CN210664925U - Integrated test system for aircraft refueling joint - Google Patents
Integrated test system for aircraft refueling joint Download PDFInfo
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- CN210664925U CN210664925U CN201920818134.2U CN201920818134U CN210664925U CN 210664925 U CN210664925 U CN 210664925U CN 201920818134 U CN201920818134 U CN 201920818134U CN 210664925 U CN210664925 U CN 210664925U
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Abstract
The application discloses aircraft refueling connects combined test system through including: the device comprises an oil filling connector test seat, an outlet pressure gauge, a stop valve, a first inlet pressure gauge, a second inlet pressure gauge, a pressure inlet hose, a pressure regulating module and a reversing valve; one end of the refueling joint test seat is connected with the outlet pressure gauge; the reversing valve is arranged between the stop valve and the pressure inlet hose; the first inlet pressure gauge and the second inlet pressure gauge are also arranged between the reversing valve and the stop valve; the stop valve is also connected with the pressure regulating module. The purpose of carrying out static voltage stabilization test on the refueling joint through the device is achieved, the device is suitable for various personnel, the device is operated through the application, the device has the advantages of being reliable in performance, simple and convenient to operate, high in control precision and strong in function expansibility, and the technical effects of effective control on each step and accurate in test result are achieved.
Description
Technical Field
The application relates to the technical field of testing device design, in particular to an aircraft refueling joint comprehensive test system.
Background
The existing check out test set of most domestic aviation filling stations is comparatively simple, provides pressure through the hand pump, only can simply test the leakproofness that the aircraft refueled the joint, connects the leakproofness of other valves and all can't detect to the ground well, and the function is single, and equipment falls behind, does not have comprehensive testing ability. In addition, the detection is carried out by the prior art, the experience of detection personnel is mostly relied on, and the accuracy of the detection result cannot be ensured.
Aiming at various technical problems in the related art, no effective solution is provided at present.
SUMMERY OF THE UTILITY MODEL
The main objective of this application is to provide an aircraft refueling joint combined test system to solve the problem that exists among the correlation technique.
To achieve the above objects, according to one aspect of the present application, there is provided an aircraft refueling joint comprehensive testing system.
The aircraft refueling joint comprehensive test system according to the application comprises:
the device comprises an oil filling connector test seat, an outlet pressure gauge, a stop valve, a first inlet pressure gauge, a second inlet pressure gauge, a pressure inlet hose, a pressure regulating module and a reversing valve;
one end of the refueling joint test seat is connected with the outlet pressure gauge;
the reversing valve is arranged between the stop valve and the pressure inlet hose;
the first inlet pressure gauge and the second inlet pressure gauge are also arranged between the reversing valve and the stop valve;
the stop valve is also connected with the pressure regulating module.
Further, the integrated test system for the aircraft refueling joint further comprises: a pressure relief valve and an overflow valve;
the pressure release valve is connected with one end of the refueling joint test seat;
the overflow valve is arranged between the reversing valve and the stop valve.
Further, the integrated test system for the aircraft refueling joint further comprises: a quick connector;
the pressure inlet hose is fixedly provided with the quick-connection plug.
Further, the integrated test system for the aircraft refueling joint further comprises: the refueling rubber pipe joint seat is used for being connected with a refueling hose to be tested;
and the oil filling rubber pipe joint seat is connected with the reversing valve.
Further, the integrated test system for the aircraft refueling joint further comprises: the well plug is used for plugging the inlet of the tested well connector, and the well connector seat is connected with the tested well connector;
the ground well joint seat is arranged in the ground well plug, and one end of the ground well joint seat is used for being connected with the pressure inlet hose.
Further, the integrated test system for the aircraft refueling joint further comprises: a disc-shaped oil collecting tray;
the oil collecting tray is arranged below the ground well plug.
