CN108591140A - The load test stand of aviation hydraulic oil pump vehicle - Google Patents

The load test stand of aviation hydraulic oil pump vehicle Download PDF

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Publication number
CN108591140A
CN108591140A CN201810381371.7A CN201810381371A CN108591140A CN 108591140 A CN108591140 A CN 108591140A CN 201810381371 A CN201810381371 A CN 201810381371A CN 108591140 A CN108591140 A CN 108591140A
Authority
CN
China
Prior art keywords
pressure
fuel tank
low
oil pump
pressurized fuel
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201810381371.7A
Other languages
Chinese (zh)
Inventor
朱忠华
胡之兵
谢森
张乾
路祥生
刘伟
王珊珊
王耀民
周峰
季常宁
吕倩
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
PEOPLE'S LIBERATION ARMY AIR FORCE AEROSPACE GROUND EQUIPMENT REPAIR SHOP IN NANJING
Original Assignee
PEOPLE'S LIBERATION ARMY AIR FORCE AEROSPACE GROUND EQUIPMENT REPAIR SHOP IN NANJING
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by PEOPLE'S LIBERATION ARMY AIR FORCE AEROSPACE GROUND EQUIPMENT REPAIR SHOP IN NANJING filed Critical PEOPLE'S LIBERATION ARMY AIR FORCE AEROSPACE GROUND EQUIPMENT REPAIR SHOP IN NANJING
Priority to CN201810381371.7A priority Critical patent/CN108591140A/en
Publication of CN108591140A publication Critical patent/CN108591140A/en
Pending legal-status Critical Current

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15BSYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B11/00Servomotor systems without provision for follow-up action; Circuits therefor
    • F15B11/02Systems essentially incorporating special features for controlling the speed or actuating force of an output member
    • F15B11/028Systems essentially incorporating special features for controlling the speed or actuating force of an output member for controlling the actuating force
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15BSYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B21/00Common features of fluid actuator systems; Fluid-pressure actuator systems or details thereof, not covered by any other group of this subclass
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01DMEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
    • G01D21/00Measuring or testing not otherwise provided for
    • G01D21/02Measuring two or more variables by means not covered by a single other subclass
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15BSYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2211/00Circuits for servomotor systems
    • F15B2211/20Fluid pressure source, e.g. accumulator or variable axial piston pump
    • F15B2211/21Systems with pressure sources other than pumps, e.g. with a pyrotechnical charge

Abstract

The invention discloses a kind of load test stands of aviation hydraulic oil pump vehicle, the gas pressurization system being connected including pressurized fuel tank and with pressurized fuel tank, high pressure connection line, low-pressure connection tube road, high-pressure connecting pipe road is equipped with concatenated proportional pressure control valve, flowmeter, high pressure oily filter, high-pressure manometer, valve on particulate pollutant detector and high-pressure unit, high pressure connection line is connected to by proportional pressure control valve on pressurized fuel tank, low-pressure connection tube road is equipped with concatenated temperature sensor, valve on low pressure gauge and low-pressure machine, low-pressure connection tube road is connected to by temperature sensor on pressurized fuel tank, the gas pressurization system is connected to by charge valve on pressurized fuel tank;The aviation hydraulic oil pump vehicle load test stand of the present invention is multiple functional, dependable performance, is mainly used for simulating the dynamic load of plane hydraulic system, facilitates the detection of aviation hydraulic oil pump vehicle performance indicator, improve the efficiency of aviation hydraulic oil pump vehicle maintenance maintenance.

