CN218865487U - Aircraft tank service truck combined test platform - Google Patents
Aircraft tank service truck combined test platform Download PDFInfo
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- CN218865487U CN218865487U CN202223564847.1U CN202223564847U CN218865487U CN 218865487 U CN218865487 U CN 218865487U CN 202223564847 U CN202223564847 U CN 202223564847U CN 218865487 U CN218865487 U CN 218865487U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The utility model discloses an aircraft tank service truck combined test platform, this kind of aircraft tank service truck combined test platform, through removing the testboard appointed work area, use fender wheel ware chucking truckle, put down the adjustable ground of support frame both sides and prop to level ground and ensure steadily, extract the safety catch on the flexible platform, pull out required operating position with flexible platform, reinsert the safety catch location, the adjustable ground of putting down flexible platform one side props to level ground and ensures steadily again, will lead the static electric wire of leading in the static electric wire reel and pull out and press from both sides and connect at appointed hookup location, prevent to lead static, close ball valve and butterfly valve, the oil outlet rubber pipe and the oil feed of tank service truck refuel articulate, the aircraft is connected through the oil feed rubber pipe to the oil feed refuel joint, reopen ball valve and butterfly valve, observe the pressure display of manometer, whether unanimous with the data that detect before, thereby accomplish the test to tank service truck pressure control system.
Description
Technical Field
The utility model relates to a tank service truck test technical field especially relates to an aircraft tank service truck combined test platform.
Background
According to the civil aviation industry standard MH/T6005-2009 of the people's republic of China, the civil aircraft refueling standard, and the annex B (normative annex) refueling equipment maintenance rule, people need to regularly perform flow tests on a refueller pressure control system and a dead demann control valve to check the performance condition in the whole flow rate range, and after any maintenance of the refueller, the pressure control equipment is adjusted, or all changes which may affect the control system such as the replacement of a refueller rubber tube and the like, and similar tests are performed.
SUMMERY OF THE UTILITY MODEL
In order to achieve the purpose, the utility model provides a convenient aircraft tank service truck combined test platform to tank service truck pressure control system test.
In order to solve the technical problem, the utility model provides a following technical scheme: the utility model provides an aircraft tank service truck combined test platform, includes the support frame, be equipped with the lower test tube assembly and the last test tube assembly of intercommunication on the support frame, be equipped with butterfly valve and ball valve between lower test tube assembly and the last test tube assembly, test tube assembly one end is equipped with a plurality of oil intakes and refuels the joint down for connect the tank service truck rubber tube that produces oil, it is equipped with a plurality of oil offals and refuels joint to go up test tube assembly one end for connect aircraft oil intake rubber tube, upward be equipped with the manometer on the test tube assembly for detect the oil transportation pressure.
Preferably, one side of the support frame is horizontally provided with a telescopic platform in a sliding manner, and the telescopic platform is fixed through a safety pin.
Preferably, the bottom surface of the support frame is provided with a plurality of casters.
Preferably, both sides of the support frame and one side of the telescopic platform are provided with adjustable ground supports.
Preferably, one side of the support frame is provided with a static conducting wire winding drum.
Preferably, the supporting frame is provided with a collecting box for placing the wheel stopper.
Preferably, one side of the support frame, which is far away from the telescopic platform, is provided with a push-pull rod.
Compared with the prior art, the utility model discloses the beneficial effect that can reach is:
the utility model discloses a remove the testboard to appointed work area, use and keep off wheel ware chucking truckle, put down the adjustable ground of support frame both sides and prop to level ground and ensure steadily, extract the safety catch on the flexible platform, pull out required operating position with flexible platform, reinsert the safety catch location, the adjustable ground of putting down flexible platform one side again props to level ground and ensures steadily, will lead the static electric wire of leading in the static electric wire reel and pull out and press from both sides and connect at appointed hookup location, prevent to lead static, close ball valve and butterfly valve, the oil outlet rubber pipe and the oil feed of tank service truck refuel and connect, it connects the aircraft to go out the oil feed rubber pipe, open ball valve and butterfly valve again, observe the pressure display of manometer, whether unanimous with the data of periodic detection before, thereby accomplish the test to tank service truck pressure control system.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
wherein: 1. a support frame; 2. a lower test pipe assembly; 3. an upper test pipe assembly; 4. a butterfly valve; 5. a ball valve; 6. an oil inlet and filling joint; 7. an oil outlet and filling joint; 8. a pressure gauge; 9. a telescopic platform; 10. a conductive electrostatic wire reel; 11. a caster wheel; 12. an adjustable ground support; 13. a collection box; 14. a push-pull rod.
