CN201971167U - Cleaning device for airplane ground hydraulic system - Google Patents
Cleaning device for airplane ground hydraulic system Download PDFInfo
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- CN201971167U CN201971167U CN2010206787501U CN201020678750U CN201971167U CN 201971167 U CN201971167 U CN 201971167U CN 2010206787501 U CN2010206787501 U CN 2010206787501U CN 201020678750 U CN201020678750 U CN 201020678750U CN 201971167 U CN201971167 U CN 201971167U
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Abstract
The utility model provides a cleaning device for an airplane ground hydraulic system, the cleaning device is a ground protection device matched with the airplane. The cleaning device mainly consists of a carriage-type specially assembled part and a trailer chassis, wherein the trailer chassis can be an automobile chassis to form a self-cleaning device and also can be a non-motorized chassis to form a fixed trailer device; the specially assembled part is mainly composed of a hydraulic device, an instrument control system, an electric control system, a power system and a vehicle body, wherein the vehicle body comprises a vehicle frame, a door and a window; the vehicle body is formed by using a metal shell to wrap the specially assembled part to be concentratively installed on the trailer chassis. The cleaning device integrates the functions of a hydraulic oil pump vehicle and a cleaning tanker together to finish airplane ground detection and maintenance, thereby realizing multiple functions of power source, purifying, cleaning, injecting, on-line inspection of contamination level and test platform and the like, and realizing guarantee of multiple types of airplanes. The cleaning device has the characteristics that the cleaning device has strong flexibility, compact structure, small vibration and low noise and is easy to park or transfer.
Description
Technical field
The utility model relates to a kind of aircraft floor hydraulic efficiency pressure system cleaning apparatus, exactly is a kind of plane hydraulic system ground detection, maintenance, cleaning apparatus, is the ground handling equipment supporting with aircraft.
Background technology
Plane hydraulic system ground handling equipment of the prior art mainly contains two kinds of forms, a kind of hydraulic oil pump tender that propulsion source is provided for plane hydraulic system; The another kind of cleaning Vehicle that the hydraulic oil cleaning is provided for plane hydraulic system.When the plane hydraulic system surface work, two kinds of equipment use respectively, exist device category many, function singleness, clean that flow is little, pressure is low, can't on-line monitoring etc. technical barrier and complicated operation, wasting manpower and material resources.
Summary of the invention
The purpose of this utility model is at above-mentioned the deficiencies in the prior art, and a kind of new installation of design-calculated.It is a kind of guarantee equipment that propulsion source, purification, cleaning, online detection, filling and test platform etc. are multi-functional, the multimachine kind is one that collects.On the basis of hydraulic oil pump tender, improve the hydraulic efficiency pressure system cleaning speed, realize the pollution degree of hydraulic oil grade of online detection cleaning apparatus itself and plane hydraulic system, real-time monitoring system is dynamic, understands hydraulic services wear debris degree.
For achieving the above object, the utility model adopts following technical proposals: aircraft floor hydraulic efficiency pressure system cleaning apparatus, and mainly adorn partly and pull chassis (5) two large divisions and form by van-type is special.It is pulled chassis (5) and can be car chassis (constituting the self-propelled cleaning apparatus), also can be non-motor chassis (constituting fixed type pulling type equipment).Its special dress part mainly is made up of hydraulic efficiency gear (3), instrument maneuvering system (2), electric control system (1), power system (4) and car body (6).Car body (6) comprises vehicle frame, door and window, and it is adorned the part enclosure aggregate with metal shell with the spy and is installed in and pulls chassis (5) and go up and constitute.Establish parts such as hydraulic tubing, power, cleaning, online detection, supervision in the car body.Concrete structure and annexation are: described hydraulic efficiency gear comprises radiator, the low pressure oil filter, Hydraulic Pump, assemblies such as degree of contamination on-line measuring device, the annexation of its structure and propulsion source part is: aircraft floor back leakage connection (24) successively with low pressure hose (23), oil radiator (22) communicates, be divided into four the tunnel in oil radiator (22) outlet, one the tunnel directly enters low-pressure filter (15), another road enters low-pressure safety valve (29) and leads to outside the system, one the tunnel communicate again with aie escape valve (30), the four the tunnel enters low-pressure filter (15) by degree of contamination on-line measuring device (21) communicates with Hydraulic Pump (12), be divided into three the tunnel at Hydraulic Pump (12), one the tunnel with oil return oil filter, oil radiator (22) communicates, another road and pressure regulating valve (10) constitute the loop, again one the tunnel with high-pressure filter (20), precise oil filter (13), check valve (14), governor valve (16) communicates, be divided into three the tunnel in governor valve (16) outlet, one the tunnel directly communicates with flow counter (17), another road and flow regulating valve (11), oil radiator (22) communicates, Third Road and safety valve integrated package (28), oil radiator (22) communicates.Flow counter (17) communicates with the top connection of aircraft machine with high-pressure rubber pipe (25), aircraft floor fuel-intake connection (26).Electric-motor pump (18) communicates with fuel tank (19), communicates with oil radiator (22) by safety valve integrated package (28).Self-loopa assembly (27) constitutes the loop separately.
