CN215851970U - Helicopter fuel system test equipment device - Google Patents
Helicopter fuel system test equipment device Download PDFInfo
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- CN215851970U CN215851970U CN202122370597.7U CN202122370597U CN215851970U CN 215851970 U CN215851970 U CN 215851970U CN 202122370597 U CN202122370597 U CN 202122370597U CN 215851970 U CN215851970 U CN 215851970U
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Abstract
The utility model discloses a helicopter fuel system test device.A fuel storage tank is provided with a fuel port a, a fuel port b, a fuel port c, a fuel port d, a fuel port e, a fuel port f and a fuel port g. The oil port a and the oil port b of the oil storage tank are connected with a pressure oiling/oil pumping system, the oil port c of the oil storage tank is connected with a gravity oiling system, the oil port d and the oil port e of the oil storage tank are connected with a filtering circulation system, the oil port f of the oil storage tank is connected with an oil supply testing system, and the oil port g of the oil storage tank is connected with an oil pumping system. Automatically testing a helicopter fuel system, wherein the testing comprises gravity refueling, metering oil pumping, pressure refueling, pressure oil pumping and oil supply state testing; monitoring, controlling and metering the flow, pressure, temperature, on-off state and fuel quantity; storing the test medium, and performing circulating filtration and detection to ensure that the medium is clean and available; and the temperature of the test medium is controlled to ensure that the fuel temperature is not overheated. The test is automatically controlled, so that the integration, the intellectualization and the high efficiency of the test are realized; and safety monitoring is carried out on a test site, and the safety of the test process and the test site is ensured.
Description
Technical Field
The utility model relates to the field of test equipment, in particular to a test equipment device for a helicopter fuel system.
Background
The current domestic current situation of a fuel system test is as follows: the method depends on more manpower and has lower automation degree. Therefore, according to the functional requirements of the system and different test types, corresponding test procedures are summarized through combing, and a helicopter fuel system test device is designed. The test operator can conveniently and efficiently complete different tests in a standard way.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a helicopter fuel system test device to solve the technical problem.
In order to achieve the purpose, the utility model adopts the following technical scheme: a helicopter fuel system test device comprises an oil storage tank, a pressure oiling/pumping system, a gravity oiling system, a filtering circulation system, an oil supply test system and a pumping system, wherein the oil storage tank is provided with an oil port a, an oil port b, an oil port c, an oil port d, an oil port e, an oil port f and an oil port g. The oil port a and the oil port b of the oil storage tank are connected with a pressure oiling/oil pumping system, the oil port c of the oil storage tank is connected with a gravity oiling system, the oil port d and the oil port e of the oil storage tank are connected with a filtering circulation system, the oil port f of the oil storage tank is connected with an oil supply testing system, and the oil port g of the oil storage tank is connected with an oil pumping system.
The pressure oil filling/pumping system comprises a first electric stop valve, a first oil pump, a first one-way valve, a first filter, a pressure controller, a second electric stop valve, a first electric proportional control valve, a first flowmeter, a first pressure sensor and a first quick-change connector. The oil port a of the accumulator tank is sequentially connected with a first electric stop valve, a first oil pump, a first one-way valve, a first filter, a pressure controller, a second electric stop valve, a first flowmeter, a first pressure sensor and finally a first quick-change connector. And the first proportional regulating valve is connected in parallel to the middle of the first electric stop valve and the first flow meter.
The gravity refueling system comprises a second proportion regulating valve, a second flowmeter, a second pressure sensor, a third electric stop valve, a second quick-change connector, a second oil pump, a second one-way valve, a second oil filter, a third proportion regulating valve, a third flowmeter, a third pressure sensor, a third electric stop valve and a third quick-change connector. And an oil port c in the oil storage tank is sequentially connected with a second oil pump, a second one-way valve, a second oil filter, a third flow meter, a third pressure sensor, a third electric stop valve and a third quick-change connector. And the third proportional control valve is connected in parallel between the oil port b of the oil storage tank and the third flow meter. And an outlet of the pressure controller is sequentially connected with a second proportional control valve and an oil port b of the oil storage tank. And the outlet of the pressure controller is sequentially connected with a second flowmeter, a pressure sensor, a fourth electric stop valve and a second quick-change connector.
