacks, simplifies the operation and saves the labor cost; the driver is integrated with the servo motor to reversely rotate to drive the bidirectional plunger pump to absorb oil, so that the jack is quickly returned when the jack is in idle-load accelerated descent, and the working efficiency is improved.
Description
Technical Field
The utility model relates to an aircraft maintenance technical field, concretely relates to electronic jacking hydraulic system of aircraft.
Background
The airplane jack is necessary equipment for jacking an airplane in airplane maintenance work, and the existing jack for the airplane in China is usually a hydraulic jack. The hydraulic jack is also called oil jack, and is a jack which adopts a plunger or a hydraulic cylinder as a rigid jacking piece. Simple hoisting equipment is generally only provided with a hoisting mechanism for hoisting heavy objects. Simple structure, light weight, stable operation, large supporting force, self-locking and the like. The hydraulic jack has strong jacking capacity, and the jacking force of the heavy hydraulic jack exceeds 100t.
The plane has large volume and weight, belongs to precision machinery, and has high requirements on the safety of equipment, so that the lifting and descending operations of the jack are required to be stable and safe. At present, the domestic airplane jacking hydraulic systems are all systems with one jack corresponding to one set, and each set of system is provided with an oil suction pump, a control valve set and the like. And 3 jacks are needed to work simultaneously during jacking of the airplane, the system is numerous and complicated with the existing hydraulic system, the burden of operators is caused during operation, meanwhile, because each system works independently, if the synchronous lifting function needs to be realized, the operation of multiple persons is needed, a large amount of labor cost is increased, and when the jack descends in an idle load, the hydraulic oil pressure in the jack can only be returned to the oil tank by the user, so that the operation is troublesome and the efficiency is low.
The prior art has the following defects:
(1) A plurality of systems are needed for controlling a plurality of jacks, the operation is complex, the burden of operators is caused, the synchronous lifting function of the plurality of jacks needs to be operated by a plurality of persons, and the labor cost is increased;
(2) The jack is unloaded to descend and only can rely on the user to return the hydraulic pressure oil pressure in the jack to the oil tank, and troublesome poeration and inefficiency.
SUMMERY OF THE UTILITY MODEL
In order to solve the technical problem, the utility model provides an electronic jacking hydraulic system of aircraft.
The utility model provides an electric jacking hydraulic system for an airplane, which comprises an oil tank, a bidirectional plunger pump, a driver integrated servo motor, a throttling stop valve, a pressure gauge, a jack and a hydraulic pipeline;
the bidirectional plunger pump is used for sucking oil from the oil tank, so that hydraulic oil enters the jack and the jack is controlled to lift;
the driver integrated servo motor provides power for the bidirectional plunger pump and controls the bidirectional plunger pump to absorb oil;
the throttling stop valve is used for fine adjustment to achieve slow descending of the airplane jack.
Furthermore, the bidirectional plunger pump drives the oil suction through the reverse rotation of the driver integrated servo motor, so that the airplane jack can descend quickly.
Furthermore, the device also comprises a hand-operated pump which forms a double-pressure supply structure together with the bidirectional plunger pump.
Furthermore, the jack also comprises an overflow valve which is connected in parallel with the bidirectional plunger pump to be used as safety protection, so that the phenomenon that the service life is influenced by heating caused by pressure building in the jack is prevented.
Furthermore, a pressure gauge is arranged at the port of the overflow valve and used for displaying the pressure condition in the hydraulic pipeline in real time.
Furthermore, a plurality of check valves are arranged to prevent the hydraulic oil from suddenly flowing back.
Further, still include cartridge formula oil absorption filter, set up in the oil tank exit end, adopt the half-bridge design for filter the hydraulic oil that gets into the jack, guarantee the cleanness of jack internal line.
Furthermore, the oil tank is also provided with an air filter for filtering particles in the air and prolonging the service life of the equipment.
The utility model has the advantages that:
(1) The system can simultaneously control 3 jacks to work, so that the single jack can be controlled to be lifted independently or a plurality of jacks can be controlled to be lifted synchronously, the operation is simplified and the labor cost is saved;
(2) The driver integrated servo motor reversely rotates to drive the bidirectional plunger pump to absorb oil, so that the jack is quickly returned after being accelerated to descend in no-load, and the working efficiency is improved.
Drawings
FIG. 1 is a schematic diagram of an aircraft jacking hydraulic system;
FIG. 2 is a structural diagram of a hydraulic jacking integrated unit of the airplane of the present embodiment;
the reference numbers in the figures illustrate: 1-oil tank, 2-air filter, 3-overflow valve, 4-plug-in oil absorption filter, 6-hand pump, 7-plug-in bidirectional plunger pump, 8-driver integrated servo motor, 9-throttle stop valve, 11-pressure measuring joint, 12-pressure measuring hose, 13-pressure gauge, 14-jack, 15-mounting surface.