Further, as aforementioned aircraft fueling joint combined test system, the pressure regulating module includes: the oil pump is connected with the oil tank through a pipeline;
the lower part and the upper part of the oil tank are respectively connected with one end of the oil outlet pipeline and one end of the oil return pipeline;
the other end of the oil outlet pipeline and the other end of the oil return pipeline are respectively connected to the stop valve;
the oil pump is arranged on the oil outlet pipeline;
the voltage-regulating frequency converter, the motor and the oil pump are connected in sequence.
Further, the integrated test system for the aircraft refueling joint further comprises: one-way valves and safety valves;
the one-way valve is arranged on the oil outlet pipeline;
the safety valve is arranged on the oil return pipeline.
Further, the integrated test system for the aircraft refueling joint further comprises: a filter and a blow-down valve;
the filter is arranged on the oil outlet pipeline between the one-way valve and the stop valve;
the blowoff valve is arranged at the bottom of the oil tank.
Further, the integrated test system for the aircraft refueling joint further comprises: a transparent oil return main pipe;
and two ends of the transparent oil return main pipe are respectively connected with an oil return pipeline and an oil tank.
In this application embodiment, adopt the mode of an aircraft refueling joint combined test system, through including: the device comprises an oil filling connector test seat, an outlet pressure gauge, a stop valve, a first inlet pressure gauge, a second inlet pressure gauge, a pressure inlet hose, a pressure regulating module and a reversing valve; one end of the refueling joint test seat is connected with the outlet pressure gauge; the reversing valve is arranged between the stop valve and the pressure inlet hose; the first inlet pressure gauge and the second inlet pressure gauge are also arranged between the reversing valve and the stop valve; the stop valve is also connected with the pressure regulating module. The purpose of carrying out static voltage stabilization test on the refueling joint through the device is achieved, the device is suitable for various personnel, the device is operated through the application, the device has the advantages of being reliable in performance, simple and convenient to operate, high in control precision and strong in function expansibility, and the technical effects of effective control on each step and accurate in test result are achieved.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, serve to provide a further understanding of the application and to enable other features, objects, and advantages of the application to be more apparent. The drawings and their description illustrate the embodiments of the invention and do not limit it. In the drawings:
FIG. 1 is a schematic diagram of a system architecture of an aircraft refueling joint comprehensive testing system according to an embodiment of the present application.
Detailed Description
In order to make the technical solutions better understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only partial embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It should be understood that the data so used may be interchanged under appropriate circumstances such that embodiments of the application described herein may be used. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
In this application, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings. These terms are used primarily to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to a particular orientation or to be constructed and operated in a particular orientation.
Moreover, some of the above terms may be used to indicate other meanings besides the orientation or positional relationship, for example, the term "on" may also be used to indicate some kind of attachment or connection relationship in some cases. The specific meaning of these terms in this application will be understood by those of ordinary skill in the art as appropriate.
Furthermore, the terms "mounted," "disposed," "provided," "connected," and "sleeved" are to be construed broadly. For example, it may be a fixed connection, a removable connection, or a unitary construction; can be a mechanical connection, or an electrical connection; may be directly connected, or indirectly connected through intervening media, or may be in internal communication between two devices, elements or components. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
According to embodiment 1 of the application, an aircraft refueling joint comprehensive test system is provided. As shown in fig. 1, the present application relates to an aircraft refueling joint comprehensive test system, comprising:
the device comprises an oil filling connector test seat 1, an outlet pressure gauge 2, a stop valve 4, a first inlet pressure gauge 5, a second inlet pressure gauge 6, a pressure inlet hose 7, a pressure regulating module and a reversing valve 9; preferably, in order to prevent the refueling joint test seat 1 from being polluted, a dustproof cover matched with the refueling joint test seat is further arranged;
one end of the refueling joint test seat 1 is connected with the outlet pressure gauge 2;
the reversing valve 9 is arranged between the stop valve 4 and the pressure inlet hose 7;
the first inlet pressure gauge 5 and the second inlet pressure gauge 6 are also arranged between the reversing valve 9 and the stop valve 4;
the stop valve 4 is also connected with the pressure regulating module 4.