Detailed Description
In order to make the technical means, the creation features, the achievement purposes and the functions of the invention easy to understand, the invention is further explained below with reference to the specific embodiments, but the following embodiments are only the preferred embodiments of the invention, not all. Based on the embodiments in the implementation, other embodiments obtained by those skilled in the art without any creative work belong to the protection scope of the present invention. The experimental methods in the following examples are conventional methods unless otherwise specified, and materials, reagents and the like used in the following examples are commercially available unless otherwise specified.
The embodiment is as follows:
as shown in fig. 1, the utility model provides an aircraft refueling truck comprehensive test bench, which comprises a support frame 1, wherein a lower test pipeline assembly 2 and an upper test pipeline assembly 3 which are communicated with each other are arranged on the support frame 1, a butterfly valve 4 and a ball valve 5 are arranged between the lower test pipeline assembly 2 and the upper test pipeline assembly 3, one end of the lower test pipeline assembly 2 is provided with a plurality of oil inlet refueling joints 6 for connecting oil outlet rubber pipes of refueling trucks, one end of the upper test pipeline assembly 3 is provided with a plurality of oil outlet refueling joints 7 for connecting the aircraft oil inlet rubber pipes, and the upper test pipeline assembly 3 is provided with a pressure gauge 8 for detecting oil delivery pressure;
all pipelines and equipment are stainless steel, aluminum or carbon steel sprayed with epoxy resin;
oil is simulated to be slowly added into the aircraft through the control of the ball valve 5, and oil is simulated to be rapidly added into the aircraft through the butterfly valve 4;
the oil inlet refueling joint 6 and the oil outlet refueling joint 7 both adopt HJS-63A aviation pressure refueling joints, the specific using method is the prior art, redundant description is omitted again, and after the test work is finished, dust covers need to be covered on the oil inlet refueling joint 6 and the oil outlet refueling joint 7 to prevent dust from entering the oil inlet refueling joint 6 and the oil outlet refueling joint 7;
as shown in fig. 1, the bottom surface of the support frame 1 is provided with a plurality of casters 11, so that the whole device can be conveniently moved, and the maximum walking speed of the device is not more than 5km/h;
a push-pull rod 14 is arranged on one side of the support frame 1, which is far away from the telescopic platform 9, and the whole device is conveniently pushed to move through the push-pull rod 14;
as shown in fig. 1, a telescopic platform 9 is horizontally arranged on one side of the support frame 1 in a sliding manner, and the telescopic platform 9 is fixed through a safety pin;
the two sides of the support frame 1 and one side of the telescopic platform 9 are both provided with adjustable ground supports 12, so that the support frame 1 and the telescopic platform 9 are stably positioned on the ground, when the test board moves to a specified position, the adjustable ground supports 12 are adjusted to contact the ground to support the whole device, at the moment, the caster wheels 11 are suspended, the stability of the device is ensured, and the whole device can not shake when people stand on the telescopic platform 9 conveniently, wherein the adjustable ground supports 12 are the prior art and are common lead screw lifting mechanisms, and are not described in more detail herein;
the telescopic platform 9 is pulled out of the support frame 1, and then the telescopic platform 9 is fixed by using a safety pin, so that a worker can conveniently stand on the telescopic platform 9 to connect the oil outlet and filling joint 7 with an oil inlet rubber pipe of an airplane;
as shown in fig. 1, one side of the support frame 1 is provided with a static electricity conducting wire reel 10 on which a static electricity conducting wire is wound for grounding, preventing static electricity conduction and avoiding combustion or explosion of fuel oil caused by static electricity;
as shown in fig. 1, the supporting frame 1 is provided with a collecting box 13 for placing a wheel stopper, the wheel stopper is used for limiting the movement of the caster 11, and the wheel stopper is matched with the adjustable ground support 12 for use, so that the device is further placed stably;
