CN205478682U - External hydraulic pump cooler of aircraft - Google Patents
External hydraulic pump cooler of aircraft Download PDFInfo
- Publication number
- CN205478682U CN205478682U CN201620203816.9U CN201620203816U CN205478682U CN 205478682 U CN205478682 U CN 205478682U CN 201620203816 U CN201620203816 U CN 201620203816U CN 205478682 U CN205478682 U CN 205478682U
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- Prior art keywords
- hydraulic pump
- external hydraulic
- aircraft
- hydraulic system
- utility
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- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model discloses an external hydraulic pump cooler of aircraft, including a box, the top surface of box is opened has the through -hole, and the fixed radiator fan that is equipped with in top of box, the inherent radiator fan's of box the fixed radiator that is equipped with in below, the entry of radiator are equipped with into that oil pipe, export are equipped with out oil pipe, and the removal gyro wheel is installed to the bottom surface of box. The utility model discloses can prevent that hydraulic system is overheated for hydraulic system provides the heat dissipation function when carrying out rudder face control test, and can the quick travel, the operating personnel of being convenient for uses and carries, adopt intelligent control's mode, can carry out real time monitoring to the state of hydraulic system when carrying out rudder face control test in real time to automatically regulated rate of heat removal is equipped with the state that dedicated status display ware shows hydraulic system in real time simultaneously, the utility model discloses the structure is succinct, with low costs, can effectively reduce the cost of aircraft maintenance and test.
Description
Technical field
This utility model relates to a kind of aircraft external hydraulic pump cooler.
Background technology
Hydraulic system is the important component part of aircraft, and the hydraulic system of general aircraft is all from radiator, liquid
Pressure system can produce substantial amounts of heat when normal work, and radiator takes away guarantee hydraulic system properly heat
Temperature range work.But the hydraulic system of commercial narrow body aircraft carries out rudder face under service mode and controls test
Time (low power consumpting state), the carrying radiator and cannot work of hydraulic system, and hydraulic system is carrying out rudder face control
Also heat can be produced during system test (low power consumpting state).Although the heat produced during test is not than hydraulic pressure system
The heat produced when normal work of uniting is big, but to control the testing time long due to rudder face, and productive set is substantial amounts of
Heat so that Prevention of Hydraulic System Overheating, under long-time overheat condition, hydraulic system may damage generation economy damage
Lose.
Utility model content
The purpose of this utility model is to provide a kind of aircraft external hydraulic pump cooler, can carry out for hydraulic system
Rudder face controls to provide heat sinking function during test, prevents Prevention of Hydraulic System Overheating.
The purpose of this utility model is to take following technical scheme to be achieved:
A kind of aircraft external hydraulic pump cooler, including a casing, it is characterised in that: the end face of casing has logical
Hole, the top of casing is fixed with a radiator fan, is fixed with a heat radiation in the lower section of radiator fan in casing
Device, the entrance of radiator is provided with oil inlet pipe, outlet is provided with flowline, and the bottom surface of casing is provided with mobile roller.
As a kind of embodiment of the present utility model, described mobile roller is Universal castor.
As a kind of improvement of the present utility model, described flowline is provided with an oil filter.
The embodiment recommended as this utility model, described radiator fan control the defeated of end and a host computer
Going out port to connect, the input port of host computer is connected with temperature sensor and differential pressure pickup respectively.
As a kind of improvement of the present utility model, the control end of radiator fan is through the output of a converter Yu host computer
Port connects.
As a kind of embodiment of the present utility model, described host computer is PLC.
As a kind of improvement of the present utility model, described host computer and converter are commonly connected to a display
On.
Compared with prior art, this utility model has the advantage that
This utility model can prevent hydraulic pressure system for hydraulic system offer heat sinking function when carrying out rudder face and controlling to test
Unite overheated；And can quickly move, it is simple to operator use and carry；Use the mode of Based Intelligent Control,
In real time the hydraulic system state when carrying out rudder face and controlling test can be monitored in real time, and be automatically adjusted scattered
Hot speed, is equipped with special status displays simultaneously and shows the state of hydraulic system in real time；This utility model structure
Succinctly, low cost, can effectively reduce the cost of aircraft maintenance and test.
Accompanying drawing explanation
By embodiment, the utility model is described in further detail below in conjunction with the accompanying drawings.
Fig. 1 is schematic diagram of the present utility model；
Fig. 2 is the connection diagram that this utility model controls assembly.
In figure: 1-casing, 2-through hole, 3-radiator fan, 4-radiator, 5-oil inlet pipe, 6-flowline, 7-
Oil filter, 8-Universal castor, 9-PLC, 10-temperature sensor, 11-differential pressure pickup, 12-converter, 13-
Display.