Specifically, the static pressure stabilizing test of the oil filling joint can be performed through the device in the embodiment, and the steps are as follows:
1. opening the dust cap, rotating and clamping the outlet of the tested connector and the oiling connector test seat 1 on the inner side of the test bed, connecting the inlet adapter connector of the tested connector and the pressure inlet hose 7 of the test bed, and assembling the quick connector (the size of the hose quick connector is an external thread R1/4);
2. opening a stop valve 4, opening switches of a first inlet pressure gauge 5 and a second inlet pressure gauge 6 and a switch of an outlet pressure gauge 2 (note: when the test pressure is larger than the range of the pressure gauges, the switches must be closed), and placing a reversing valve 9 at a joint test position (preferably, when a handle on the reversing valve 9 is positioned at the right side, the position is adjusted to be the joint test position);
3. after the system exhausts the pipeline and product air through the adjusting and pressure regulating module (corresponding adjustment can be carried out by setting a corresponding adjusting frequency adjusting knob when in use), the overflow valve 10 is closed, the pressure regulating module of the adjusting and pressure regulating module slowly pressurizes to 0.3Mpa, the stop valve 4 is closed, and whether leakage exists at the joints of the tested joint and the test bed is checked;
4. and opening the stop valve 4, continuously adjusting the pressure regulating module to gradually pressurize to the specified pressure of the technical conditions of the connector, and checking the tested product.
And the pressure resistance test of the refueling joint, the specific test flow is as follows:
1. and the pressure regulating module is regulated to continuously pressurize to specified pressure-resistant pressure, the stop valve 4 is closed, and the tested product is checked.
On the basis of the aircraft refueling joint comprehensive test system in the embodiment 1, the system further comprises: a relief valve 3 and an overflow valve 10;
the pressure release valve 3 is connected with one end of the refueling joint test seat 1;
the overflow valve 10 is arranged between the reversing valve 9 and the stop valve 4.
Specifically, the device in this embodiment can perform a static pressure stabilization test of the filler neck or perform pressure relief after the pressure resistance test of the filler neck is completed, and the steps are as follows:
after the test is finished, the overflow valve 10 is slowly opened to release the pressure, and the stop valve 4 is opened.
In addition, to lower pressure like 0.03 Mpa's experiment, can be after exhausting the pipeline air, adjust the pressure regulating module earlier to 0, close overflow valve 10, close stop valve 4, adjust the pressure regulating module again, slowly open the stop valve, when first inlet pressure table 5 shows 0.03Mpa, close stop valve 4, can obtain various lower pressure.
On the basis of the aircraft refueling joint comprehensive test system in the embodiment 1, the system further comprises: a quick connector 11;
the pressure inlet hose 7 is fixedly provided with the quick-connection-peg 11; preferably, the size of the quick connector is an external thread R1/4; therefore, when the outlet of the tested connector is connected with the oil filling connector on the inner side of the test bed, the inlet adapter connector of the tested connector and the pressure inlet hose of the test bed can be connected well through the quick-connection-peg 11.
Embodiment 2 an aircraft refueling joint integrated test system as described above, according to one embodiment of the present application, an aircraft refueling joint integrated test system is provided. As shown in fig. 1, the present application relates to an aircraft refueling joint comprehensive test system, comprising:
the device comprises an oil filling connector test seat 1, an outlet pressure gauge 2, a stop valve 4, a first inlet pressure gauge 5, a second inlet pressure gauge 6, a pressure inlet hose 7, a pressure regulating module and a reversing valve 9; preferably, in order to prevent the refueling joint test seat 1 from being polluted, a dustproof cover matched with the refueling joint test seat is further arranged;
one end of the refueling joint test seat 1 is connected with the outlet pressure gauge 2;
the reversing valve 9 is arranged between the stop valve 4 and the pressure inlet hose 7;
the first inlet pressure gauge 5 and the second inlet pressure gauge 6 are also arranged between the reversing valve 9 and the stop valve 4;
the stop valve 4 is also connected with the pressure regulating module 4.