when the device is used, the pressure control system of the refueling truck and the dead man control valve need to be subjected to flow test regularly or after the refueling truck is maintained at any time, pressure control equipment is adjusted, or the condition such as the replacement of a refueling truck rubber pipe is changed, the test platform is moved to a designated working area, the caster 11 is clamped by using the wheel blocking device, the adjustable supports 12 on the two sides of the support frame 1 are put down to the horizontal ground to ensure the stability, the safety pin on the telescopic platform 9 is pulled out, the telescopic platform 9 is pulled out of a required working position and then is inserted into the safety pin for positioning, the adjustable support 12 on one side of the telescopic platform 9 is put down to the horizontal ground to ensure the stability, a worker can conveniently stand on the telescopic platform 9 to connect the oil outlet refueling joint 7 with the airplane through the oil inlet rubber pipe, the static conducting wire in the static conducting wire reel 10 is pulled out and clamped at the designated connecting position to prevent static conducting, the ball valve 5 and the butterfly valve 4 are closed, the oil outlet rubber pipe of the refueling truck is connected with the oil inlet rubber pipe 6, the oil outlet refueling joint 7 is connected with the airplane through the rubber pipe, the oil inlet rubber pipe 5 and the butterfly valve 4 is opened to observe whether the pressure of the ball valve 8 is consistent with the pressure of the pressure test system, and simultaneously to observe whether the pressure of the medium of the refueling truck to detect the pressure of the pressure meter to observe whether the pressure of the refueling truck to observe whether the medium to detect the medium.
It should be noted that when the tested vehicle is equipped with the dual pressure control system, each system should be tested individually, and should not be affected by other pressure control valve systems, when testing the Hose End Pressure Control Valve (HEPCV), the in-line pressure control valve (ILPCV) system should be adjusted such that the outlet pressure { at least 0.7bar (10 lbf/in2} is greater than the test limit value of the Hose End Pressure Control Valve (HEPCV), for the pressure compensation system, it can be achieved by adjusting the air pressure to 6.9bar (100 lbf/in 2), when testing the in-line pressure control valve (ILPCV) system, a bypass or a blocking device should be used to eliminate the influence of the Hose End Pressure Control Valve (HEPCV) on the test, and the pressure value on the pressure gauge 8 of the testing device should be recorded;
when testing the Hose End Pressure Control Valve (HEPCV):
adjusting an in-line pressure control valve (ILPCV) (if installed), testing each valve in a Hose End Pressure Control Valve (HEPCV) system for water hammer pressure control due to rapid closure of aircraft tank valves, fully opening a butterfly valve 4 and a ball valve 5, connecting each hose in sequence, testing at a maximum flow rate, adjusting the butterfly valve 4 to a position where the flow rate begins to drop, closing the ball valve 5 within a closing time of 2-4S, wherein the maximum water hammer pressure indicated by a pressure gauge 8 of the testing device should not exceed 8.3bar (120 lbf/in 2), recording the water hammer pressure value, and fully opening the butterfly valve 4 to release pressure;
similarly, a pressure control test is performed on each Hose End Pressure Control Valve (HEPCV) within a flow rate range, each hose is connected in turn, the ball valve 5 is slowly closed within 30S from the maximum flow rate, then the butterfly valve 4 is closed, the pressure displayed by the pressure gauge 8 of the test device during closing should not exceed 3.5bar (50 lbf/in 2) except that the pressure is between 3.5bar (50 lbf/in 2) and 4.2bar (60 lbf/in 2) when the flow rate is very low (before closing), the pressure does not exceed 4.2bar (60 lbf/in 2) when the butterfly valve 4 and the ball valve 5 are completely closed, the pressure at closing is recorded, the ball valve 5 and the butterfly valve 430S are closed and the pressure is recorded, if the pressure increases under no flow, the pressure is called 'peristaltic pressure' of 0.35bar (5 lbf/in 2);
after the test work of a rubber tube end pressure control valve (HEPCV) is finished, adjusting the air pressure of an online pressure control valve (ILPCV) to be in a correct setting, and sealing or locking at the position;
when testing an in-line pressure control valve (ILPCV):
the inline pressure control valve (ILPCV) is disabled by using a bypass or shut-off device, a pressure control test is performed on the inline pressure control valve (ILPCV) system over a range of flow rates, the connected hoses are cycled at a maximum flow rate (e.g., two platform hoses or two reel hoses), and more than one venturi (or other device) is used as an inline pressure control valve (ILPCV) compensation system (e.g., one reel hose and one platform hose), and the venturi tests are performed separately, based on the differences in venturi design { e.g., if the venturi is designed for two hoses, two platform hoses must be connected and the Hose End Pressure Control Valve (HEPCV) is disabled }, the set mode during the test is very important, the butterfly valve 4 and the ball valve 5 are fully opened, the valve B is adjusted to a position at which the flow rate begins to drop, the flow rate is gradually reduced using the ball valve 5, and the pressure value indicated by the test set pressure gauge 8 is recorded during the period from maximum to zero.
