CN2584516Y - Hydraulic oil pump vehicle for helicopter - Google Patents
Hydraulic oil pump vehicle for helicopter Download PDFInfo
- Publication number
- CN2584516Y CN2584516Y CN02280814U CN02280814U CN2584516Y CN 2584516 Y CN2584516 Y CN 2584516Y CN 02280814 U CN02280814 U CN 02280814U CN 02280814 U CN02280814 U CN 02280814U CN 2584516 Y CN2584516 Y CN 2584516Y
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- hydraulic
- helicopter
- sealing joint
- self
- oil
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Abstract
The utility model relates to a hydraulic oil pump vehicle for a helicopter, which mainly comprises a go-anywhere vehicle and a special loading part. The hydraulic oil pump vehicle is characterized in that the special loading part is composed of a power device, an instrument controller, a transmission device, a hydraulic device, an electric control device and a structural member of a vehicle body, wherein the power device provides power shared by the vehicle and the special loading part, the power device is connected with a power taking device, and the hydraulic device is composed of two independent hydraulic devices. The hydraulic oil pump vehicle has the characteristic that three kinds of pressure and flow rate can be simultaneously produced to be used for helicopters with different models simultaneously. The utility model has the advantages of compact design and structure, small size, transportable transition of the helicopters, rainproof capability, windproof capability, sandfroof capability and fireproof capability.
Description
Technical field: the utility model relates to a kind of helicopter hydraulic oil pump tender, is the hydraulic efficiency equipment for helicopter maintenance and detection use, exactly is a kind of helicopter ground handling equipment.
Background technology: also do not have a kind of hydraulic oil pump tender that helicopter uses that is specifically designed in the prior art.The hydraulic oil pump tender that helicopter uses is with being used for helicopter after the repacking of aircraft hydraulic oil pump truck.Its pressure of the hydraulic oil pump tender of this structure, flow are bigger than normal, have only individual event pressure, and volume and weight are big, can't realize helicopter transition transportation.
Summary of the invention: the purpose of this utility model is at the deficiencies in the prior art, and provides a kind of self-propelled hydraulic oil pump tender that adopts the cross-country car repacking to people, specializes in helicopter and uses.This hydraulic oil pump tender power adopts electrical motor, is the metal case structure, is trailing type small-sized hydraulic hydrant cart.For achieving the above object, the utility model adopts following technical proposals: the helicopter hydraulic oil pump tender mainly comprises cross-country car and special dress two large divisions.Special dress part is handled (2), driving device (3), hydraulic efficiency gear (4), electrical control gear (5) and body construction part (6) by engine installation (1), instrument and is formed.Engine installation (1) is automobile and special dress partial common power, and engine installation (1) connects with power takeoff (7), and its takeoff output passes to special dress part by the power takeoff (7) that is connected on the engine installation driving engine.Driving device (3) is made up of change speed gear box (8), transmission shaft (9), prerotator (10).One end of transmission shaft (9) is connected by the mouth of unitor with change speed gear box (8); The other end is connected with prerotator (10), Hydraulic Pump (11), bidentate wheel Hydraulic Pump (12) respectively.Hydraulic efficiency gear (4) by two independently hydraulic efficiency gear form, its (one) device is made up of from end socket (13), oil radiator assembly (14), shutoff valve (15), oil filter (16), flow transmitter (22), bidentate wheel Hydraulic Pump (12), oil filter assembly (17), flexible pipe (18), high pressure self-sealing joint (19), (20), pressure regulating valve (21) etc. low pressure.Its concrete connecting relation is to realize forming closed hydraulic circuit with helicopter hydraulic system.Low pressure self-sealing joint (13), high pressure self-sealing joint (19), (20) are docked composition hydraulic efficiency pressure system C/LOOP respectively with self-sealing joint on the helicopter machine.Low pressure self-sealing joint (13) links to each other with oil radiator assembly (14), shutoff valve (15), oil filter (16) with conduit by low pressure hose, and be divided into two-way and link to each other with duplex geared pump (12) through two groups of conduits with two flow transmitters (22) respectively, be connected with oil filter assembly (17), flexible pipe (18), high pressure self-sealing joint (19), (20) respectively again.Pressure regulating valve (21) is connected in parallel on respectively between duplex geared pump (12) and the oil filter assembly (17).Its (two) device is made up of the self-styled valve joint of low pressure (23), low pressure hose (24), oil radiator assembly (14), hydraulic efficiency pressure switch (25), oil filter (26), flow transmitter (25), Hydraulic Pump (11), oil filter assembly (29), high pressure hose (30), high pressure self-sealing joint (31), valve module of voltage regulation parts such as (28).Its concrete connecting relation is to realize forming the hydraulic pressure C/LOOP with single hydraulic efficiency pressure system helicopter.Low pressure self-sealing joint (23), high pressure self-sealing joint (31) are docked with the top connection of helicopter machine respectively.Low pressure self-sealing joint (23) is connected with each other by conduit tube component with low pressure hose (24), oil radiator assembly (14), hydraulic efficiency pressure switch (25), oil filter (26), flow transmitter (25), link to each other with Hydraulic Pump (11) again, after link to each other with oil filter assembly (29), high pressure hose (30), high pressure self-sealing joint (31) again.Valve module of voltage regulation (28) is connected in parallel between Hydraulic Pump (11) and the oil filter assembly (29).