Further comprising: a relief valve 3 and an overflow valve 10;
the pressure release valve 3 is connected with one end of the refueling joint test seat 1;
the overflow valve 10 is arranged between the reversing valve 9 and the stop valve 4;
further comprising: the refueling rubber pipe joint seat 12 is used for being connected with a refueling hose to be tested;
the oil filling rubber pipe joint seat 12 is connected with the reversing valve 9.
The test bench in the embodiment can be used for carrying out the pressure resistance test of the oil filling rubber pipe; the specific process is as follows:
1. opening the stop valve 4 and the switches of the first inlet pressure gauge 5 and the second inlet pressure gauge 6, and placing the reversing valve 9 at a hose test position (preferably, when a handle on the reversing valve 9 is positioned at the left side, the hose test position is adjusted);
2. pulling out an oiling hose of an aircraft refueling truck, rotationally clamping an oiling joint of the oiling hose with an oiling hose joint seat 12 on the left side of a test bed, opening a flow switch of the oiling joint of the tested hose, filling the tested hose with oiling, and closing a relevant valve of the tested hose on the refueling truck;
3. slowly pressurizing to 0.3Mpa, checking whether the tested hose has leakage (preferably, other oil supply devices can be adopted to provide all the test oil);
4. gradually pressurizing to a pressure-resistant pressure specified by technical conditions, and checking whether the tested hose has leakage or abnormality;
5. after the test is finished, the overflow valve 10 is slowly opened to release the pressure, and the stop valve 4 is opened.
Meanwhile, the test bench in the embodiment can be used for testing the sealing performance of the medium-low pressure valve, and the specific flow is as follows:
1. assembling the inlet of the tested medium-low pressure valve and the quick connection plug of the pressure inlet hose 7 of the test bed;
2. the pressure release valve 3 is closed, the pressure gauge switch is closed according to the test pressure, the stop valve 4 is opened, and the reversing valve 9 is arranged at the joint test position (the handle is right);
3. slowly pressurizing to the rated working pressure of the valve, and checking whether the tested valve leaks or not;
4. after the test is finished, the overflow valve 10 is slowly opened to release the pressure, and the stop valve 4 is opened.
Embodiment 3, an aircraft refueling joint comprehensive test system as described above, comprising:
the device comprises an oil filling connector test seat 1, an outlet pressure gauge 2, a stop valve 4, a first inlet pressure gauge 5, a second inlet pressure gauge 6, a pressure inlet hose 7, a pressure regulating module and a reversing valve 9; preferably, in order to prevent the refueling joint test seat 1 from being polluted, a dustproof cover matched with the refueling joint test seat is further arranged; one end of the refueling joint test seat 1 is connected with the outlet pressure gauge 2; the reversing valve 9 is arranged between the stop valve 4 and the pressure inlet hose 7; the first inlet pressure gauge 5 and the second inlet pressure gauge 6 are also arranged between the reversing valve 9 and the stop valve 4; the stop valve 4 is also connected with the pressure regulating module 4.
Further comprising: a relief valve 3 and an overflow valve 10; the pressure release valve 3 is connected with one end of the refueling joint test seat 1; the overflow valve 10 is arranged between the reversing valve 9 and the stop valve 4;
further comprising: the refueling rubber pipe joint seat 12 is used for being connected with a refueling hose to be tested; the oil filling rubber pipe joint seat 12 is connected with the reversing valve 9.
Further comprising: a ground well plug 13 for blocking the inlet of the ground well joint to be measured and a ground well joint seat 14 connected with the ground well joint to be measured; the ground well joint seat 14 is arranged in the ground well plug 13, and one end of the ground well joint seat 14 is used for being connected with the pressure inlet hose 7.
Further comprising: a disc-shaped oil pan 15; the oil collecting tray 15 is arranged below the ground well plug 13.