The filtering and circulating system comprises an electric three-way ball valve, a third oil pump, an oil cooler and a water distribution filter, and an oil port d of the oil storage tank is sequentially connected with the electric three-way ball valve, the third oil pump, the oil cooler, the water distribution filter and an oil port e of the oil storage tank.
The oil supply testing system comprises a fourth oil pump, a relay oil tank, a fourth flowmeter, a fourth filter, a fourth proportion regulating valve, a fifth oil pump, a fifth proportion regulating valve, a fourth pressure sensor, a fourth quick-change connector, a fifth flowmeter, a fifth filter, a sixth proportion regulating valve, a sixth oil pump, a seventh proportion regulating valve, a fifth pressure sensor and a fifth quick-change connector. Oil storage tank hydraulic fluid port f connects gradually the fourth oil pump, to middle oil tank, and middle oil tank comes out to be connected 2 way oil feed line, connects gradually fourth flowmeter, fourth filter, fifth oil pump, fifth proportional control valve, fourth pressure sensor and fourth quick change coupler the first way. And the fourth proportional control valve is connected in parallel between the fourth filter and the fifth proportional control valve. The second path is sequentially connected with a fifth flowmeter, a fifth filter, a sixth proportion regulating valve, a sixth oil pump, a seventh proportion regulating valve, a fifth pressure sensor and a fifth quick-change connector. And the sixth proportional control valve is connected in parallel between the fifth filter and the seventh proportional control valve.
The oil pumping system comprises a sixth flowmeter, a sixth filter, a seventh oil pump, an eighth proportional control valve, a sixth pressure sensor, a sixth quick-change connector, a seventh flowmeter, a seventh filter, an eighth oil pump, a ninth proportional control valve, a seventh pressure sensor and a seventh quick-change connector. The oil pumping system comprises 2 oil pumping pipelines, wherein the first pipeline is connected with a sixth flowmeter, a sixth filter, a seventh oil pump, an eighth proportional control valve, a sixth pressure sensor and a sixth quick-change connector in sequence from an oil storage tank port g. And the second path of oil is connected with a seventh flowmeter, a seventh filter, an eighth oil pump, a ninth proportional control valve, a seventh pressure sensor and a seventh quick-change connector in sequence from an oil port g of the oil storage tank.
Compared with the prior art, the utility model has the following advantages: automatically testing a helicopter fuel system, wherein the testing comprises gravity refueling, metering oil pumping, pressure refueling, pressure oil pumping and oil supply state testing; monitoring, controlling and metering the flow, pressure, temperature, on-off state and fuel quantity; storing the test medium, and performing circulating filtration and detection to ensure that the medium is clean and available; and the temperature of the test medium is controlled to ensure that the fuel temperature is not overheated. The test is automatically controlled, so that the integration, the intellectualization and the high efficiency of the test are realized; and safety monitoring is carried out on a test site, and the safety of the test process and the test site is ensured.
Drawings
FIG. 1 is a schematic diagram of the device of the present invention.
FIG. 2 is a schematic view of the pressure/oil pumping system and the gravimetric refueling system of the present invention.
FIG. 3 is a schematic diagram of the oil supply testing system of the present invention.
FIG. 4 is a schematic diagram of an oil pumping system of the present invention.
In the figure: A. a pressure oil filling/pumping system, a B weight oil filling system, a C filtering circulation system, a D oil supply testing system, an E oil pumping system, a 1 oil storage tank, a 2 first electric stop valve, a 3 first oil pump, a 4 first check valve, a 5 first filter, a 6 pressure controller, a 7 second electric stop valve, a 8 first ratio adjusting valve, a 9 first flow meter, a 10 first pressure sensor, a 11 first quick-change connector, a 12 second ratio adjusting valve, a 13 second flow meter, a 14 second pressure sensor, a 15 third electric stop valve, a 16 second quick-change connector, a 17 second oil pump, a 18 second check valve, a 19 second oil filter, a 20 third ratio adjusting valve, a 21, a third flow meter, a 22, a third pressure sensor, a 23 fourth electric quick-change connector, a 24 third quick-change connector, 25. 26, a third oil pump, 27, an oil cooler, 28, a water diversion filter, 29, a fourth oil pump, 30, a relay oil tank, 31, a fourth flowmeter, 32, a fourth filter, 33, a fourth proportion regulating valve, 34, a fifth oil pump, 35, a fifth proportion regulating valve, 36, a fourth pressure sensor, 37, a fourth quick-change connector, 38, a fifth flowmeter, 39, a fifth filter, 40, a sixth proportion regulating valve, 41, a sixth oil pump, 42, a seventh proportion regulating valve, 43, a fifth pressure sensor, 44 and a fifth quick-change connector. 45. A sixth flow meter, 46, a sixth filter, 47, a seventh oil pump, 48, an eighth proportional control valve, 49, a sixth pressure sensor, 50, a sixth quick-change coupling, 51, a seventh flow meter, 52, a seventh filter, 53, an eighth oil pump, 54, a ninth proportional control valve, 55, a seventh pressure sensor, 56, a seventh quick-change coupling.
Detailed Description
The utility model is explained in further detail below with reference to the figures and the specific embodiments.
The helicopter fuel system test equipment device comprises an oil storage tank 1, a pressure oiling/oil pumping system A, a gravity oiling system B, a filtering circulation system C, an oil supply test system D and an oil pumping system E, wherein the oil storage tank 1 is provided with an oil port a, an oil port B, an oil port C, an oil port D, an oil port E, an oil port f and an oil port g. An oil port a and an oil port B of the oil storage tank 1 are connected with the pressure oiling/oil pumping system A, an oil port C of the oil storage tank 1 is connected with the gravity oiling system B, an oil port D and an oil port E of the oil storage tank 1 are connected with the filtering and circulating system C, an oil port f of the oil storage tank 1 is connected with the oil supply testing system D, and an oil port g of the oil storage tank 1 is connected with the oil pumping system E.
The pressure oil filling/pumping system A comprises a first electric stop valve 2, a first oil pump 3, a first one-way valve 4, a first filter 5, a pressure controller 6, a second electric stop valve 7, a first proportional control valve 8, a first flow meter 9, a first pressure sensor 10 and a first quick-change connector 11. The oil port a of the accumulator tank 1 is sequentially connected with a first electric stop valve 2, a first oil pump 3, a first one-way valve 4, a first filter 5, a pressure controller 6, a second electric stop valve 7, a first flow meter 9, a first pressure sensor 10 and finally a first quick-change connector 11. The first proportional regulating valve 8 is connected in parallel to the middle of the first electric shutoff valve 2 and the first flow meter 9.
The gravity refueling system B comprises a second proportion regulating valve 12, a second flowmeter 13, a second pressure sensor 14, a third electric stop valve 15, a second quick-change connector 16, a second oil pump 17, a second one-way valve 18, a second oil filter 19, a third proportion regulating valve 20, a third flowmeter 21, a third pressure sensor 22, a third electric stop valve 23 and a third quick-change connector 24. An oil port c of the oil storage tank 1 is sequentially connected with a second oil pump 17, a second one-way valve 18, a second oil filter 19, a third flow meter 21, a third pressure sensor 22, a third electric stop valve 15 and a third quick-change connector 24. The third proportional control valve 20 is connected in parallel between the oil port b of the oil storage tank 1 and the third flow meter 21. And the outlet of the pressure controller 6 is sequentially connected with a second proportional control valve 12 and an oil port b of the oil storage tank 1. And the outlet of the pressure controller 6 is connected with a second flow meter 13, a pressure sensor 14, a fourth electric stop valve 15 and a second quick-change connector 16 in sequence.
