CN201788411U - Hydraulic test system of fuel controller - Google Patents

Hydraulic test system of fuel controller Download PDF

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Publication number
CN201788411U
CN201788411U CN2010205075209U CN201020507520U CN201788411U CN 201788411 U CN201788411 U CN 201788411U CN 2010205075209 U CN2010205075209 U CN 2010205075209U CN 201020507520 U CN201020507520 U CN 201020507520U CN 201788411 U CN201788411 U CN 201788411U
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China
Prior art keywords
valve
pipeline
pressure
fuel
fuel controller
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Expired - Fee Related
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CN2010205075209U
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Chinese (zh)
Inventor
石建友
万波
叶池旺
李秋菊
周琳
雷建军
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Wuhan Hangda Aero Science & Technology Development Co Ltd
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Wuhan Hangda Aero Science & Technology Development Co Ltd
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Abstract

The utility model relates to a hydraulic test system of an airplane APU (auxiliary power unit) fuel controller (hereinafter referred to as a fuel controller). The hydraulic test system includes a lube oil loop connected with a lube oil inlet and a lube oil return opening of an adapter, a fuel supplying loop for providing a hydraulic source to the fuel controller, an actuator testing loop for testing the load-carrying performance of an actuator, a backpressure loop for testing the loading carrying performance of an oil outlet of the fuel controller, a pressure testing loop for testing the pressure and the pressure difference of the fuel controller, a pump running-in and performance testing loop for testing the running-in and performance of an internal gear pump of the fuel controller. The hydraulic test system meets the testing requirements of performance characteristics of the airplane APU fuel controller, can test the integrated performance of the airplane fuel controller and the pump running-in and performance, and is user-friendly.