Particularly, the test bed in the application can be used for testing the sealing performance of the ground well joint
1. Closing the pressure relief valve 3 (preferably, the pressure relief valve 3 is closed when the handle is downward), blocking an inlet of the tested ground well joint by using a ground well plug 13, clamping the tested ground well joint with a ground well joint seat 14, connecting a pressure inlet hose 74 with the ground well joint seat 14, closing a switch of an inlet pressure gauge 1, and opening a switch of an inlet pressure gauge 2; preferably, the well joint base 14 is also provided with a quick-connect connector 11, so that the pressure inlet hose 74 and the well joint base 14 can be connected through two quick-connect connectors 11;
2. opening the stop valve 4, and adjusting the reversing valve 9 to the joint test (the handle is right);
3. connecting an external maximum 1Mpa air source with a test bed 1Mpa air pressure inlet, and connecting a test bed 0-0.8 Mpa air pressure outlet
The air pipe is connected with the air pressure inlet of the tested ground well joint, and the air pressure valve is regulated to pressurize to the opening working pressure of the tested ground well joint (the pressure regulating method is that the pressure is increased by 0.1MPa from 0 to 8 circles every time the air pipe rotates one circle clockwise, namely the maximum air pressure of 0.8MPa is output);
4. slowly pressurizing to the rated working pressure of the tested ground well joint, closing the stop valve, and checking whether the tested ground well joint has leakage;
5. after the test is finished, the overflow valve 10 is slowly opened to release the pressure, and the stop valve 4 is opened.
In some embodiments, an aircraft refueling joint integrated test system as described above, the pressure regulating module comprises: the oil tank 16, the oil pump 17, the voltage-regulating frequency converter 18, the motor 19, the oil outlet pipeline 20 and the oil return pipeline 21;
the lower part and the upper part of the oil tank 16 are respectively connected with one end of the oil outlet pipeline 20 and one end of the oil return pipeline 21;
the other end of the oil outlet pipeline 20 and the other end of the oil return pipeline 21 are respectively connected to the stop valve 4;
the oil pump 17 is arranged on the oil outlet pipeline 20;
the voltage-regulating frequency converter 18, the motor 19 and the oil pump 17 are connected in sequence.
Preferably, the motor 19 is an explosion-proof motor; the running power of the motor 19 can be changed by adjusting the frequency of the voltage-regulating frequency converter 18, so that the conveying condition of the oil pump 17 on the test oil can be changed; and the test oil is ejected from the oil outlet pipe 20 and recovered from the oil return pipe 21.
In some embodiments, the aircraft refueling joint comprehensive testing system as described above further comprises: a check valve 22 and a relief valve 23;
the check valve 22 is arranged on the oil outlet pipeline 20; specifically, by providing the check valve 22, the test oil can be prevented from being recovered from the oil outlet pipe 20, causing damage to the oil outlet pipe 20 and the oil pump 17,
the safety valve 23 is arranged on the oil return pipeline 21; specifically, the safety valve 23 may be arranged to open the safety valve 23 on the oil return pipe 21 when the hydraulic pressure in the system is too high, so that the oil can be smoothly recovered and depressurized.
In some embodiments, the aircraft refueling joint comprehensive testing system as described above further comprises: a filter 24 and a blow-off valve 25;
the filter 24 is arranged on the oil outlet pipeline 20 between the check valve 22 and the stop valve 4; specifically, the filter 24 can be arranged to keep the test oil pure, so as to eliminate the influence of impurities on the test equipment;
the drain valve 25 is arranged at the bottom of the oil tank 16; specifically, impurities in the oil tank 16 can be removed in time by arranging the drain valve 25, and the purity of the test oil is increased.
Further, an oil filling port 27 is also formed in the oil tank 16; preferably, a filter screen 28 is arranged on the oil filling port 27 and used for filtering out redundant impurities; a liquid level meter 29 is arranged in the oil tank and used for visually showing the liquid level height in the oil tank 16.