Characteristics of the present utility model are: (1) hydraulic efficiency gear is made of two parts, can produce three kinds of different pressure, flow simultaneously, provides the different model helicopter to use simultaneously; (2) project organization compactness, volume is little, and helicopter can transport transition; (3) have rainproof, windproof sand, fire resistance property.
Description of drawings:
Fig. 1 is a structural representation of the present utility model.
Fig. 2 is a hydraulic device structure scheme drawing among Fig. 1.
Fig. 3 is a transmission structures scheme drawing among Fig. 1.
Specific embodiment:
With reference to Fig. 1,2,3, the helicopter hydraulic oil pump tender mainly comprises cross-country car and special dress two large divisions.Special dress part is made up of engine installation 1, instrument manipulation 2, driving device 3, hydraulic efficiency gear 4, electrical control gear 5 and body construction part 6.Engine installation 1 is automobile and special dress partial common power, and engine installation 1 connects with power takeoff 7, and its takeoff output passes to special dress part by the power takeoff 7 that is connected on the engine installation driving engine.During running car, power takeoff 7 must place neutral gear.Driving device 3 is made up of change speed gear box 8, transmission shaft 9, prerotator 10.One end of transmission shaft 9 is connected by the mouth of unitor with change speed gear box 8; The other end is connected with prerotator 10, Hydraulic Pump 11, bidentate wheel Hydraulic Pump 12 respectively.Its power is to transmit like this: the power of driving engine 1 is transferred to change speed gear box 8 through power takeoff 7, converts three kinds of rotating speeds to by change speed gear box 8 again, passes to prerotator 10 and Hydraulic Pump 11, bidentate wheel Hydraulic Pump 12 respectively, satisfies the power requirement of hydraulic pressure pump truck.Hydraulic efficiency gear 4 by two independently hydraulic efficiency gear form, its (one) device is made up of from end socket 13, oil radiator assembly 14, shutoff valve 15, oil filter 16, flow transmitter 22, bidentate wheel Hydraulic Pump 12, oil filter assembly 17, flexible pipe 18, high pressure self-sealing joint 19,20, pressure regulating valve 21 etc. low pressure.Its concrete connecting relation is to realize forming closed hydraulic circuit with helicopter hydraulic system.Low pressure self-sealing joint 13, high pressure self-sealing joint 19,20 are docked composition hydraulic efficiency pressure system C/LOOP respectively with self-sealing joint on the helicopter machine.Low pressure self-sealing joint 13 links to each other with oil radiator assembly 14, shutoff valve 15, oil filter 16 with conduit by low pressure hose, and be divided into two-way and link to each other with duplex geared pump 12 (this gear type pump can form two kinds of pressure) through two groups of conduits with two flow transmitters 22 respectively, be connected with oil filter assembly 17, flexible pipe 18, high pressure self-sealing joint 19,20 respectively again.Pressure regulating valve 21 is connected in parallel on respectively between duplex geared pump 12 and the oil filter assembly 17.Its (two) device is made up of parts such as the self-styled valve joint 23 of low pressure, low pressure hose 24, oil radiator assembly 14, hydraulic efficiency pressure switch 25, oil filter 26, flow transmitter 25, Hydraulic Pump 11, oil filter assembly 29, high pressure hose 30, high pressure self-sealing joint 31, valve module of voltage regulation 28.Its concrete connecting relation is to realize forming the hydraulic pressure C/LOOP with single hydraulic efficiency pressure system helicopter.Low pressure self-sealing joint 23, high pressure self-sealing joint 31 are docked with the top connection of helicopter machine respectively.Low pressure self-sealing joint 23 and low pressure hose 24, oil radiator assembly 14, hydraulic efficiency pressure switch 25, oil filter 26, flow transmitter 25 are connected with each other by conduit tube component, link to each other with Hydraulic Pump 11 again, link to each other with oil filter assembly 29, high pressure hose 30, high pressure self-sealing joint 31 again.Valve module of voltage regulation 28 is connected in parallel between Hydraulic Pump 11 and the oil filter assembly 29.