Detailed description of the invention
Aircraft external hydraulic pump cooler as illustrated in fig. 1 and 2 is embodiment of the present utility model, including a case
Body 1, the end face of casing 1 has through hole 2, and the top of casing 1 is fixed with a radiator fan 3, in casing
Be fixed with a radiator 4 in the lower section of radiator fan 3, the entrance of radiator 4 is provided with oil inlet pipe 5, outlet
Being provided with flowline 6, the bottom surface of casing 1 is provided with Universal castor 8.On the basis of the above, the present embodiment goes out
Oil pipe 6 is provided with an oil filter 7, and heat eliminating medium can be avoided to pollute aircraft hydraulic oil.And at the present embodiment
In, in order to reach the purpose of Based Intelligent Control, radiator fan 3 control defeated through a converter 12 and PLC9 of end
Going out port to connect, the input port of PLC9 is connected with temperature sensor 10 and differential pressure pickup 11 respectively,
Can be monitored the parameter of hydraulic system in real time by temperature sensor 10 and differential pressure pickup 11, PLC is according to liquid
The real-time parameter of pressure system is automatically adjusted the wind speed of radiator fan.PLC9 and converter 12 are commonly connected to one and show
Showing on device 13, the record not only having met aircraft work card requires but also can show early warning situation, facilitates direct inquiry system
The parameters of work, is also used for detecting the duty of hydraulic system, reacts maintenance needs, make internal system
Clean situation meets the requirement of aircraft maintenance.
When actually used, by the oil-out phase of the oil inlet pipe of embodiment radiator with hydraulic system aircraft hydraulic oil
Connect, flowline is connected with the oil-in of hydraulic system aircraft hydraulic oil, so that this utility model heat radiation
Device is connected with hydraulic system.Then start radiator fan radiator to be dispelled the heat, due to radiator and hydraulic pressure
System becomes a blood circulation, after hydraulic oil is lowered the temperature in radiator, back flows back in hydraulic system also
Hydraulic system is lowered the temperature, above procedure reciprocation cycle, utilize PLC according to temperature sensor and pressure difference sensing simultaneously
Device obtains parameter and regulates the speed of radiator fan, thus reaches the accurate control to aircraft hydraulic oil temperature requirements
System.
Above-described embodiment of the present utility model is not the restriction to this utility model protection domain, this utility model
Embodiment be not limited to this, all this kind is according to foregoing of the present utility model, common according to this area
Technological know-how and customary means, without departing under this utility model above-mentioned basic fundamental thought premise, to this practicality
The amendment of other various ways that novel said structure is made, replace or change, all should fall of the present utility model
Within protection domain.
Claims (7)
1. an aircraft external hydraulic pump cooler, including a casing, it is characterised in that: the end face of casing has
Through hole, the top of casing is fixed with a radiator fan, is fixed with one in the lower section of radiator fan and dissipates in casing
Hot device, the entrance of radiator is provided with oil inlet pipe, outlet is provided with flowline, and the bottom surface of casing is provided with mobile roller.
Aircraft external hydraulic pump cooler the most according to claim 1, it is characterised in that: described movement
Roller is Universal castor.
Aircraft external hydraulic pump cooler the most according to claim 1, it is characterised in that: described is fuel-displaced
Pipe is provided with an oil filter.
4. according to the arbitrary described aircraft external hydraulic pump cooler of claims 1 to 3, it is characterised in that: institute
State the output port connection controlling end and a host computer of radiator fan, the input port of host computer respectively with temperature
Sensor is connected with differential pressure pickup.
Aircraft external hydraulic pump cooler the most according to claim 4, it is characterised in that: radiator fan
Control end to be connected with the output port of host computer through a converter.
Aircraft external hydraulic pump cooler the most according to claim 5, it is characterised in that: described is upper
Machine is PLC.
Aircraft external hydraulic pump cooler the most according to claim 6, it is characterised in that: described is upper
Machine and converter are commonly connected on a display.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620203816.9U CN205478682U (en) | 2016-03-16 | 2016-03-16 | External hydraulic pump cooler of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620203816.9U CN205478682U (en) | 2016-03-16 | 2016-03-16 | External hydraulic pump cooler of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205478682U true CN205478682U (en) | 2016-08-17 |
Family
ID=56654158
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620203816.9U Active CN205478682U (en) | 2016-03-16 | 2016-03-16 | External hydraulic pump cooler of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205478682U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109322879A (en) * | 2018-12-01 | 2019-02-12 | 江苏汉东机械有限公司 | A kind of hydraulic machinery radiator |
-
2016
- 2016-03-16 CN CN201620203816.9U patent/CN205478682U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109322879A (en) * | 2018-12-01 | 2019-02-12 | 江苏汉东机械有限公司 | A kind of hydraulic machinery radiator |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |