CN111532448B - Aviation hydraulic oil pump truck with coil frame - Google Patents
Aviation hydraulic oil pump truck with coil frame Download PDFInfo
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- CN111532448B CN111532448B CN202010290159.7A CN202010290159A CN111532448B CN 111532448 B CN111532448 B CN 111532448B CN 202010290159 A CN202010290159 A CN 202010290159A CN 111532448 B CN111532448 B CN 111532448B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid-Pressure Circuits (AREA)
- Rigid Pipes And Flexible Pipes (AREA)
Abstract
The invention discloses an aviation hydraulic oil pump truck with a belt reel support, which comprises a hydraulic hose butted with an airplane hydraulic system, wherein the hydraulic hose comprises a rear section, a middle section and a front section, a pair of electromagnetic valves are arranged at two ends of the middle section, the pair of electromagnetic valves are connected on an electric wire in series, and the pair of electromagnetic valves are normally closed valves; when the first hydraulic hose is stretched, the electric wire is broken before the middle section of the hydraulic hose along with the increase of the tensile force, and the middle section of the hydraulic hose is broken before the front section and the rear section of the hydraulic hose along with the continuous increase of the tensile force. The invention can prevent the continuous leakage of the oil pump vehicle and the airplane hydraulic system after the hydraulic hose is pulled off.
Description
Technical Field
The invention relates to the field of airplane ground hydraulic energy source guarantee equipment, in particular to an aviation hydraulic oil pump truck with a belt reel support.
Background
Modern aircraft are generally provided with a hydraulic system, when the hydraulic system of the aircraft is detected and maintained on the ground, performance detection of the hydraulic system of the aircraft is completed by ground oil pump equipment, and an aviation hydraulic oil pump vehicle is mainly designed for meeting the requirement.
The Chinese patent with the application number of 201610672043.3 discloses an aviation hydraulic oil pump truck, which comprises a high-pressure disc pipe frame and a low-pressure coil pipe frame, wherein the high-pressure disc pipe frame and the low-pressure coil pipe frame are respectively used for pulling out a hydraulic hose when being butted with an airplane and are respectively butted with an oil inlet and an oil outlet of an airplane hydraulic system; a hydraulic hose on the high-pressure coil pipe frame conveys hydraulic oil to an oil inlet of an aircraft hydraulic system; and a hydraulic hose on the low-pressure disc pipe frame absorbs oil from an oil outlet of an aircraft hydraulic system.
The aviation hydraulic pressure oil pump truck in the above-mentioned patent is self-propelled oil pump truck, and when hydraulic hose still was being connected with the aircraft, if people's maloperation in the oil pump truck driver's cabin, start the oil pump truck and keep away from the aircraft, then hydraulic hose can be stretched and pulled apart, and hydraulic hose is pulled apart the back, and oil pump truck and aircraft hydraulic system all can continuously leak.
Disclosure of Invention
In order to solve the defects of the prior art, the invention provides an aviation hydraulic oil pump vehicle with a coil pipe frame, wherein the coil pipe frame comprises a high-pressure coil pipe frame and a low-pressure coil pipe frame; a first hydraulic hose capable of being in butt joint with an oil inlet of an aircraft hydraulic system is arranged on the high-pressure coil pipe frame; a second hydraulic hose capable of being in butt joint with an oil outlet of an airplane hydraulic system is arranged on the low-pressure coil pipe frame;
the first hydraulic hose is formed by sequentially connecting three sections: the high-pressure coil pipe comprises a rear section connected with the high-pressure coil pipe frame, a middle section connected with the rear section and a front section connected with the middle section; one end of the first hydraulic hose, which is butted with an oil inlet of an aircraft hydraulic system, is taken as an output end of the first hydraulic hose, and the output end is positioned at the front section of the first hydraulic hose; on the first hydraulic hose: the length of the middle section is not more than 5cm, the tensile strength of the middle section is less than that of the front section and the rear section, the front section is provided with a first electromagnetic valve, the rear section is provided with a second electromagnetic valve, the first electromagnetic valve and the second electromagnetic valve are both close to the middle section, and the first electromagnetic valve and the second electromagnetic valve are both normally closed valves; the aviation hydraulic oil pump truck is provided with a first control module which controls the opening and closing of a first electromagnetic valve and a second electromagnetic valve through a first electric wire, the first electric wire is arranged on the outer wall of a first hydraulic hose, and the first electromagnetic valve and the second electromagnetic valve are connected in series on the first electric wire; the tensile strength of the first wire is smaller than that of the middle section of the first hydraulic hose; when the first hydraulic hose is stretched, the first electric wire is broken before the middle section of the first hydraulic hose along with the increase of the tensile force, and the middle section of the first hydraulic hose is broken before the front section and the rear section of the first hydraulic hose along with the continuous increase of the tensile force;
the second hydraulic hose is formed by sequentially connecting three sections: the low-pressure coil pipe frame comprises a rear section connected with the low-pressure coil pipe frame, a middle section connected with the rear section and a front section connected with the middle section; one end of the second hydraulic hose, which is butted with an oil outlet of the aircraft hydraulic system, is taken as an input end of the second hydraulic hose, and the input end is positioned at the front section of the second hydraulic hose; on the second hydraulic hose: the length of the middle section is not more than 5cm, the tensile strength of the middle section is less than that of the front section and the rear section, the front section is provided with a third electromagnetic valve, the rear section is provided with a fourth electromagnetic valve, the third electromagnetic valve and the fourth electromagnetic valve are both close to the middle section, and the third electromagnetic valve and the fourth electromagnetic valve are both normally closed valves; the aviation hydraulic oil pump truck is provided with a second control module which controls the opening and closing of a third electromagnetic valve and a fourth electromagnetic valve through a second electric wire, the second electric wire is wired on the outer wall of a second hydraulic hose, and the third electromagnetic valve and the fourth electromagnetic valve are connected in series on the second electric wire; the tensile strength of the second wire is smaller than that of the middle section of the second hydraulic hose; when the second hydraulic hose is stretched, along with the pulling force increase, the second electric wire is broken in advance of second hydraulic hose interlude, and along with the pulling force continues to increase, second hydraulic hose interlude is broken in advance of second hydraulic hose anterior segment and back end.
Preferably, the aviation hydraulic oil pump vehicle is a self-propelled oil pump vehicle.
Preferably, the aviation hydraulic oil pump vehicle comprises a cab.
Preferably, the first control module is provided with a first current detection unit, the first current detection unit detects the current of the first wire, and when the current of the first wire is abnormal due to the fact that the first wire is broken, the first current detection unit detects the abnormality and sends a first alarm signal outwards.
Preferably, a first alarm is arranged in the cab, and the first alarm is triggered to alarm by a first alarm signal.
Preferably, the second control module is provided with a second current detection unit, the second current detection unit detects the current of the second wire, and when the current of the second wire is abnormal due to the fact that the second wire is broken, the second current detection unit detects the abnormality and sends a second alarm signal outwards.
Preferably, a second alarm is arranged in the cab, and the second alarm is triggered to alarm by a second alarm signal.
A first hydraulic hose on the high-pressure disc pipe frame is butted with an oil inlet of an aircraft hydraulic system, and hydraulic oil is conveyed to the oil inlet; when hydraulic oil is conveyed to the oil inlet, the first control module controls the first electromagnetic valve and the second electromagnetic valve to be opened through the first electric wire;
a second hydraulic hose on the low pressure disc pipe frame is butted with an oil outlet of an airplane hydraulic system and absorbs oil from the oil outlet; when oil is absorbed from the oil outlet, the second control module controls the third electromagnetic valve and the fourth electromagnetic valve to be opened through a second wire;
the aviation hydraulic oil pump vehicle is a self-propelled oil pump vehicle, when the first hydraulic hose and the second hydraulic hose are connected with the airplane, if a person in a cab of the oil pump vehicle operates by mistake and the oil pump vehicle is started to be far away from the airplane, the first hydraulic hose and the second hydraulic hose can be stretched;
when the first hydraulic hose is stretched, the first electric wire is broken before the middle section of the first hydraulic hose along with the increase of the tensile force, and the middle section of the first hydraulic hose is broken before the front section and the rear section of the first hydraulic hose along with the continuous increase of the tensile force, namely the first hydraulic hose is broken at the middle section; the first electromagnetic valve and the second electromagnetic valve are normally closed, when the first electric wire is broken, the first electromagnetic valve and the second electromagnetic valve can be powered off and closed, so that after the first hydraulic hose is broken, the front section of the first hydraulic hose connected with an oil inlet of an aircraft hydraulic system is sealed by the first electromagnetic valve, and the rear section of the first hydraulic hose connected with the high-pressure coil pipe frame is sealed by the second electromagnetic valve, so that the oil inlet of the aircraft hydraulic system cannot continuously leak, and the first hydraulic hose connected with the high-pressure coil pipe frame cannot continuously leak;
when the second hydraulic hose is stretched, the second electric wire is broken before the middle section of the second hydraulic hose along with the increase of the tensile force, and the middle section of the second hydraulic hose is broken before the front section and the rear section of the second hydraulic hose along with the continuous increase of the tensile force, namely the second hydraulic hose is broken at the middle section; the third electromagnetic valve and the fourth electromagnetic valve are normally closed, when the second wire is broken, the third electromagnetic valve and the fourth electromagnetic valve can be powered off and closed, so that after the second hydraulic hose is broken, the front section of the second hydraulic hose connected with the oil outlet of the aircraft hydraulic system is sealed by the third electromagnetic valve, and the rear section of the second hydraulic hose connected with the low-pressure coil pipe frame is sealed by the fourth electromagnetic valve, so that the oil outlet of the aircraft hydraulic system cannot continuously leak, and the second hydraulic hose connected with the low-pressure coil pipe frame cannot continuously leak;
therefore, the invention can prevent the continuous leakage of the oil pump truck and the aircraft hydraulic system after the hydraulic hose is pulled off.
Drawings
FIG. 1 is a schematic illustration of a first hydraulic hose;
fig. 2 is a schematic view of a second hydraulic hose.
Detailed Description
The following description of the embodiments of the present invention will be made with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and the protection scope of the present invention is not limited thereby.
As shown in fig. 1 and fig. 2, the invention provides an aviation hydraulic oil pump truck with a reel support, which is a self-propelled oil pump truck, and comprises a cab; the coil frame comprises a high-pressure coil frame and a low-pressure coil frame; a first hydraulic hose 10 which can be butted with an oil inlet of an aircraft hydraulic system is arranged on the high-pressure coil pipe frame; a second hydraulic hose 20 which can be butted with an oil outlet of the aircraft hydraulic system is arranged on the low-pressure coil pipe frame;
the first hydraulic hose 10 is formed by sequentially connecting three sections: a rear section 11 connected with the high-pressure coil frame, a middle section 12 connected with the rear section 11, and a front section 13 connected with the middle section 12; one end of the first hydraulic hose 10, which is butted with an oil inlet of an aircraft hydraulic system, is taken as an output end of the first hydraulic hose 10, and the output end is positioned at the front section 13 of the first hydraulic hose 10; on the first hydraulic hose 10: the length of the middle section 12 is not more than 5cm, the tensile strength of the middle section 12 is less than that of the front section 13 and the rear section 11, the front section 13 is provided with a first electromagnetic valve 14, the rear section 11 is provided with a second electromagnetic valve 15, the first electromagnetic valve 14 and the second electromagnetic valve 15 are both close to the middle section 12, and the first electromagnetic valve 14 and the second electromagnetic valve 15 are both normally closed valves; a first control module for controlling the opening and closing of the first electromagnetic valve 14 and the second electromagnetic valve 15 through a first electric wire is arranged on the aviation hydraulic oil pump truck, the first electric wire (not shown in fig. 1) is wired on the outer wall of the first hydraulic hose 10, and the first electromagnetic valve 14 and the second electromagnetic valve 15 are connected in series on the first electric wire; the tensile strength of the first wire is less than the tensile strength of the middle section 12 of the first hydraulic hose 10; when the first hydraulic hose 10 is stretched, the first electric wire is broken before the middle section 12 of the first hydraulic hose 10 along with the increase of the tensile force, and the middle section 12 of the first hydraulic hose 10 is broken before the front section 13 and the rear section 11 of the first hydraulic hose 10 along with the increase of the tensile force;
the second hydraulic hose 20 is formed by sequentially connecting three sections: a rear section 21 connected to the low pressure coil frame, a middle section 22 connected to the rear section 21, and a front section 23 connected to the middle section 22; one end of the second hydraulic hose 20, which is butted with an oil outlet of the aircraft hydraulic system, is taken as an input end of the second hydraulic hose 20, and the input end is positioned at a front section 23 of the second hydraulic hose 20; on the second hydraulic hose 20: the length of the middle section 22 is not more than 5cm, the tensile strength of the middle section 22 is less than that of the front section 23 and the rear section 21, the front section 23 is provided with a third electromagnetic valve 24, the rear section 21 is provided with a fourth electromagnetic valve 25, the third electromagnetic valve 24 and the fourth electromagnetic valve 25 are both close to the middle section 22, and the third electromagnetic valve 24 and the fourth electromagnetic valve 25 are both normally closed valves; a second control module for controlling the opening and closing of the third electromagnetic valve 24 and the fourth electromagnetic valve 25 through a second electric wire is arranged on the aviation hydraulic oil pump truck, the second electric wire (not shown in fig. 2) is wired on the outer wall of the second hydraulic hose 20, and the third electromagnetic valve 24 and the fourth electromagnetic valve 25 are connected in series on the second electric wire; the tensile strength of the second electric wire is smaller than that of the intermediate section 22 of the second hydraulic hose 20; when the second hydraulic hose 20 is pulled, the second electric wire is broken before the middle section 22 of the second hydraulic hose 20 as the pulling force increases, and the middle section 22 of the second hydraulic hose 20 is broken before the front section 23 and the rear section 21 of the second hydraulic hose 20 as the pulling force continues to increase.
A first hydraulic hose 10 on the high-pressure disc pipe frame is butted with an oil inlet of an aircraft hydraulic system and conveys hydraulic oil to the oil inlet; when hydraulic oil is conveyed to the oil inlet, the first control module controls the first electromagnetic valve 14 and the second electromagnetic valve 15 to be opened through the first electric wire;
a second hydraulic hose 20 on the low pressure pipe frame is butted with an oil outlet of the airplane hydraulic system and absorbs oil from the oil outlet; when oil is absorbed from the oil outlet, the second control module controls the third electromagnetic valve and the fourth electromagnetic valve to be opened through a second wire;
the aviation hydraulic oil pump vehicle is a self-propelled oil pump vehicle, when the first hydraulic hose 10 and the second hydraulic hose 20 are connected with an airplane, if a person in a cab of the oil pump vehicle operates by mistake and the oil pump vehicle is started to be far away from the airplane, the first hydraulic hose 10 and the second hydraulic hose 20 can be stretched;
when the first hydraulic hose 10 is stretched, as the pulling force increases, the first electric wire is broken before the middle section 12 of the first hydraulic hose 10, and as the pulling force continues to increase, the middle section 12 of the first hydraulic hose 10 is broken before the front section 13 and the rear section 11 of the first hydraulic hose 10, that is, the first hydraulic hose 10 is broken at the middle section 12; the two ends of the middle section 12 of the first hydraulic hose 10 are provided with a first electromagnetic valve 14 and a second electromagnetic valve 15, the first electromagnetic valve 14 and the second electromagnetic valve 15 are normally closed valves, when a first electric wire is broken, the first electromagnetic valve 14 and the second electromagnetic valve 15 are powered off and closed, so that after the first hydraulic hose 10 is broken, the front section 13 of the first hydraulic hose 10 connected with an oil inlet of an aircraft hydraulic system is sealed by the first electromagnetic valve 14, and the rear section 11 of the first hydraulic hose 10 connected with a high-pressure coil frame is sealed by the second electromagnetic valve 15, so that the oil inlet of the aircraft hydraulic system cannot continuously leak, and the first hydraulic hose 10 connected with the high-pressure coil frame cannot continuously leak;
when the second hydraulic hose 20 is stretched, the second electric wire is broken before the middle section 22 of the second hydraulic hose 20 as the pulling force increases, and the middle section 22 of the second hydraulic hose 20 is broken before the front section 23 and the rear section 21 of the second hydraulic hose 20 as the pulling force continues to increase, that is, the second hydraulic hose 20 is broken at the middle section 22; the third electromagnetic valve 24 and the fourth electromagnetic valve 25 are arranged at two ends of the middle section 22 of the second hydraulic hose 20, because the third electromagnetic valve 24 and the fourth electromagnetic valve 25 are normally closed valves, when the second electric wire is broken, the third electromagnetic valve 24 and the fourth electromagnetic valve 25 are powered off and closed, after the second hydraulic hose 20 is broken, the front section 23 of the second hydraulic hose 20 connected with the oil outlet of the aircraft hydraulic system is sealed by the third electromagnetic valve 24, and the rear section 21 of the second hydraulic hose 20 connected with the low-pressure coil frame is sealed by the fourth electromagnetic valve 25, so that the oil outlet of the aircraft hydraulic system cannot continuously leak, and the second hydraulic hose 20 connected with the low-pressure coil frame cannot continuously leak;
therefore, the invention can prevent the continuous leakage of the oil pump truck and the aircraft hydraulic system after the hydraulic hose is pulled off.
Preferably, the first control module is provided with a first current detection unit, the first current detection unit detects the current of the first wire, and when the current of the first wire is abnormal due to the fact that the first wire is broken, the first current detection unit detects the abnormality and sends a first alarm signal outwards; a first alarm is arranged in the cab and triggered to alarm by a first alarm signal.
Preferably, the second control module is provided with a second current detection unit, the second current detection unit detects the current of the second wire, and when the current of the second wire is abnormal due to the fact that the second wire is broken, the second current detection unit detects the abnormality and sends a second alarm signal outwards; and a second alarm is arranged in the cab and triggered to alarm by a second alarm signal.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the technical principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.
Claims (1)
1. The aviation hydraulic oil pump truck with the pipe frame is a self-propelled oil pump truck, and comprises a cab; the coil frame comprises a high-pressure coil frame and a low-pressure coil frame; a first hydraulic hose capable of being in butt joint with an oil inlet of an aircraft hydraulic system is arranged on the high-pressure coil pipe frame; a second hydraulic hose capable of being in butt joint with an oil outlet of the aircraft hydraulic system is arranged on the low-pressure coil pipe frame; the method is characterized in that:
the first hydraulic hose is formed by sequentially connecting three sections: the high-pressure coil pipe comprises a rear section connected with the high-pressure coil pipe frame, a middle section connected with the rear section and a front section connected with the middle section; one end of the first hydraulic hose, which is butted with an oil inlet of an aircraft hydraulic system, is taken as an output end of the first hydraulic hose, and the output end is positioned at the front section of the first hydraulic hose; on the first hydraulic hose: the length of the middle section is not more than 5cm, the tensile strength of the middle section is less than that of the front section and the rear section, the front section is provided with a first electromagnetic valve, the rear section is provided with a second electromagnetic valve, the first electromagnetic valve and the second electromagnetic valve are both close to the middle section, and the first electromagnetic valve and the second electromagnetic valve are both normally closed valves; the aviation hydraulic oil pump truck is provided with a first control module which controls the opening and closing of a first electromagnetic valve and a second electromagnetic valve through a first electric wire, the first electric wire is arranged on the outer wall of a first hydraulic hose, and the first electromagnetic valve and the second electromagnetic valve are connected in series on the first electric wire; the tensile strength of the first wire is smaller than that of the middle section of the first hydraulic hose; when the first hydraulic hose is stretched, the first electric wire is pulled apart before the middle section of the first hydraulic hose along with the increase of the tensile force, and the middle section of the first hydraulic hose is pulled apart before the front section and the rear section of the first hydraulic hose along with the continuous increase of the tensile force;
the second hydraulic hose is formed by sequentially connecting three sections: the low-pressure coil pipe frame comprises a rear section connected with the low-pressure coil pipe frame, a middle section connected with the rear section and a front section connected with the middle section; one end of the second hydraulic hose, which is butted with an oil outlet of the aircraft hydraulic system, is taken as an input end of the second hydraulic hose, and the input end is positioned at the front section of the second hydraulic hose; on the second hydraulic hose: the length of the middle section is not more than 5cm, the tensile strength of the middle section is less than that of the front section and the rear section, the front section is provided with a third electromagnetic valve, the rear section is provided