Description

The load test stand of aviation hydraulic oil pump vehicle
Technical field
The present invention relates to the ground handling equipment field of plane hydraulic system more particularly to a kind of aviation hydraulic oil pump vehicles Load test stand.
Background technology
Currently, the hydraulic system performance checking of two, three generations's aircraft relies primarily on aviation hydraulic oil pump vehicle realization;Airplane hydraulic pressure Requirement of the system to Specifeca tion speeifications such as hydrant cart output pressure, flow, temperature, Oil Qualities is extremely stringent;Once oil pump The oil supply system of vehicle breaks down, and will have a direct impact on the operation of plane hydraulic system, thus hydrant cart worked before need Carry out multiple detection and maintenance work.
However, during aviation hydraulic oil pump vehicle use, maintenance and repair, set due to lacking advanced performance detection Standby, common detection device is difficult the working performance progress complete detection to aviation hydraulic oil pump vehicle, therefore to its confirming performance Can only by with plane hydraulic system On-line measurement, such detection method not only occupies the guarantee time of aircraft, but also when boat When empty hydraulic oil pump tender breaks down, the plane hydraulic system of detection can be damaged, there are some potential safety problems, oil supply Pump truck maintenance brings more inconvenience.
Invention content
In view of the above problems, present invention aims at provide one kind to simulate plane hydraulic system work, energy Enough detect the load test stand of aviation hydraulic oil pump vehicle performance indicator.
In order to achieve the above object, the technical solution adopted by the present invention is as follows:A kind of load examination of aviation hydraulic oil pump vehicle Platform is tested, the load test stand includes that pressurized fuel tank and the gas pressurization system being connected with pressurized fuel tank, high pressure are connect Pipeline, low-pressure connection tube road, high-pressure connecting pipe road are equipped with concatenated proportional pressure control valve, and flowmeter, high pressure oily filter are high Valve on pressure pressure table, particulate pollutant detector and high-pressure unit, high pressure connection line are connected to supercharging by proportional pressure control valve On fuel tank, low-pressure connection tube road is equipped with valve in concatenated temperature sensor, low pressure gauge and low-pressure machine, low pressure Connecting line is connected to by temperature sensor on pressurized fuel tank, and the gas pressurization system is connected to supercharging by charge valve On fuel tank, the gas pressurization system is made of nitrogen cylinder, gas-charging connection, check valve and pressure reducing valve, the nitrogen cylinder It is connected on charge valve by pressure reducing valve, the pressure reducing valve is equipped with the gas-charging connection and check valve in parallel with nitrogen cylinder.
High pressure connection line of the present invention is movably connected in the height of aviation hydraulic oil pump vehicle by valve on high-pressure unit It presses on output pipe, the low pressure that the low-pressure connection tube road is connected to aviation hydraulic oil pump vehicle by valve in low-pressure machine exports On pipeline, when the present apparatus simulates air line, the pressure in pressurized fuel tank, aircraft fluid are controlled by gas pressurization system Pump truck is connected by low pressure output pipe oil return by high pressure connection line and low pressure by high pressure output line output hydraulic pressure oil It takes over the oil product that the detecting instrument of road exports aviation hydraulic oil pump vehicle to be detected, finds the operation of high pressure oil pump truck in time Whether break down.
The middle part of pressurized fuel tank of the present invention is equipped with partition board, and pressurized fuel tank is separated into two mutually independent increasings by partition board Pressure area:IIth area of Ith area of hydraulic pressure and hydraulic pressure;Detection zone is formed by multiple anallobars, it can be simultaneously to multiple aviation hydraulic oil pump vehicles Detecting system be detected.
Pressurized fuel tank of the present invention is equipped with two groups of high pressure connection lines and low-pressure connection tube road, one group of high pressure connection Pipeline, low-pressure connection tube road are connected to form I system of hydraulic pressure with Ith area of hydraulic pressure, another group of high pressure connection line, low-pressure connection tube road It is connected to form II system of hydraulic pressure with IIth area of hydraulic pressure;There are two hydraulic system, a use for usual aviation hydraulic oil pump vehicle tool In normal use, one, for spare, but when being detected using the present apparatus, needs simultaneously to carry out two groups of hydraulic systems same When detect, ensure hydraulic oil pump tender on all hydraulic system operation stability.