Detailed Description
The foregoing is only an overview of the embodiments of the present invention, and in order to make the technical means of the embodiments of the present invention more clearly understood, the embodiments of the present invention may be implemented according to the content of the description, and in order to make the above and other objects, features and advantages of the embodiments of the present invention more obvious and understandable, the following detailed description of the embodiments of the present invention is given.
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, not all, of the embodiments of the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts all belong to the protection scope of the present invention. It is to be understood that the description of the embodiments herein is for purposes of illustration and explanation only and is not intended to limit the invention. The term "coupled", unless expressly stated or limited otherwise, is to be construed broadly, e.g., "coupled" may be a fixed connection or a removable connection or as an integral part; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
Fig. 1 shows a schematic diagram of an aircraft jacking hydraulic system of the present invention, which includes an oil tank 1, a bidirectional plunger pump 7, a driver integrated servo motor 8, a throttle stop valve 9, a pressure gauge 13, a jack 14 and a hydraulic pipeline; the bidirectional plunger pump 7 is used for sucking oil from the oil tank 1, so that hydraulic oil enters the jack 14 and the jack 14 is controlled to lift; the driver integrated servo motor 8 provides power for the bidirectional plunger pump 7 and controls the bidirectional plunger pump 7 to suck oil; the throttle stop valve 9 is used for fine adjustment to realize slow descending of the aircraft jack 14. The driver integrated servo motor 8 has forward rotation and reverse rotation functions, forward rotation drives the bidirectional plunger pump 7 to suck oil from the oil tank 1 into the jack 14, reverse rotation of the motor drives the bidirectional plunger pump 7 to suck oil from the jack 14 and return the oil to the oil tank 1, and therefore the pressure relief process of the system is accelerated, and the descending speed of the jack 14 is accelerated.
The system is also internally provided with a hand pump 6, and the two-way plunger pump 7 forms a double-pressure supply structure together, so that the manual operation is switched when the two-way plunger pump 7 breaks down, and the normal work of the system is ensured. Parallelly connected overflow valve 3 that is provided with two-way plunger pump 7 and hand pump 6, be used as the safety protection of system, prevent that the too high suppress pressure of 14 internal pressures of jack from leading to the fact the influence life-span of generating heat, still be provided with manometer 13 simultaneously at the exit end of overflow valve 3, a pressure situation for in the real-time display hydraulic pressure pipeline, manometer 13 is connected with the pressure measurement joint 11 that is located 3 exit end hydraulic pressure pipelines of overflow valve through pressure measurement hose 12 in this embodiment, the dismantled and assembled change of manometer, make things convenient for later stage equipment maintenance. In order to ensure the cleanness of the hydraulic pipeline, the cartridge oil absorption filter 4 adopting a half-bridge structure design is arranged at the outlet end of the mailbox, so that the space is saved during filtering. The oil tank 1 is also provided with an air filter 2 for filtering particles in air and prolonging the service life of equipment. In order to prevent the safety accident caused by the sudden descending of the jack 14 due to the sudden backflow of the hydraulic oil in the hydraulic pipeline in the working process, a plurality of one-way valves are arranged at a plurality of positions in the system, so that the hydraulic oil can be ensured to enter the jack 14 in a one-way mode when the jack 14 is lifted, and the hydraulic oil can flow back to the oil tank 1 along a specific route when the pressure is released.
Fig. 2 is a structural diagram of the aircraft jacking hydraulic integrated unit according to the embodiment, the integrated structure has the advantage of small occupied space, in the diagram, the bidirectional plunger pump 7 is of an internal insertion structure and is located in the housing above the driver integrated servo motor 8, the top of the housing is an installation surface 15 for connecting and installing equipment such as an oil tank 1 and a jack set, the throttling stop valve 9 and the hand pump 6 are respectively arranged on the front surface and the side surface of the housing at the top of the driver integrated servo motor 8, and the plug-in oil absorption filter 4 is installed close to the hand pump 6. A series of check valve sets are arranged inside the top shell of the integrated unit. The following is a specific workflow of this embodiment.
Control of individual jacks [ example 1 ]:
as shown in fig. 1, the system is started, the manual operation hand pump 6 or the driver integrated servo motor 8 rotates forward to drive the bidirectional plunger pump 7, oil is absorbed from the oil tank 1 through the oil absorption filter 4, then hydraulic oil enters the jack 14 through the one-way valve, the jack 14 is enabled to lift alone, the lifting speed can be controlled by setting the rotating speed of the driver integrated servo motor 8, when the jack 14 is lifted to a proper position, the driver integrated servo motor 8 stops, the jack 14 stops working, the lifting height is fixed, and if the height needs to be finely adjusted, the throttle stop valve 9 is manually unscrewed for adjustment.
when two or more jacks need to be lifted simultaneously, the initial position and the height of each jack are determined firstly, all the jacks needing to be lifted simultaneously are connected to the positions of the jacks 14 in the figure 1, the system is started, the driver integrated servo motor 8 rotates forwards to drive the bidirectional plunger pump 7, oil is absorbed from the oil tank 1 through the oil absorption filter 4, then hydraulic oil enters the jack group through the one-way valve, the jacks 14 are lifted independently, the lifting speed can be controlled by setting the rotating speed of the driver integrated servo motor 8, when the jacks 14 are lifted to the proper positions, the driver integrated servo motor 8 stops, the jacks 14 stop working, the lifting height is fixed, and if the height needs to be finely adjusted, the throttle stop valve 9 is manually unscrewed for adjustment.