For an in-line pressure control valve (ILPCV) compensation system, the pressure value recorded at full flow should not exceed 3.8bar (55 lbf/in 2) as indicated by the test rig pressure gauge, should not exceed 4.5bar (65 lbf/in 2) when closed, and if the recorded pressure value exceeds the limit, the system should be adjusted by qualified personnel and then retested.
For the pressure values indicated by the venturi gauges of the venturi compensation system, the recorded pressure values indicated by the measuring device pressure gauge 8 should not exceed 0.3bar (5 lbf/in 2) between 2.4bar (35 lbf/in 2) and 3.8bar (55 lbf/in 2) and when closed.
For a compensation system without an in-line pressure control valve (ILPCV), the pressure values recorded at maximum flow rate as indicated by the test unit pressure gauge and the oil pressure gauge should not exceed 3.8bar (55 lbf/in 2) and should not exceed 5.5bar (80 lbf/in 2) when closed.
And (3) completely opening the ball valve 5 to release pressure, closing the butterfly valve 4 within 2-4S from the full flow rate, and recording the highest water hammer pressure value displayed instantly by the pressure gauge 8 of the testing device.
After the in-line pressure control valve (ILPCV) test is completed, the in-line pressure control valve (ILPCV) bypass or shut-off device should be removed.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. The utility model provides an aircraft tank service truck combined test platform, includes support frame (1), its characterized in that: be equipped with lower test tube assembly (2) and last test tube assembly (3) of intercommunication on support frame (1), be equipped with butterfly valve (4) and ball valve (5) between test tube assembly (2) and last test tube assembly (3) down, test tube assembly (2) one end is equipped with a plurality of oil intakes and refuels joint (6) down for connect the tank service truck rubber tube that produces oil, it is equipped with a plurality of oil offals and refuels joint (7) to go up test tube assembly (3) one end, be used for connecting aircraft oil intake rubber tube, be equipped with manometer (8) on last test tube assembly (3) for detect the oil transportation pressure.
2. An aircraft fuelling vehicle integrated test stand according to claim 1 wherein: one side of the support frame (1) horizontally slides to be provided with a telescopic platform (9), and the telescopic platform (9) is fixed through a safety pin.
3. An aircraft fuelling vehicle combined test stand according to claim 2 wherein: the bottom surface of the support frame (1) is provided with a plurality of trundles (11).
4. An aircraft fuelling vehicle combined test stand according to claim 3 wherein: both sides of the support frame (1) and one side of the telescopic platform (9) are provided with adjustable ground supports (12).
5. An aircraft fuelling vehicle combined test stand according to claim 1 wherein: one side of the support frame (1) is provided with a static conducting wire winding drum (10).
6. An aircraft fuelling vehicle combined test stand according to claim 1 wherein: the supporting frame (1) is provided with a collecting box (13) for placing a catch wheel device.
7. An aircraft fuelling vehicle integrated test stand according to claim 2 wherein: and a push-pull rod (14) is arranged on one side of the support frame (1) far away from the telescopic platform (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223564847.1U CN218865487U (en) | 2022-12-30 | 2022-12-30 | Aircraft tank service truck combined test platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223564847.1U CN218865487U (en) | 2022-12-30 | 2022-12-30 | Aircraft tank service truck combined test platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218865487U true CN218865487U (en) | 2023-04-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223564847.1U Active CN218865487U (en) | 2022-12-30 | 2022-12-30 | Aircraft tank service truck combined test platform |
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| Country | Link |
|---|---|
| CN (1) | CN218865487U (en) |
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2022
- 2022-12-30 CN CN202223564847.1U patent/CN218865487U/en active Active
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