Gas pressurization system of the present invention is separately connected Ith area of hydraulic pressure and hydraulic pressure II by two charge valves in parallel Area;When there are when the detection zone of multiple separations, pressure control is carried out respectively by charge valve in parallel in pressurized fuel tank.
The top of pressurized fuel tank of the present invention is equipped with Pneumatic safety valve and vent valve, and the bottom of pressurized fuel tank, which is equipped with, drains the oil Plug;Pneumatic safety valve in fuel tank when superpressure for being vented, and vent valve is used in giving pressurized fuel tank pressure release, and plug of draining the oil is for putting Hydraulic oil in empty pressurized fuel tank.
Single high pressure connection line forms one group with single low-pressure connection tube road and connect on pressurized fuel tank of the present invention Pipeline, the quantity of anallobar and the group number on pressurized fuel tank upper connector road match in the pressurized fuel tank;Due to producing There are the needs of multiple hydraulic oil pump tenders to be detected in journey, and the present apparatus passes through multigroup connecting tube for being connect with a pressurized fuel tank Road completes to detect while multiple hydraulic oil pump tenders, and work efficiency is high.
The advantage of the invention is that:The device of the invention is simple in structure, passes through the gas boosting being connected with pressurized fuel tank Plane hydraulic system is simulated on system, high pressure connection line, low-pressure connection tube road.On high pressure connection line and low-pressure connection tube road Pass through the solid particle pollution of hydraulic oil in oil contamination degree detector real time on-line monitoring aviation hydraulic oil pump vehicle hydraulic system Degree;The output pressure of aviation hydraulic oil pump vehicle is detected by high-pressure manometer;Filter aviation hydraulic oil pump vehicle is filtered by high pressure oil Interior hydraulic oil;The output flow of aviation hydraulic oil pump vehicle is detected by flowmeter;Change system pressure by proportional pressure control valve, Realize the simulation of plane hydraulic system dynamic load;It is used to detect the oil return pressure of aviation hydraulic oil pump vehicle by low pressure gauge Power;Hydraulic fluid temperature in aviation hydraulic oil pump vehicle hydraulic system is detected by temperature sensor.
The aviation hydraulic oil pump vehicle load test stand of the present invention is multiple functional, and dependable performance is changed by proportional pressure control valve System pressure realizes the simulation of plane hydraulic system dynamic load, facilitates the detection of aviation hydraulic oil pump vehicle performance indicator, carry The high efficiency of aviation hydraulic oil pump vehicle maintenance maintenance.
Description of the drawings
Fig. 1 is the aviation hydraulic oil pump vehicle load test stand schematic device of the present invention.
Wherein, valve on 1 high-pressure unit, 2 oil contamination degree detectors, 3 high-pressure manometers, 4 high pressure oily filters, 5 flows Meter, 6 proportional pressure control valves, valve in 7 low-pressure machines, 8 low pressure gauges, 9 temperature sensors, 10 drain the oil plug, and 11 is pneumatic Safety valve, 12 charge valves, 13 second depressurized valves, 14 one-level pressure relief valves, 15 vent valves, 16 pressurized fuel tanks, 17 is pneumatic single To valve, 18 gas-charging connections, 19 nitrogen cylinders.
Specific implementation mode
The present invention is described in further detail with specific implementation mode for explanation below in conjunction with the accompanying drawings.
Embodiment 1:A kind of load test stand of aviation hydraulic oil pump vehicle as shown in Figure 1, the load test stand packet Include pressurized fuel tank 16 and the gas pressurization system being connected with pressurized fuel tank 16, high pressure connection line, low-pressure connection tube road, institute The high-pressure connecting pipe road stated is equipped with concatenated proportional pressure control valve 6, and flowmeter 5, high pressure oily filter 4, high-pressure manometer 3, particle are dirty Valve 1 on analyte detection instrument 2 and high-pressure unit is contaminated, high pressure connection line is connected to by proportional pressure control valve 6 16 on pressurized fuel tank, described Low-pressure connection tube road be equipped with concatenated temperature sensor 9, valve 7 in low pressure gauge 8 and low-pressure machine, low-pressure connection tube road It is connected on pressurized fuel tank 16 by temperature sensor 9, the gas pressurization system is connected to pressurised oil by charge valve 12 On case 16, the gas pressurization system is made of nitrogen cylinder 19, gas-charging connection 18, check valve 17 and pressure reducing valve 13,14, institute The nitrogen cylinder 19 stated is connected to by pressure reducing valve 13,14 on charge valve, and the pressure reducing valve 13 is equipped in parallel with nitrogen cylinder 19 Gas-charging connection 18 and check valve 17.