Constructional feature of the present utility model is: the chassis is pulled in a, employing, and alerting ability is strong; The function of b, hydraulic oil pump tender and cleaning Vehicle rolls into one, and finishes the requirement of aircraft floor detection and handling labor; C, realization propulsion source, purification, cleaning, filling, the online detection degree of contamination and test platform etc. are multi-functional, the multimachine kind ensures; D, on-line monitoring parts of dual system can be monitored multichannel contamination level of oil liquid grade; E, according to the aircraft utilization requirement, pressure can be regulated arbitrarily; F, miniaturization, compact conformation is easy to park or cut to; G, little, the low noise of vibration; H, real-time monitoring system are dynamic, understand hydraulic services wear debris degree.
Description of drawings
Fig. 1 is a structural representation of the present utility model.
Fig. 2 is the birds-eye view of Fig. 1.
Fig. 3 is the utility model hydraulic system structure scheme drawing.
Fig. 4 is the birds-eye view of Fig. 3.
Fig. 5 is the utility model degree of contamination on-line measuring device scheme drawing.
The specific embodiment
Embodiment:
With reference to Fig. 1-4, aircraft floor hydraulic efficiency pressure system cleaning apparatus is mainly adorned partly and is pulled chassis 5 two large divisions and form by van-type is special.It is pulled the chassis and can be car chassis (constituting the self-propelled cleaning apparatus), also can be non-motor chassis (constituting fixed type pulling type equipment).Its special dress part mainly is made up of hydraulic efficiency gear 3, instrument maneuvering system 2, electric control system 1, power system 4 and car body 6.Car body comprises vehicle frame, door and window, and it is adorned the part enclosure aggregate with metal shell with the spy and is installed in and pulls on the chassis 5 and constitute.Establish hydraulic tubing in the car body, power, clean, online detection, parts such as supervision, concrete structure and annexation are: described hydraulic efficiency gear comprises radiator, the low pressure oil filter, Hydraulic Pump, assemblies such as degree of contamination on-line measuring device, the annexation of its structure and propulsion source part is: aircraft floor back leakage connection 24 successively with low pressure hose 23, oil radiator 22 communicates, be divided into four the tunnel in oil radiator 22 outlets, one the tunnel directly enters low-pressure filter 15, another road enters low-pressure safety valve 29 and leads to outside the system, one the tunnel communicate again with aie escape valve 30, the four the tunnel enters low-pressure filter 15 by degree of contamination on-line measuring device 21 communicates with Hydraulic Pump 12, be divided into three the tunnel at Hydraulic Pump 12, one the tunnel with oil return oil filter, oil radiator 22 communicates, another road and pressure regulating valve 10 constitute the loop, again one the tunnel with high-pressure filter 20, precise oil filter 13, check valve 14, governor valve 16 communicates, be divided into three the tunnel in governor valve 16 outlets, one the tunnel directly communicates with flow counter 17, another road and flow regulating valve 11, oil radiator 22 communicates, Third Road and safety valve integrated package 28, oil radiator 22 communicates.Flow counter 17 communicates with the top connection of aircraft machine with high-pressure rubber pipe 25, aircraft floor fuel-intake connection 26.Electric-motor pump 18 communicates with fuel tank 19, communicates with oil radiator 22 by safety valve integrated package 28.Self-loopa assembly 27 constitutes the loop separately.Hydraulic principle of the present utility model is: hydraulic oil arrives oil radiator 22 through aircraft floor back leakage connection 24, low pressure hose 23, realizing that reducing oil temperature back arrives low-pressure filter 15, arrive Hydraulic Pump 12 after blocking the large-size particle in the fluid, the high pressure oil that produces, the hydraulic oil that blocks behind molecule, the cleaning by high-pressure filter 20, precise oil filter 13 realizations provides high pressure, big flow, the up-to-standard hydraulic oil of degree of contamination grade through check valve 14, flow counter 17, high-pressure rubber pipe 25, aircraft floor fuel-intake connection 26 for aircraft.
With reference to Fig. 5, degree of contamination detecting device 21 comprises degree of contamination sensor 31, on-off valve 32, integrated valve block 33.Above-mentioned degree of contamination sensor 31, on-off valve 32 and integrated valve block 33 are connected by pipeline.Fluid enters degree of contamination sensor 31 through integrated valve block 33, on-off valve 32, and the fluid after the detection turns back to system through on-off valve 32 and integrated valve block 33.
Claims (2)
1. aircraft floor hydraulic efficiency pressure system cleaning apparatus, mainly adorn partly and pull chassis (5) two large divisions and form by van-type is special, it is characterized in that: the described chassis (5) of pulling can be car chassis, constitutes the self-propelled cleaning apparatus, also can be non-motor chassis and constitutes fixed type pulling type equipment; Described special dress part mainly is made up of hydraulic efficiency gear (3), instrument maneuvering system (2), electric control system (1), power system (4) and car body (6), car body (6) comprises vehicle frame, door and window, and it is adorned the part enclosure aggregate with metal shell with the spy and is installed in and pulls chassis (5) and go up and constitute.