Filtration circulation system C contains electronic tee bend ball valve 25, third oil pump 26, oil-cooling machine 27, water diversion filter 28, 1 hydraulic fluid port d of oil storage tank connects gradually electronic tee bend ball valve 25, third oil pump 26, oil-cooling machine 27, water diversion filter 28 and oil storage tank hydraulic fluid port e.
The oil supply test system D includes a fourth oil pump 29, a relay oil tank 30, a fourth flow meter 31, a fourth filter 32, a fourth proportional control valve 33, a fifth oil pump 34, a fifth proportional control valve 35, a fourth pressure sensor 36, a fourth quick-change coupling 37, a fifth flow meter 38, a fifth filter 39, a sixth proportional control valve 40, a sixth oil pump 41, a seventh proportional control valve 42, a fifth pressure sensor 43, and a fifth quick-change coupling 44. The oil port f of the oil storage tank 1 is sequentially connected with a fourth oil pump 29 and a relay oil tank 30, the relay oil tank 30 is connected with a 2-way oil supply pipeline, and the first way is sequentially connected with a fourth flowmeter 31, a fourth filter 32, a fifth oil pump 34, a fifth proportional control valve 35, a fourth pressure sensor 36 and a fourth quick-change connector 37. And a fourth proportional control valve 33 connected in parallel between the fourth filter 32 and the fifth proportional control valve 35. The second path is connected with a fifth flowmeter 38, a fifth filter 39, a sixth oil pump 41, a seventh proportional control valve 42, a fifth pressure sensor 43 and a fifth quick-change connector 44 in sequence. And a fourth proportional control valve 33 connected in parallel between the fourth filter 32 and the fifth proportional control valve 35.
The oil pumping system E comprises a sixth flow meter 45, a sixth filter 46, a seventh oil pump 47, an eighth proportional control valve 48, a sixth pressure sensor 49, a sixth quick-change coupling 50, a seventh flow meter 51, a seventh filter 52, an eighth oil pump 53, a ninth proportional control valve 54, a seventh pressure sensor 55 and a seventh quick-change coupling 56. The oil pumping system E comprises 2 oil pumping pipelines, wherein the first oil pipeline is connected with a sixth flowmeter 45, a sixth filter 46, a seventh oil pump 47, an eighth proportional control valve 48, a sixth pressure sensor 49 and a sixth quick-change connector 50 from an oil port g of the oil storage tank 1 in sequence. The second path is connected from the oil port g of the oil storage tank 1 to a seventh flowmeter 51, a seventh filter 52, an eighth oil pump 53, a ninth proportional control valve 54, a seventh pressure sensor 55 and a seventh quick-change connector 56 in sequence.
As shown in fig. 1 to 4, the specific process of testing by the system of the present invention is as follows:
the oil storage tank is used for storing fuel oil for the test, and the oil flows back to the port e of the oil storage tank from the oil port d of the oil storage tank through the circulating filter system C. The fuel in the oil storage tank is circularly filtered, the temperature of the fuel is monitored and displayed, and the fuel is cooled when the temperature of the fuel is overhigh. The temperature control system is integrated in the circulating filter pipeline, and is used for cooling when the fuel temperature reaches an upper limit and stopping cooling when the fuel temperature is reduced to a specified temperature.