Embodiment 2:As shown in Figure 1, high pressure connection line is movably connected in hydraulic air oil pump by valve on high-pressure unit 1 The high-pressure output tube road of vehicle, the low-pressure connection tube road is connected to aviation hydraulic oil pump vehicle by valve in low-pressure machine 7 On low pressure output pipe, when the present apparatus simulates air line, the pressure in pressurized fuel tank 16 is controlled by gas pressurization system, Aviation hydraulic oil pump vehicle, by low pressure output pipe oil return, passes through high-pressure connecting pipe by high pressure output line output hydraulic pressure oil The oil product that the detecting instrument of road and low-pressure connection tube road exports aviation hydraulic oil pump vehicle is detected, and finds high pressure oil in time Whether the operation of pump truck breaks down.
Embodiment 3:As shown in Figure 1, the middle part of pressurized fuel tank 16 is equipped with partition board, pressurized fuel tank is separated into two phases by partition board Mutual independent anallobar:IIth area of Ith area of hydraulic pressure and hydraulic pressure;Detection zone is formed by multiple anallobars, it can be simultaneously to multiple aviations The detecting system of hydraulic oil pump tender is detected.
Embodiment 4:As shown in Figure 1, pressurized fuel tank 16 be equipped with two groups of high pressure connection lines and low-pressure connection tube road, one group High pressure connection line, low-pressure connection tube road are connected to form I system of hydraulic pressure with Ith area of hydraulic pressure, another group of high pressure connection line, low pressure Connecting line is connected to form II system of hydraulic pressure with IIth area of hydraulic pressure;There are two hydraulic pressure systems for usual aviation hydraulic oil pump vehicle tool System, one is used for normal use, and one, for spare, but when being detected using the present apparatus, is needed simultaneously to two groups of hydraulic pressure System is carried out while being detected, and ensures the stability of all hydraulic system operation on hydraulic oil pump tender.
Embodiment 5:As shown in Figure 1, gas pressurization system by two charge valves 12 in parallel be separately connected Ith area of hydraulic pressure and IIth area of hydraulic pressure;When there are when the detection zone of multiple separations, air pressure control is carried out respectively by charge valve in parallel in pressurized fuel tank 16 System.
Embodiment 6:As shown in Figure 1, the top of pressurized fuel tank 16 is equipped with Pneumatic safety valve 11 and vent valve 15, pressurized fuel tank 16 bottom is equipped with plug 10 of draining the oil;For being vented when superpressure in fuel tank 16, vent valve 15 is used in increasing Pneumatic safety valve 11 16 pressure release of pressure oil case, the hydraulic oil that plug 10 of draining the oil is used to be vented in pressurized fuel tank 16.
Embodiment 7:As shown in Figure 1, single high pressure connection line is formed with single low-pressure connection tube road on pressurized fuel tank 16 One group of connecting line, the quantity of anallobar and the group number on 16 upper connector road of pressurized fuel tank match in the pressurized fuel tank 16; Needs due to there are multiple hydraulic oil pump tenders in process of production are detected, and the present apparatus with a pressurized fuel tank 16 by connecting The multigroup connecting line connect is completed to detect while multiple hydraulic oil pump tenders, and work efficiency is high.
Embodiment 8:Technical solution simulation aircraft using the present invention carries out the operational instances of On-line measurement.
(1) hydraulic air there are into pump truck hydraulic system high and low pressure banjo fixing butt jointing and hydraulic pressure I, II system in load test stand Valve docks on high and low press;
(2) 19 upper switch of nitrogen cylinder is opened, adjusts one-level pressure relief valve 14, second depressurized valve 13 successively, opens charge valve 12, Xiang Zeng It is pressurized to 0.35MPa in pressure oil case 16;
(3) start aviation hydraulic oil pump vehicle, aviation hydraulic oil pump vehicle operating pressure is set as 26MPa, flow set 90L/ min;
(4) proportional pressure control valve 6 is adjusted to be down to after 10MPa load pressure by 26MPa in 10S and be restored to 26MPa, flow at this time Amount is 0,10S is then run, as a work period;
(5) in operation observe aviation hydraulic oil pump vehicle on pressure gauge, flowmeter, dustiness detector instruction parameter Whether the instruction parameter with corresponding pressure gauge, flowmeter, dustiness detector in load test stand such as exists in tolerance In tolerance, then it can determine whether that aviation hydraulic oil pump vehicle is normal;
(6) aviation hydraulic oil pump vehicle is closed;
(7) vent valve 15 is opened, gas in pressurized fuel tank 16 is discharged;
(8) dismantle hydraulic air have in pump truck hydraulic system high and low pressure banjo fixing butt jointing and load test stand hydraulic pressure I, II system it is high, Valve in low-pressure machine.
It should be noted that above-mentioned is only presently preferred embodiments of the present invention, protection model not for the purpose of limiting the invention It encloses, the arbitrary combination made on the basis of the above embodiments or equivalents all belong to the scope of protection of the present invention.