2. aircraft floor hydraulic efficiency pressure system cleaning apparatus as claimed in claim 1, it is characterized in that: establish hydraulic efficiency gear in its described car body (6), power, clean, online detection, monitor parts, concrete structure and annexation are: described hydraulic efficiency gear comprises radiator, the low pressure oil filter, Hydraulic Pump, degree of contamination on-line measuring device assembly, the annexation of its structure and propulsion source part is: aircraft floor back leakage connection (24) successively with low pressure hose (23), oil radiator (22) communicates, be divided into four the tunnel in oil radiator (22) outlet, one the tunnel directly enters low-pressure filter (15), another road enters low-pressure safety valve (29) and leads to outside the system, one the tunnel communicate again with aie escape valve (30), the four the tunnel enters low-pressure filter (15) by degree of contamination detecting device (21) communicates with Hydraulic Pump (12), be divided into three the tunnel at Hydraulic Pump (12), one the tunnel with oil return oil filter, oil radiator (22) communicates, another road and pressure regulating valve (10) constitute the loop, again one the tunnel with high-pressure filter (20), precise oil filter (13), check valve (14), governor valve (16) communicates, be divided into three the tunnel in governor valve (16) outlet, one the tunnel directly communicates with flow counter (17), another road and flow regulating valve (11), oil radiator (22) communicates, Third Road and safety valve integrated package (28), oil radiator (22) communicates, flow counter (17) and high-pressure rubber pipe (25), aircraft floor fuel-intake connection (26) communicates with the top connection of aircraft machine, electric-motor pump (18) communicates with fuel tank (19), communicate with oil radiator (22) by safety valve integrated package (28), self-loopa assembly (27) constitutes the loop separately; Degree of contamination detecting device (21) comprises degree of contamination sensor (31), on-off valve (32) and integrated valve block (33), and above-mentioned degree of contamination sensor (31), on-off valve (32) and integrated valve block (33) are connected by pipeline.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206787501U CN201971167U (en) | 2010-12-24 | 2010-12-24 | Cleaning device for airplane ground hydraulic system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206787501U CN201971167U (en) | 2010-12-24 | 2010-12-24 | Cleaning device for airplane ground hydraulic system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201971167U true CN201971167U (en) | 2011-09-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010206787501U Expired - Lifetime CN201971167U (en) | 2010-12-24 | 2010-12-24 | Cleaning device for airplane ground hydraulic system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201971167U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103818562A (en) * | 2013-12-03 | 2014-05-28 | 海丰通航科技有限公司 | Airplane ground service integrated support system |
| CN105800183A (en) * | 2016-04-07 | 2016-07-27 | 中国南方航空工业(集团)有限公司 | Liquid storage tank for engine cleaning vehicle |
| CN108698698A (en) * | 2016-02-09 | 2018-10-23 | 塞尔有限责任公司 | Air exit, the wall elements with the air exit and the cleaning method using the air exit |
| CN108816974A (en) * | 2018-09-03 | 2018-11-16 | 张家港韶液液压技术有限公司 | The hydraulic system of scouring stage |
| CN108872546A (en) * | 2017-05-08 | 2018-11-23 | 沈阳航达机载设备有限公司 | A kind of quality detection device suitable for high pressure and low pressure oil liquid |
-
2010
- 2010-12-24 CN CN2010206787501U patent/CN201971167U/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103818562A (en) * | 2013-12-03 | 2014-05-28 | 海丰通航科技有限公司 | Airplane ground service integrated support system |
| CN103818562B (en) * | 2013-12-03 | 2017-01-25 | 海丰通航科技有限公司 | Airplane ground service integrated support system |
| CN108698698A (en) * | 2016-02-09 | 2018-10-23 | 塞尔有限责任公司 | Air exit, the wall elements with the air exit and the cleaning method using the air exit |
| CN108698698B (en) * | 2016-02-09 | 2021-10-19 | 赛峰客舱德国有限公司 | Exhaust outlet, wall element having the same, and cleaning method using the same |
| CN105800183A (en) * | 2016-04-07 | 2016-07-27 | 中国南方航空工业(集团)有限公司 | Liquid storage tank for engine cleaning vehicle |
| CN108872546A (en) * | 2017-05-08 | 2018-11-23 | 沈阳航达机载设备有限公司 | A kind of quality detection device suitable for high pressure and low pressure oil liquid |
| CN108816974A (en) * | 2018-09-03 | 2018-11-16 | 张家港韶液液压技术有限公司 | The hydraulic system of scouring stage |
| CN108816974B (en) * | 2018-09-03 | 2023-12-29 | 张家港韶液液压技术有限公司 | Hydraulic system of flushing station |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee | ||
| CP03 | Change of name, title or address |
Address after: 110048, 239-6 West Shen Shen road, Yuhong District, Liaoning, Shenyang Patentee after: Shenyang Hangda Airborne Equipment Co., Ltd. Address before: 110034 No. 2 Qianshan West Road, Yuhong District, Liaoning, Shenyang Patentee before: Shenyang Hangda Airborne Equipment Co. |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20110914 |