The manipulation of hydrant cart is used
1, preparation and the inspection before driving: preparation before the hydrant cart work and inspection be related to each system of hydrant cart can be normally, the important step of safety, reliable operation, especially to long car of new car and standing time, more should cause enough attention, to avoid fault, cause damage.(1) automobile is conventional prepares; (2) electrical control and indicating instrument, the contact of each master cock is reliable, and lead should be firm with being connected of connection terminal, no sealing-off, the hidden danger of the short trouble that do not have.Various indicating instruments are working properly, and keep good class of accuracy; (3) driving system; (4) inspection of hydraulic efficiency pressure system is to use the important step of hydrant cart, the major part tangible mechanical damage that do not have, and each metal tubes joint is answered non-loosening, oil impregnate phenomenon.Each compression indicator, flow gauge, temperature gage are answered indicating correct, and oil radiator exit shutoff valve is in full-gear, and the operating fluid in the hydraulic efficiency pressure system should be identical with the hydraulic fluid trade mark on the helicopter, and system and fuel tank are filled with operating fluid.The operational phase that can enter hydrant cart after preparation before hydrant cart has carried out driving and the inspection.
During use, (1) with hydrant cart be placed on the suitable position of aircraft on, rubber tube is taken out at the back door of opening car, opens fuel tank air cock and system deflation switch.With force pump to system's repairing, see the relief port place fuel-displaced be the shutdown system air cock, get final product when oil suction compression indicator indication reaches 0.05Mpa, after system is full of oil, close the fuel tank air cock.(2) screw off cover of dust and machine top connection blanking cover on the self-sealing joint, clean the dirt of joint, behind the airing corresponding joints on car self-sealing joint and the machine is connected with the gasoline of cleaning.(3) open unloader valve in the corresponding system of two driver seat rear middle part.(4) start automotive engine, make the part-time case handle place Neutral Position, gear change hand lever places " one grade " gear.When power-transfer clutch is in semi-linkage, dial the power takeoff handle backward, make power takeoff hang up properly gear, make gear change hand lever place " 4 grades " gear then.(5) adjust engine speed with " manual accelerator ", engine speed is being transferred under the 1000-1500r/min state running after 2-3 minute, check each system health, treat that all can transfer to rated speed of rotation to rotating speed after normal, at this moment can help the hydraulic efficiency pressure system voltage supply to detect debugging or cleaning to aircraft is main and auxiliary.When speed gage is indicated: during n=3000r/min, its main system flow should be 6L/min; The ancillary system flow should be 18L/min.(6) if debug and check the main and auxiliary hydraulic efficiency pressure system that helps of helicopter simultaneously, the unloader valve that at this moment need close main system and auxilliary system simultaneously.(7) if only need two one of them systems of hydraulic efficiency pressure system of debugging and inspection helicopter, at this moment only close corresponding unloader valve in the hydrant cart hydraulic efficiency pressure system, another unloader valve must be located full-gear.(8) after hydrant cart was finished plane hydraulic system detection, debugging or cleaning: a, open the unloader valve of work system, shutdown was stopped.B, the back of stopping push neutral position to the power takeoff handle forward, and the part-time case handle is suspended to the 2H gear.C, PTO Power Take Off switch unload the self-sealing joint that docks with aircraft, and first-class cover of dust is placed on the rubber tube volume in the car, shuts on the car each.