Claims (7)

1. a kind of load test stand of aviation hydraulic oil pump vehicle, which is characterized in that the load test stand includes pressurized fuel tank And be connected with pressurized fuel tank gas pressurization system, high pressure connection line, low-pressure connection tube road, the high-pressure connecting pipe Road is equipped with concatenated proportional pressure control valve, flowmeter, high pressure oily filter, high-pressure manometer, particulate pollutant detector and high-pressure unit Upper valve, high pressure connection line are connected to by proportional pressure control valve on pressurized fuel tank, and low-pressure connection tube road is equipped with string Valve in the temperature sensor of connection, low pressure gauge and low-pressure machine, low-pressure connection tube road is connected to supercharging by temperature sensor On fuel tank, the gas pressurization system is connected to by charge valve on pressurized fuel tank, and the gas pressurization system is by nitrogen Bottle, gas-charging connection, check valve and pressure reducing valve are formed, and the nitrogen cylinder is connected to by pressure reducing valve on charge valve, described Pressure reducing valve is equipped with the gas-charging connection and check valve in parallel with nitrogen cylinder.
2. the load test stand of aviation hydraulic oil pump vehicle as described in claim 1, which is characterized in that the high-pressure connecting pipe Road is movably connected in the high-pressure output tube road of aviation hydraulic oil pump vehicle, the low-pressure connection tube road by valve on high-pressure unit It is connected on the low pressure output pipe of aviation hydraulic oil pump vehicle by valve in low-pressure machine.
3. the load test stand of aviation hydraulic oil pump vehicle as described in claim 1, which is characterized in that in the pressurized fuel tank Portion is equipped with partition board, and pressurized fuel tank is separated into two mutually independent anallobars by partition board:IIth area of Ith area of hydraulic pressure and hydraulic pressure.
4. the load test stand of aviation hydraulic oil pump vehicle as claimed in claim 3, which is characterized in that on the pressurized fuel tank Equipped with two groups of high pressure connection lines and low-pressure connection tube road, one group of high pressure connection line, low-pressure connection tube road are connected with Ith area of hydraulic pressure It connects to form I system of hydraulic pressure, another group of high pressure connection line, low-pressure connection tube road are connected to form II system of hydraulic pressure with IIth area of hydraulic pressure System.
5. the load test stand of aviation hydraulic oil pump vehicle as described in claim 3 or 4, which is characterized in that the gas increases Pressure system is separately connected IIth area of Ith area of hydraulic pressure and hydraulic pressure by two charge valves in parallel.
6. the load test stand of aviation hydraulic oil pump vehicle as described in claim 1, which is characterized in that the top of the pressurized fuel tank Portion is equipped with Pneumatic safety valve and vent valve, and the bottom of pressurized fuel tank is equipped with plug of draining the oil.
7. the load test stand of aviation hydraulic oil pump vehicle as described in claim 1, which is characterized in that on the pressurized fuel tank Single high pressure connection line and single low-pressure connection tube road form one group of connecting line, the quantity of anallobar in the pressurized fuel tank Match with the group number on pressurized fuel tank upper connector road.
CN201810381371.7A 2018-04-25 2018-04-25 The load test stand of aviation hydraulic oil pump vehicle Pending CN108591140A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201810381371.7A CN108591140A (en) 2018-04-25 2018-04-25 The load test stand of aviation hydraulic oil pump vehicle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201810381371.7A CN108591140A (en) 2018-04-25 2018-04-25 The load test stand of aviation hydraulic oil pump vehicle

Publications (1)

Publication Number Publication Date
CN108591140A true CN108591140A (en) 2018-09-28

Family

ID=63609868

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201810381371.7A Pending CN108591140A (en) 2018-04-25 2018-04-25 The load test stand of aviation hydraulic oil pump vehicle

Country Status (1)

Country Link
CN (1) CN108591140A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110107559A (en) * 2019-05-29 2019-08-09 太原科技大学 A kind of hydraulic test bench hydraulic control system
CN113236634A (en) * 2021-06-16 2021-08-10 北京中航世科电子技术有限公司 Oil liquid purification device for oil pump vehicle

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110107559A (en) * 2019-05-29 2019-08-09 太原科技大学 A kind of hydraulic test bench hydraulic control system
CN110107559B (en) * 2019-05-29 2020-04-03 太原科技大学 Hydraulic control system of hydraulic test bed
CN113236634A (en) * 2021-06-16 2021-08-10 北京中航世科电子技术有限公司 Oil liquid purification device for oil pump vehicle

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