Description

Fuel controller hydro-test system
Technical field
The utility model relates to a kind of pilot system of fuel controller, and more particularly it is an a kind of aircraft APU fuel controller hydro-test system.It is used for the hydraulic test of aircraft APU fuel controller, the main controller model that is suitable for has PN:441921 (B737-600/700/800/900), PN:441761 (B777), PN:3883240 (A330/A340), PN:3882730 (EMB-120/BAE146/CR-RJ), PN:3882825 (A320/B737/MD80), PN:4503653 (B737) and PN:4500039 (A320/A321), is aircraft type in the bracket.
Background technology
Fuel controller is an integrated control device of being made up of filtrator, gear-type pump, safety valve, torque motor, differential pressure regulator, flow control valve and switch electromagnetic valve.Its effect is when APU turns round, and provides pressure and the accurate fuel oil of flow to it, thereby guarantees that APU runs well.
Need qualified after tested can coming into operation before the fuel controller installation, or after it breaks down, need analyzing failure cause, more renew part or repairing after finding out trouble unit, come into operation after qualified after tested again, therefore need a kind of test device of fuel controller that fuel controller is tested, find out the fault of fuel controller fast or do final Acceptance Test.
Fuel controller hydro-test system is the test device of fuel controller core.
Summary of the invention
The purpose of this utility model provide a kind of meet aircraft APU fuel controller performance characteristic test request, can testing airplane APU fuel controller the hydro-test system.
The purpose of this utility model is achieved through the following technical solutions: the fuel controller hydraulic test system, it is characterized in that the adapter inner rotatable part of also giving that it comprises with the lubricating oil import of adapter links to each other with the lubricating oil oil return opening provides lubricated lubricating oil loop, be used for providing the fuel feed loop of hydraulic power source to fuel controller, be used to test the actuator test loop of actuator bringing onto load performance, be used to test the backpressure circuit of fuel controller oil-out bringing onto load performance, the pump break-in and the performance test loop of the pressure measurement loop of test fuel controller pressure and pressure reduction and test fuel controller internal gear pump break-in and performance.
In technique scheme, described lubricating oil loop comprises the lubricating oil import of the supercharge pump, ball valve and the adapter that are connected with oil tank by pipeline, be connected with oil filter on the pipeline between supercharge pump and the ball valve, on ball valve and the direct pipeline of lubricating oil oil-in the 7th pressure transducer be installed.Be connected with needle-valve on the branch road of pipeline between oil filter and the ball valve, control the lubricating oil intake pressure by needle-valve.The lubricating oil oil return opening of adapter is connected with oil tank by pipeline.
In technique scheme, described fuel feed loop comprises fuel tank, on fuel tank, be connected with centrifugal pump in turn by pipeline, filtrator, refrigeratory and flowmeter, and in the fuel feed interface on the feeding fuel controller, on the pipeline branch pipe between filtrator and the refrigeratory, be connected with safety valve, safety valve feeds in the fuel tank by pipeline branch pipe, on the pipeline branch pipe between refrigeratory and the flowmeter, be connected with pressure-regulating valve, pressure-regulating valve feeds in the fuel tank by pipeline branch pipe, and first pressure transducer and first temperature sensor are installed on the pipeline between flowmeter and the fuel feed interface.
In technique scheme, described actuator test loop comprises the actuator restriction device, the actuator restriction device is by pipeline first differential pressure pickup in parallel, the first differential pressure pickup two ends are equipped with second pressure transducer by actuator oil return opening on the pipeline feeding fuel controller and the actuator oil-out on the fuel controller on the pipeline between first differential pressure pickup and the actuator oil-in.
In technique scheme, described actuator restriction device, is composed in parallel with second stop valve of connecting and second throttling valve with after the first throttle valve is connected by first stop valve again.
In technique scheme, described backpressure circuit comprises back pressure test interface, throttling valve, flow divider valve and orifice union, back pressure regulating valve and the flowmeter that connects by pipeline successively, on the pipeline between the back pressure test interface on throttling valve and the fuel controller three-temperature sensor, the 5th pressure transducer and the 3rd differential pressure pickup are installed, the 6th pressure transducer is installed on the pipeline of described orifice union and back pressure regulating valve, back pressure regulating valve is in parallel with stop valve, and described flowmeter feeds fuel tank by pipeline.
In technique scheme, described flow divider valve and orifice union are made up of flow divider valve, first segment head piece and second restriction, one end of flow divider valve is connected with throttling valve, two interfaces of the other end of flow divider valve connect the first segment head piece and second restriction respectively, and the first segment head piece is connected the 6th pressure transducer with second restriction by pipeline.
In technique scheme, described pressure measurement loop comprises second differential pressure pickup, the two ends of second differential pressure pickup by pipeline successively respectively with fuel controller on the pressure reduction test port be connected with the pressure test mouth, on the pipeline branch road between second differential pressure pickup and the pressure test mouth the 4th pressure transducer is installed.
In technique scheme, described pump break-in and performance test loop comprise pump break-in and performance test interface, high pressure filter, the 3rd pressure transducer, second temperature sensor, flowmeter and the counterbalance valve that connects by pipeline, and described counterbalance valve is connected with fuel tank by pipeline.
Adopt the fuel controller hydraulic test system of technique scheme to possess following functional advantage:
1, adapter of the present utility model is used for drive unit and connects with installation between the fuel controller input shaft, guarantees that power transmission is reliable and stable.
2, fuel feed of the present utility model loop provides the fuel oil of satisfactory pressure and flow to fuel controller.
3,, can test the supply capability of fuel controller actuator pressure governor under the simulated aircraft load behavior at the actuator test loop.
4, backpressure circuit is arranged at the fuel controller outlet, but fictitious load loads the back pressure performance index of test fuel controller under load behavior.
5, the loop that test is provided is tested for the pressure test and the pressure reduction of fuel controller in the pressure measurement loop;
6, pump break-in and performance test loop provide the performance test of pump running-in period and runtime.
Description of drawings
Fig. 1 is the whole theory diagram of the utility model aircraft fuel oil controller hydraulic test system.
Fig. 2 is the hydraulic schematic diagram of the utility model aircraft fuel oil controller hydraulic test system.
Among the figure: 1. centrifugal pump; 2. filtrator; 3. safety valve; 4. refrigeratory; 5. pressure-regulating valve; 6. flowmeter; 7. first pressure transducer; 8. first temperature sensor; 9. actuator restriction device; 10. first differential pressure pickup; 11. second pressure transducer; 12. high pressure filter; 13. the 3rd pressure transducer; 14. second temperature sensor; 15. flowmeter; 16 counterbalance valves; 17. the 4th pressure transducer; 18. second differential pressure pickup; 19. three-temperature sensor; 20. the 5th pressure transducer; 21. the 3rd differential pressure pickup; 22. throttling valve; 23. flow divider valve and orifice union; 24. the 6th pressure transducer; 25. stop valve; 26. back pressure regulating valve; 27. flowmeter; 28. supercharge pump; 29. oil filter; 30. needle-valve; 31. ball valve; 32. the 7th pressure transducer; 33. lubricating oil import; 34. lubricating oil oil return opening; 35. actuator oil return opening; 36. actuator oil-out; 37. fuel feed interface; 38. pump break-in and performance test interface; 39. back pressure test interface; 40. pressure reduction test port; 41. pressure test mouth; 42. fuel controller; 44. adapter; 45. lubricating oil loop; 46. actuator test loop; 47. backpressure circuit; 48. pressure measurement loop; 49. fuel feed loop; 50. pump break-in and performance test loop; 51. fuel controller; 52. fuel tank; 53. first stop valve; 54. first throttle valve; 55. second stop valve; 56. second throttling valve; 57. oil tank; 58. flow divider valve; 59. first segment head piece; 60. second restriction.