The gravity pipeline comprises 2 pipelines and a pump, each pipeline can be independently controlled and metered and can also be comprehensively controlled and metered, and the flow rate is linearly adjustable; and gravity oiling is carried out on the oil tank on the machine through a gravity oiling port. The first path is as follows: oil liquid passes through a first electric stop valve 2, a first oil pump 3, a first check valve 4, a first filter 5, a pressure controller 6, a second flowmeter 13, a second pressure sensor 14, a third electric stop valve 15, a second quick-change connector 16 and is finally connected to a gravity oil filling port of an airplane from an a port of an oil storage tank 1, and a first gravity oil filling test is realized. The second proportional control valve 12 is used for regulating the pipeline pressure and has a protection function. And a second path: the oil liquid passes through a second oil pump 17, a second one-way valve 18, a second oil filter 19, a third flow meter 21, a third pressure sensor 22, a third electric stop valve 23 and a third quick-change connector 24 in sequence from an oil port c in the oil storage tank 1 and is finally connected to a gravity oil filling port of the airplane, so that the gravity oil filling test of a second path is realized. And the third proportional control valve 20 is used for regulating the pipeline pressure and playing a role in protection.
The pressure oiling/oil pumping test system comprises 1 path of pressure pipeline and can perform pressure oiling and oil pumping on an oil tank on the machine; the constant flow/constant pressure oiling can be realized, and the oiling amount, flow and pressure can be measured; the oil filling amount and pressure can be controlled manually on site, and can also be controlled remotely through a comprehensive control system; the oiling pressure is linearly adjustable within a set range; when the maximum pressure of the oil circuit system exceeds the specified pressure, the alarm is sent, and the pressure controller 6 ensures that the pressure is stabilized within the specified pressure. The first proportional control valve 8 can control pressure during negative pressure oil pumping, and can automatically stop oil pumping when an oil-free vacuum state is judged. When pressure refueling is carried out: the oil liquid passes through a first electric stop valve 2, a first oil pump 3, a first check valve 4, a first filter 5, a pressure controller 6, a second electric stop valve 7, a first flow meter 9, a first pressure sensor 10, a first quick-change connector 11 and a pressure oil port connected to the airplane finally from an a port of the oil storage tank. The aircraft is subjected to a pressure fueling test. When pressure oil pumping is performed: the oil liquid passes through a first quick-change connector 11, a first pressure sensor 10, a first flow meter 9, a first proportion adjusting valve 8, a first oil pump 3, a first check valve 4, a first filter 5, a pressure controller 6, a second proportion adjusting valve 12 and finally is drawn back to a port b of the oil storage tank from an aircraft pressure oil port in sequence.
The oil supply test system comprises 2 independent oil supply pipelines. The system is used for checking the oil supply condition of the engine/APU when the fuel system works normally and abnormally, and simulating and checking the pipeline oil supply condition when the engine/APU works; configuring a standard oil pipe and a universal joint to be matched with an on-board engine/APU oil supply pipeline; set up special switching pipe, the switching pipe is transparent material and is unanimous with quick-witted upper pipe way pipe diameter, but the oil feeding condition of visual observation. The oil supply test system realizes controllable active constant flow oil pumping, can ensure smooth oil path and measure and calculate the oil mass and pressure under the condition of closing the oil pump of the equipment; the selection valve is arranged, so that the functions of direct measurement and oil pumping measurement can be realized. The first path is as follows: when the engine is actively supplied with oil, oil is sucked out from an oil outlet of the aircraft 1, passes through the fourth quick-change connector 37, the fourth pressure sensor 36, the fifth proportional control valve 35, the fourth proportional control valve 33, the fourth filter 32 and the fourth flow meter 31 in sequence, and flows to the intermediate oil tank 30. And finally through the oil pump 29 back to the oil reservoir 1. When the oil tank of the airplane 1 is used for pumping oil under negative pressure, the oil is sucked out from the oil tank of the airplane 1, passes through the fourth quick-change connector 37, the fourth pressure sensor 36, the fifth proportional control valve 35, the fifth oil pump 34, the fourth filter 32 and the fourth flow meter 31 in sequence, flows into the intermediate oil tank 30, passes through the fourth oil pump 29, and is pumped back to the oil storage tank 1. The second path is the same as the first path.