with a fourth electromagnetic valve, the third electromagnetic valve and the fourth electromagnetic valve are both close to the middle section, and the third electromagnetic valve and the fourth electromagnetic valve are both normally closed valves; the aviation hydraulic oil pump truck is provided with a second control module which controls the opening and closing of a third electromagnetic valve and a fourth electromagnetic valve through a second electric wire, the second electric wire is arranged on the outer wall of a second hydraulic hose, and the third electromagnetic valve and the fourth electromagnetic valve are connected in series on the second electric wire; the tensile strength of the second wire is smaller than that of the middle section of the second hydraulic hose; when the second hydraulic hose is stretched, the second electric wire is broken before the middle section of the second hydraulic hose along with the increase of the tensile force, and the middle section of the second hydraulic hose is broken before the front section and the rear section of the second hydraulic hose along with the continuous increase of the tensile force;
the first control module is provided with a first current detection unit, the first current detection unit detects the current of the first wire, and when the current of the first wire is abnormal due to the fact that the first wire is broken, the first current detection unit detects the abnormality and sends a first alarm signal outwards; a first alarm is arranged in the cab and triggered to alarm by a first alarm signal;
the second control module is provided with a second current detection unit which detects the current of the second wire, and when the current of the second wire is abnormal due to the fact that the second wire is broken, the second current detection unit detects the abnormality and sends a second alarm signal outwards; and a second alarm is arranged in the cab and triggered to alarm by a second alarm signal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010290159.7A CN111532448B (en) | 2020-04-14 | 2020-04-14 | Aviation hydraulic oil pump truck with coil frame |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010290159.7A CN111532448B (en) | 2020-04-14 | 2020-04-14 | Aviation hydraulic oil pump truck with coil frame |
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| CN111532448A CN111532448A (en) | 2020-08-14 |
| CN111532448B true CN111532448B (en) | 2022-07-15 |
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| US5156190A (en) * | 1990-08-29 | 1992-10-20 | Colin R. Staley, III | Hydraulic safety hose with fluid removal conduit |
| CN1846094A (en) * | 2003-08-28 | 2006-10-11 | 丰田自动车株式会社 | Gas supply apparatus |
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| CN207132090U (en) * | 2017-07-28 | 2018-03-23 | 深圳中燃哈工大燃气技术研究院有限公司 | LPG is with pump tank car and unloads liquid system |
| CN207279264U (en) * | 2017-08-09 | 2018-04-27 | 湖南省水运建设投资集团有限公司 | A kind of loading system of LNG filling ship |
| CN208566175U (en) * | 2018-06-21 | 2019-03-01 | 自贡中至能源设备制造有限公司 | A kind of LNG loading system of band LNG vacuum checking device |
| CN209259665U (en) * | 2018-09-06 | 2019-08-16 | 中国石油化工股份有限公司 | Liquid hydrocarbon entrucking emergency breaks valve closer |
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2020
- 2020-04-14 CN CN202010290159.7A patent/CN111532448B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5156190A (en) * | 1990-08-29 | 1992-10-20 | Colin R. Staley, III | Hydraulic safety hose with fluid removal conduit |
| CN1846094A (en) * | 2003-08-28 | 2006-10-11 | 丰田自动车株式会社 | Gas supply apparatus |
| CN203131420U (en) * | 2013-02-26 | 2013-08-14 | 张家港中集圣达因低温装备有限公司 | Snap break device and pump filling device with same |
| CN103542252A (en) * | 2013-09-30 | 2014-01-29 | 江苏现代造船技术有限公司 | Filling device for LNG (Liquefied Natural Gas) |
| CN203809916U (en) * | 2014-02-22 | 2014-09-03 | 张世杰 | Pull-breaking protective quick connector |
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| CN209259665U (en) * | 2018-09-06 | 2019-08-16 | 中国石油化工股份有限公司 | Liquid hydrocarbon entrucking emergency breaks valve closer |
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| Publication number | Publication date |
|---|---|
| CN111532448A (en) | 2020-08-14 |
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