Embodiment
Describe performance of the present utility model in detail below in conjunction with accompanying drawing, but they do not constitute to qualification of the present utility model, only do for example.Simultaneously by illustrating that advantage of the present utility model will become clear more and understanding easily.
Consult accompanying drawing as can be known, it comprises the lubricating oil loop 45 that links to each other with lubricating oil oil return opening 34 with the lubricating oil import 33 of adapter 44 the utility model fuel controller hydraulic test system, be used for providing the fuel feed loop 49 of hydraulic power source to fuel controller 51, be used to test the actuator test loop 46 of actuator bringing onto load performance, be used to test the backpressure circuit 47 of fuel controller oil-out bringing onto load performance, the pressure measurement loop 48 of test fuel controller pressure and pressure reduction, and the break-in of test fuel controller internal gear pump and the pump break-in and the performance test loop 50 of performance.
Lubricating oil loop 45 comprises the lubricating oil import 34 of the supercharge pump 28, ball valve 31 and the adapter 44 that are connected with oil tank 57 by pipeline, be connected with oil filter 29 on the pipeline between supercharge pump 28 and the ball valve 31, be connected with needle-valve 30 on the branch road of pipeline between oil filter 29 and the ball valve 31, needle-valve 30 is connected to oil tank by pipeline.The lubricating oil oil return opening 33 of adapter 44 is connected to oil tank by pipeline.On ball valve 31 and the pipeline that lubricating oil oil-in 34 is connected the 7th pressure transducer 32 is installed.The effect of supercharge pump 28 provides high pressure lubricating oil oil sources, and branch road needle-valve 30 is regulated charge oil pressure, and by pressure transducer 32 its pressure sizes of monitoring, the break-make of ball valve 31 control lubricating oil fuel feeding.
Fuel feed loop 49 comprises fuel tank 52, on fuel tank 52, be connected with centrifugal pump 1 in turn by pipeline, filtrator 2, refrigeratory 4 and flowmeter 6, and in the fuel feed interface 37 on the feeding fuel controller 51, on the pipeline branch pipe between filtrator 2 and the refrigeratory 4, be connected with safety valve 3, safety valve 3 feeds in the fuel tank 52 by pipeline branch pipe, on the pipeline branch pipe between refrigeratory 4 and the flowmeter 6, be connected with pressure-regulating valve 5, pressure-regulating valve 5 feeds in the fuel tank 52 by pipeline branch pipe, and first pressure transducer 7 and first temperature sensor 8 are installed on the pipeline between flowmeter 6 and the fuel feed interface 37.Fuel oil is by centrifugal pump 1 supercharging output elevated pressures fuel oil in the fuel tank, filtrator 2 and refrigeratory 4 are guaranteed the cleaning of fluid and are kept temperature stabilization, set the opening pressure restriction fuel feeding top pressure of safety valve 3, regulate the charge oil pressure and the flow of bypass pressure-regulating valve 5 control aircraft fuel oil controllers 51.Flowmeter 6, pressure transducer 7 and temperature sensor 8 are monitored fuel supply flow rate, pressure and temperature respectively.
Actuator test loop 46 comprises actuator restriction device 9, actuator restriction device 9 is by pipeline first differential pressure pickup 10 in parallel, first differential pressure pickup, 10 two ends are by being equipped with second pressure transducer 11 on actuator oil return opening 35 on the pipeline feeding fuel controller and the pipeline between 36, the first differential pressure pickups 10 of the actuator oil-in on the fuel controller and the actuator oil-in 36.Actuator restriction device 9, is composed in parallel with second stop valve 55 of connecting and second throttling valve 56 with after first throttle valve 54 is connected by first stop valve 53 again.Actuator test loop 46 is used for the performance of actuator working hole under the bringing onto load situation of testing airplane fuel controller.Its load simulation is realized by restriction device 9, and is monitored actuator oil-in pressure and oil inlet and oil return pressure reduction by pressure transducer 11 and differential pressure pickup 10.
Backpressure circuit 47 comprises back pressure test interface 39, throttling valve 22, flow divider valve and orifice union 23, back pressure regulating valve 26 and the flowmeter 27 that connects by pipeline successively, three-temperature sensor 19, the 5th pressure transducer 20 and the 3rd differential pressure pickup 21 are installed on the pipeline between the back pressure test interface 39 on throttling valve 22 and the fuel controller, the 6th pressure transducer 24 is installed on the pipeline of described orifice union 23 and back pressure regulating valve 26, back pressure regulating valve 26 is in parallel with stop valve 25, and described flowmeter 27 feeds fuel tank 52 by pipeline.
Flow divider valve and orifice union 23 are made up of flow divider valve 58, first segment head piece 59 and second restriction 60, one end of flow divider valve 58 is connected with throttling valve 22, two interfaces of the other end of flow divider valve 58 connect the first segment head piece 59 and second restriction 60 respectively, and first segment head piece 59 is connected the 6th pressure transducer 24 with second restriction 60 by pipeline.
Backpressure circuit 47 simulation fuel controller oil-outs are in the performance test of load behavior.Fuel controller oil-out pressure oil returns fuel tank through throttling valve 22, flow divider valve and orifice union 23, back pressure regulating valve 26 or stop valve 25 and flowmeter 27.By regulating throttling valve 22 control oil-out flows, back pressure regulating valve 26 Control Flow distribution valve and orifice union 23 outlet back pressures, whether the stop valve 25 may command back pressure fuel oils that are connected in parallel with it are by back pressure regulating valve 26 controls, behind stop valve 25 standard-sized sheets, back pressure pressure is reduced to zero and is returned fuel tank by stop valve 25.Temperature sensor 19, pressure transducer 20 are monitored the oily temperature and the oil pressure of oil-out respectively, and pressure transducer 24 and flowmeter 27 are tested back pressure pressure and flow respectively.
Pressure measurement loop 48 comprises second differential pressure pickup 18, the two ends of second differential pressure pickup 18 by pipeline successively respectively with fuel controller on pressure reduction test port 40 be connected with pressure test mouth 41, the 4th pressure transducer 17 is installed on the pipeline branch road between second differential pressure pickup 18 and the pressure test mouth 41.By pressure transducer 17 and differential pressure pickup 18 gaging pressures and pressure reduction.
Pump break-in and performance test loop 50 comprise pump break-in and performance test interface 38, high pressure filter 12, the 3rd pressure transducer 13, second temperature sensor 14, flowmeter 15 and the counterbalance valve 16 that connects by pipeline, and described counterbalance valve 16 is connected with fuel tank 52 by pipeline.This loop is the hydraulic circuits of fuel controller 51 internal gear pumps in running in stage and performance test setting specially.The high pressure fuel of fuel controller inner teeth wheel pump output returns fuel tank through high pressure filter 12, flowmeter 15 and counterbalance valve 16 during test, and by counterbalance valve 16 control gear pump output pressures, thereby the simulation pump band carries operating mode.
During work, all above-mentioned test interfaces are connected to the corresponding test lead of tested fuel controller, the fuel controller hydraulic system is tested.In the test process of reality, can make the test unit of the performance test of fuel controller adapt to the controller of different model, as the fuel controller model is PN:441921, PN:441761, PN:3883240, PN:3882730, PN:3882825, PN:4503653 and PN:4500039, by changing the flow divider valve and the orifice union of actuator restriction device and respective model, thereby be applicable to the test of the fuel controller of same kind different model.