The oil pumping test system comprises 2 independent pipelines and an oil pump, and oil pumping is carried out on an oil tank on the oil pumping test system through an oil discharge switch or an oil discharge valve. The oil pumping amount can be manually controlled and set on site, and the oil pumping amount can also be remotely set through a comprehensive control system to automatically control oil pumping; the oil circuit is provided with pressure compensation or safety limit design, so that the condition that the system on the machine is damaged due to overlarge oil pumping pressure is prevented; each pipeline can be independently controlled and metered or comprehensively controlled and metered; the flow and pressure signals are collected to a control system, segmented or continuous recording and control can be performed, and pressure warning and emergency treatment can be performed. The first path is as follows: the oil liquid passes through a sixth quick-change connector 50, a sixth pressure sensor 49, an eighth proportional control valve 48, a seventh oil pump 47, a sixth filter 46, a sixth flow meter 45 and is finally pumped back to the oil storage tank from the aircraft oil tank. The test function of pumping is realized. The second path is the same as the first path.
The foregoing is a preferred embodiment of the present invention, and it will be apparent to those skilled in the art that variations, modifications, substitutions and alterations can be made in the embodiment without departing from the principles and spirit of the utility model.
Claims (6)
1. The utility model provides a helicopter fuel oil system test equipment device, includes oil storage tank (1), pressure refueling/oil pumping system a, gravity refueling system b, filtration cycle system c, fuel feeding test system d and oil pumping system e, its characterized in that: the oil storage tank (1) is provided with an oil port a, an oil port b, an oil port c, an oil port d, an oil port e, an oil port f and an oil port g, the oil port a and the oil port b of the oil storage tank (1) are connected with a pressure oil filling/pumping system a, the oil port c of the oil storage tank (1) is connected with a gravity oil filling system b, the oil port d and the oil port e of the oil storage tank (1) are connected with a filtering circulation system c, the oil port f of the oil storage tank (1) is connected with an oil supply testing system d, and the oil port g of the oil storage tank (1) is connected with a pumping system e.
2. A helicopter fuel system test rig apparatus as claimed in claim 1, wherein: the pressure oil filling/pumping system a comprises a first electric stop valve (2), a first oil pump (3), a first one-way valve (4), a first filter (5), a pressure controller (6), a second electric stop valve (7), a first proportional control valve (8), a first flowmeter (9), a first pressure sensor (10) and a first quick-change connector (11), an oil port a of the oil storage tank (1) is sequentially connected with a first electric stop valve (2), a first oil pump (3), a first one-way valve (4), a first filter (5), a pressure controller (6), a second electric stop valve (7), a first flow meter (9), a first pressure sensor (10) and a first quick-change connector (11), the first proportional control valve (8) is connected in parallel to the middle of the first electric stop valve (2) and the first flow meter (9).
3. A helicopter fuel system test rig apparatus as claimed in claim 2, wherein: the gravity oiling system b comprises a second proportion regulating valve (12), a second flow meter (13), a second pressure sensor (14), a third electric stop valve (15), a second quick-change connector (16), a second oil pump (17), a second one-way valve (18), a second oil filter (19), a third proportion regulating valve (20), a third flow meter (21), a third pressure sensor (22), a third electric stop valve (15) and a third quick-change connector (24), oil ports c in the oil storage tank (1) are sequentially connected with the second oil pump (17), the second one-way valve (18), the second oil filter (19), the third flow meter (21), the third pressure sensor (22), the third electric stop valve (15) and the third quick-change connector (24), the third proportion regulating valve (20) is connected in parallel between the oil ports b of the oil storage tank (1) and the third flow meter (21), the outlet of the pressure controller (6) is sequentially connected with a second proportional control valve (12) and an oil port b of the oil storage tank (1), and the outlet of the pressure controller (6) is sequentially connected with a second flowmeter (13), a second pressure sensor (14), a third electric stop valve (15) and a second quick-change connector (16).