In some embodiments, the aircraft refueling joint comprehensive testing system as described above further comprises: a transparent oil return manifold 26;
the two ends of the transparent oil return main pipe 26 are respectively connected with the oil return pipeline 21 and the oil tank 16. In particular, by providing the transparent oil return manifold 26, the recovery of the test oil can be clearly seen.
In some embodiments, the universal wheel is arranged at the bottom of the test bed, and the universal wheel is provided with a foot brake; the test bed is provided with a static conducting wire for conducting static electricity out of the test bed to prevent fire; and before the experiment, the preparation work as follows needs to be carried out:
1. locking 2 universal wheel foot brakes in front of the test bed, checking that a static conducting wire (a stainless steel iron chain at the rear part of the test bed) of the test bed is connected, and plugging a 380V power plug connected with a cable of 5 meters onto a power socket;
2. qualified aviation kerosene is added into the oil tank 16 to the range of the upper limit and the lower limit of the liquid level meter 29;
3. switch-on main switch and 18 switch of pressure modulation converter, 18 pilot lamps of pressure modulation converter are bright, switch-on frequency conversion start/stop switch, 17 work pilot lamps of oil pump are bright, 7 to the pressurization joint test seats with experimental frock switch-on pressure import hose, open first import manometer 5, 6 switches of second import manometer, close export manometer 2 switches, open stop valve 4 (the handle is right for opening, the handle is downwards for closing), it is experimental (the handle is right) to connect to adjust reversing valve 9. Note: the arrangement is only one method for removing air in the test pipeline of the refueling joint of the system, and the specific method is determined according to products.
4. Opening a pressure relief valve 3 (the handle is opened rightwards, the handle is closed downwards), adjusting an overflow valve 10 to a maximum open position (the handle is closed leftwards), adjusting a frequency adjusting knob (used for adjusting a voltage-adjusting frequency converter 18) on a panel of the explosion-proof distribution box, adjusting a frequency display meter to about 10, observing a transparent oil return main pipe 26 at an outlet of the overflow valve, confirming that oil flows out of a hydraulic system (the motor can be proved to be correct in steering during initial use, otherwise, the hydraulic system is stopped, adjusting the phase sequence of any two electric wires of a 380V power supply), and operating for about 1 minute under a non-pressure condition to remove all air in a pipeline.
5. Adjusting the frequency adjusting knob to enable the frequency display meter to be 0, closing the pressure release valve 3, then closing the overflow valve 10 (rotating rightwards to the maximum position and screwing up gently), slowly pressurizing the adjusting frequency adjusting knob to 1.3Mpa, closing the stop valve, disconnecting the variable frequency power switch on the panel of the explosion-proof distribution box, closing the pressure adjustment, maintaining the pressure for 3 minutes and checking whether the system is normal or not.
6. After the check is finished, the overflow valve is slowly adjusted to the maximum opening position, so that the pressure of the system is relieved, the pointers of the first inlet pressure gauge 5 and the second inlet pressure gauge 6 return to zero, the stop valve 4 is opened, and the start/stop switch of the voltage-regulating frequency converter 18 is disconnected.
The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (10)
1. The utility model provides an aircraft refueling joint combined test system which characterized in that includes: the device comprises a refueling joint test seat (1), an outlet pressure gauge (2), a stop valve (4), a first inlet pressure gauge (5), a second inlet pressure gauge (6), a pressure inlet hose (7), a pressure regulating module and a reversing valve (9);
one end of the refueling joint test seat (1) is connected with the outlet pressure gauge (2);
the reversing valve (9) is arranged between the stop valve (4) and the pressure inlet hose (7);
the first inlet pressure gauge (5) and the second inlet pressure gauge (6) are also arranged between the reversing valve (9) and the stop valve (4);
the stop valve (4) is also connected with the pressure regulating module.
2. An aircraft refueling joint comprehensive testing system as set forth in claim 1 further comprising: a pressure relief valve (3) and an overflow valve (10);
the pressure release valve (3) is connected with one end of the refueling joint test seat (1);
the overflow valve (10) is arranged between the reversing valve (9) and the stop valve (4).