Example 3 jack load descent:
as shown in fig. 1, when the jack 14 descends with a load, the throttle stop valve 9 is manually and slowly unscrewed, so that the hydraulic oil in the jack 14 flows back to the tank 1 through the throttle stop valve 9 and the check valves, the descending speed of the jack 14 is controlled to be finely adjusted by screwing the number of turns of the throttle stop valve 9 in the process, and when the jack descends to a certain position, the throttle stop valve 9 is screwed and closed, so that the jack 14 stops working and is fixed in height.
Example 4 jack no-load descent:
as shown in fig. 1, when the jack 14 descends in an idle load, the fully-opened throttle stop valve 9 is manually screwed, the driver integrated servo motor 8 is started, the motor rotates reversely to drive the bidirectional plunger pump 7 to suck oil, so that hydraulic oil in the jack 14 quickly flows back to the oil tank 1, and the accelerated descending of the aircraft jack is realized. When the lifting jack descends to a determined position, the driver integrated servo motor 8 and the throttle stop valve 9 are closed, the lifting jack 14 stops working, and the height is fixed.
The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily think of various equivalent modifications or replacements within the technical scope of the present invention, and these modifications or replacements should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. An electric jacking hydraulic system of an airplane is characterized by comprising an oil tank (1), a bidirectional plunger pump (7), a driver integrated servo motor (8), a throttling stop valve (9), a pressure gauge (13), a jack (14) and a hydraulic pipeline;
the bidirectional plunger pump (7) is used for sucking oil from the oil tank (1), so that hydraulic oil enters the jack (14) through a hydraulic pipeline and controls the jack (14) to lift;
the driver integrated servo motor (8) provides power for the bidirectional plunger pump (7) and controls the bidirectional plunger pump (7) to absorb oil;
the throttling stop valve (9) is used for fine adjustment to achieve slow descending of the airplane jack.
2. The electric jacking hydraulic system for the airplane as claimed in claim 1, wherein the bidirectional plunger pump (7) drives the oil suction by the reverse rotation of the driver integrated servo motor (8) to realize the rapid descending of the airplane jack (14).
3. The electric jacking hydraulic system for airplanes as claimed in claim 1, further comprising a hand pump (6) forming a double pressure supply structure together with the bidirectional plunger pump (7).
4. The electric jacking hydraulic system of an airplane as claimed in claim 1, further comprising an overflow valve (3) connected in parallel with the bidirectional plunger pump (7) for safety protection, so as to prevent the service life of the jack from being affected by heat generated due to pressure holding inside the jack.
5. The electric jacking hydraulic system for the airplane as claimed in claim 4, wherein a pressure gauge (13) is arranged at a port of the overflow valve (3) and is used for displaying the pressure condition in the hydraulic pipeline in real time.
6. The hydraulic system for electric jacking airplane as claimed in claim 1, wherein a plurality of check valves are further provided to prevent the hydraulic oil from suddenly flowing back.
7. The electric jacking hydraulic system for the airplane as claimed in claim 1, further comprising a plug-in type oil suction filter (4) disposed at the outlet end of the oil tank, and adopting a half-bridge design for filtering the hydraulic oil entering the jack (14) to ensure the cleanliness of the internal pipeline.
8. The electric jacking hydraulic system for the airplane as claimed in claim 1, wherein an air filter (2) is further arranged on the oil tank and used for filtering particles in air and prolonging the service life of equipment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222033932.9U CN218058267U (en) | 2022-08-03 | 2022-08-03 | Electric jacking hydraulic system of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222033932.9U CN218058267U (en) | 2022-08-03 | 2022-08-03 | Electric jacking hydraulic system of airplane |
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| Publication Number | Publication Date |
|---|---|
| CN218058267U true CN218058267U (en) | 2022-12-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222033932.9U Active CN218058267U (en) | 2022-08-03 | 2022-08-03 | Electric jacking hydraulic system of airplane |
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| Country | Link |
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| CN (1) | CN218058267U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115750492A (en) * | 2022-12-21 | 2023-03-07 | 成都立航科技股份有限公司 | Novel integrated pump control hydraulic power unit and control method |
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2022
- 2022-08-03 CN CN202222033932.9U patent/CN218058267U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115750492A (en) * | 2022-12-21 | 2023-03-07 | 成都立航科技股份有限公司 | Novel integrated pump control hydraulic power unit and control method |
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