4. A helicopter fuel system test rig apparatus as claimed in claim 1, wherein: filtration circulation system c includes electronic tee bend ball valve (25), third oil pump (26), oil cooler (27), water diversion filter (28), oil storage tank (1) hydraulic fluid port d connects gradually electronic tee bend ball valve (25), third oil pump (26), oil cooler (27), water diversion filter (28) and oil storage tank hydraulic fluid port e.
5. A helicopter fuel system test rig apparatus as claimed in claim 1, wherein: the oil supply test system d comprises a fourth oil pump (29), a relay oil tank (30), a fourth flowmeter (31), a fourth filter (32), a fourth proportional control valve (33), a fifth oil pump (34), a fifth proportional control valve (35), a fourth pressure sensor (36), a fourth quick-change connector (37), a fifth flowmeter (38), a fifth filter (39), a sixth proportional control valve (40), a sixth oil pump (41), a seventh proportional control valve (42), a fifth pressure sensor (43) and a fifth quick-change connector (44), wherein an oil port (f) of the oil storage tank (1) is sequentially connected with the fourth oil pump (29) and the relay oil tank (30), the relay oil tank (30) is connected with 2 oil supply pipelines, and the first pipeline is sequentially connected with the fourth flowmeter (31), the fourth filter (32), the fifth oil pump (34), the fifth proportional control valve (35), The second path is connected with a fifth flowmeter (38), a fifth filter (39), a sixth oil pump (41), a seventh proportional control valve (42), a fifth pressure sensor (43) and a fifth quick-change connector (44) in sequence, and the fourth proportional control valve (33) is connected in parallel between the fourth filter (32) and the fifth proportional control valve (35).
6. A helicopter fuel system test rig apparatus as claimed in claim 1, wherein: the oil pumping system e comprises a sixth flow meter (45), a sixth filter (46), a seventh oil pump (47), an eighth proportional control valve (48), a sixth pressure sensor (49), a sixth quick-change connector (50), a seventh flow meter (51), a seventh filter (52), an eighth oil pump (53), a ninth proportional control valve (54), a seventh pressure sensor (55) and a seventh quick-change connector (56), the oil pumping system e comprises a 2-way oil pumping pipeline, a first way oil port g of a slave oil storage tank (1) is sequentially connected with the sixth flow meter (45), the sixth filter (46), the seventh oil pump (47), the eighth proportional control valve (48), the sixth pressure sensor (49) and the sixth quick-change connector (50), and a second way oil port g of the slave oil storage tank (1) is sequentially connected with the seventh flow meter (51), the seventh filter (52), the eighth oil pump (53), A ninth proportional regulating valve (54), a seventh pressure sensor (55) and a seventh quick-change coupling (56).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122370597.7U CN215851970U (en) | 2021-09-29 | 2021-09-29 | Helicopter fuel system test equipment device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122370597.7U CN215851970U (en) | 2021-09-29 | 2021-09-29 | Helicopter fuel system test equipment device |
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| Publication Number | Publication Date |
|---|---|
| CN215851970U true CN215851970U (en) | 2022-02-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122370597.7U Active CN215851970U (en) | 2021-09-29 | 2021-09-29 | Helicopter fuel system test equipment device |
Country Status (1)
| Country | Link |
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| CN (1) | CN215851970U (en) |
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2021
- 2021-09-29 CN CN202122370597.7U patent/CN215851970U/en active Active
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Effective date of registration: 20220721 Address after: 510475 No. 2, yangwugang Road, Benghu Town, Baiyun District, Guangzhou, Guangdong Province Patentee after: Guangzhou paiwei Intelligent Technology Co.,Ltd. Address before: Room 1204, block a, Changfeng International Plaza, 86A, Chang'an South Road, Yanta District, Xi'an City, Shaanxi Province, 710061 Patentee before: Xi'an paiwei Electromechanical Technology Co.,Ltd. |