3. An aircraft refueling joint comprehensive testing system as set forth in claim 1 further comprising: a quick connector (11);
the pressure inlet hose (7) is fixedly provided with the quick-plugging connector (11).
4. An aircraft refueling joint comprehensive testing system as set forth in claim 1 further comprising: the refueling rubber pipe joint seat (12) is used for being connected with a refueling hose to be tested;
the oil filling rubber pipe joint seat (12) is connected with the reversing valve (9).
5. An aircraft refueling joint comprehensive testing system as set forth in claim 1 further comprising: a ground well plug (13) for blocking the inlet of the ground well joint to be measured and a ground well joint seat (14) connected with the ground well joint to be measured;
the ground well joint seat (14) is arranged in the ground well plug (13), and one end of the ground well joint seat (14) is used for being connected with the pressure inlet hose (7).
6. An aircraft refueling joint comprehensive testing system as set forth in claim 5 further comprising: a disc-shaped oil collecting tray (15);
the oil collecting tray (15) is arranged below the ground well plug (13).
7. The aircraft refueling joint comprehensive testing system of claim 1, wherein the pressure regulating module comprises: the oil pump is characterized by comprising an oil tank (16), an oil pump (17), a voltage regulating frequency converter (18), a motor (19), an oil outlet pipeline (20) and an oil return pipeline (21);
the lower part and the upper part of the oil tank (16) are respectively connected with one end of the oil outlet pipeline (20) and one end of the oil return pipeline (21);
the other end of the oil outlet pipeline (20) and the other end of the oil return pipeline (21) are respectively connected to the stop valve (4);
the oil pump (17) is arranged on the oil outlet pipeline (20);
the voltage-regulating frequency converter (18), the motor (19) and the oil pump (17) are connected in sequence.
8. An aircraft refueling joint comprehensive testing system as set forth in claim 7 further comprising: a check valve (22) and a safety valve (23);
the check valve (22) is arranged on the oil outlet pipeline (20);
the safety valve (23) is arranged on the oil return pipeline (21).
9. An aircraft refueling joint comprehensive testing system as set forth in claim 8 further comprising: a filter (24) and a blow-down valve (25);
the filter (24) is arranged on the oil outlet pipeline (20) between the one-way valve (22) and the stop valve (4);
the blow-down valve (25) is arranged at the bottom of the oil tank (16).
10. An aircraft refueling joint comprehensive testing system as set forth in claim 7 further comprising: a transparent oil return header pipe (26);
and two ends of the transparent oil return main pipe (26) are respectively connected with the oil return pipeline (21) and the oil tank (16).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920818134.2U CN210664925U (en) | 2019-05-31 | 2019-05-31 | Integrated test system for aircraft refueling joint |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201920818134.2U CN210664925U (en) | 2019-05-31 | 2019-05-31 | Integrated test system for aircraft refueling joint |
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| CN210664925U true CN210664925U (en) | 2020-06-02 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110118637A (en) * | 2019-05-31 | 2019-08-13 | 北京壮大瑞业科技发展有限公司 | Aircraft refuelling connector comprehensive test system |
| CN112373722A (en) * | 2020-11-19 | 2021-02-19 | 中国航空油料有限责任公司山东分公司 | Intelligent testing arrangement of aircraft refueling joint pressure |
-
2019
- 2019-05-31 CN CN201920818134.2U patent/CN210664925U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110118637A (en) * | 2019-05-31 | 2019-08-13 | 北京壮大瑞业科技发展有限公司 | Aircraft refuelling connector comprehensive test system |
| CN112373722A (en) * | 2020-11-19 | 2021-02-19 | 中国航空油料有限责任公司山东分公司 | Intelligent testing arrangement of aircraft refueling joint pressure |
| CN112373722B (en) * | 2020-11-19 | 2021-07-27 | 中国航空油料有限责任公司山东分公司 | Intelligent testing arrangement of aircraft refueling joint pressure |
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