Claims (4)
1, helicopter hydraulic oil pump tender, mainly comprise cross-country car and special dress two large divisions, it is characterized in that: special dress part is handled (2), driving device (3), hydraulic efficiency gear (4), electrical control gear (5) and body construction part (6) by engine installation (1), instrument and is formed.
2, helicopter hydraulic oil pump tender according to claim 1 is characterized in that: described engine installation (1) is automobile and special dress partial common power, and engine installation (1) connects with power takeoff (7).
3, helicopter hydraulic oil pump tender according to claim 1, it is characterized in that: described driving device (3) is made up of change speed gear box (8), transmission shaft (9), prerotator (10), and an end of transmission shaft (9) is connected by the mouth of unitor with change speed gear box (8); The other end is connected with prerotator (10), Hydraulic Pump (11), bidentate wheel Hydraulic Pump (12) respectively.
4, helicopter hydraulic oil pump tender according to claim 1, it is characterized in that: described hydraulic efficiency gear (4) by two independently hydraulic efficiency gear form, its (one) installs by low pressure from end socket (13), oil radiator assembly (14), shutoff valve (15), oil filter (16), flow transmitter (22), bidentate wheel Hydraulic Pump (12), oil filter assembly (17), flexible pipe (18), high pressure self-sealing joint (19), (20), pressure regulating valve (21) is formed, its concrete connecting relation is to realize forming closed hydraulic circuit with helicopter hydraulic system, with low pressure self-sealing joint (13), high pressure self-sealing joint (19), (20) dock composition hydraulic efficiency pressure system C/LOOP respectively with self-sealing joint on the helicopter machine, low pressure self-sealing joint (13) is by low pressure hose and conduit and oil radiator assembly (14), shutoff valve (15), oil filter (16) links to each other, and be divided into two-way and link to each other with duplex geared pump (12) through two groups of conduits with two flow transmitters (22) respectively, again respectively with oil filter assembly (17), flexible pipe (18), high pressure self-sealing joint (19), (20) connect; Pressure regulating valve (21) is connected in parallel on respectively between duplex geared pump (12) and the oil filter assembly (17), its (two) device is by the self-styled valve joint of low pressure (23), low pressure hose (24), oil radiator assembly (14), hydraulic efficiency pressure switch (25), oil filter (26), flow transmitter (25), Hydraulic Pump (11), oil filter assembly (29), high pressure hose (30), high pressure self-sealing joint (31), valve module of voltage regulation parts such as (28) are formed, its concrete connecting relation is to realize forming the hydraulic pressure C/LOOP with single hydraulic efficiency pressure system helicopter, with low pressure self-sealing joint (23), high pressure self-sealing joint (31) docks with the top connection of helicopter machine respectively, low pressure self-sealing joint (23) and low pressure hose (24), oil radiator assembly (14), hydraulic efficiency pressure switch (25), oil filter (26), flow transmitter (25) is connected with each other by conduit tube component, link to each other with Hydraulic Pump (11) again, again with oil filter assembly (29), high pressure hose (30), high pressure self-sealing joint (31) links to each other, and valve module of voltage regulation (28) is connected in parallel between Hydraulic Pump (11) and the oil filter assembly (29).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN02280814U CN2584516Y (en) | 2002-10-31 | 2002-10-31 | Hydraulic oil pump vehicle for helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN02280814U CN2584516Y (en) | 2002-10-31 | 2002-10-31 | Hydraulic oil pump vehicle for helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2584516Y true CN2584516Y (en) | 2003-11-05 |
Family
ID=33743431
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN02280814U Expired - Fee Related CN2584516Y (en) | 2002-10-31 | 2002-10-31 | Hydraulic oil pump vehicle for helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2584516Y (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105059100A (en) * | 2015-07-29 | 2015-11-18 | 中国嘉陵工业股份有限公司（集团） | Light all-terrain vehicle with novel overall layout |
-
2002
- 2002-10-31 CN CN02280814U patent/CN2584516Y/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105059100A (en) * | 2015-07-29 | 2015-11-18 | 中国嘉陵工业股份有限公司（集团） | Light all-terrain vehicle with novel overall layout |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20031105 Termination date: 20101031 |