Claims (9)

1. fuel controller hydraulic test system, it is characterized in that it comprises the lubricating oil loop (45) that links to each other with lubricating oil oil return opening (33) with the lubricating oil import (34) of adapter (44), be used for providing the fuel feed loop (49) of hydraulic power source to fuel controller (51), be used to test the actuator test loop (46) of actuator bringing onto load performance, be used to test the backpressure circuit (47) of fuel controller oil-out bringing onto load performance, the pressure measurement loop (48) of test fuel controller pressure and pressure reduction and the break-in of test fuel controller internal gear pump and pump break-in and performance test loop (50) of performance.
2. fuel controller hydraulic test system according to claim 1, it is characterized in that: described lubricating oil loop (45) comprises the supercharge pump (28) that is connected with oil tank (57) by pipeline, the lubricating oil import (34) of ball valve (31) and adapter (44), be connected with oil filter (29) on the pipeline between supercharge pump (28) and the ball valve (31), be connected with needle-valve (30) on the branch road of pipeline between oil filter (29) and the ball valve (31), needle-valve (30) is connected to oil tank by pipeline, the lubricating oil oil return opening (33) of adapter (44) is connected to oil tank by pipeline, on ball valve (31) and the pipeline that lubricating oil oil-in (34) is connected the 7th pressure transducer (32) is installed, the effect of supercharge pump (28) provides high pressure lubricating oil oil sources, branch road needle-valve (30) is regulated charge oil pressure, and monitor its pressure size by pressure transducer (32), the break-make of ball valve (31) control lubricating oil fuel feeding.
3. fuel controller hydraulic test system according to claim 1, it is characterized in that: described fuel feed loop (49) comprises fuel tank (52), upward be connected with centrifugal pump (1) in turn at fuel tank (52) by pipeline, filtrator (2), refrigeratory (4) and flowmeter (6), and in the fuel feed interface (37) on the feeding fuel controller (51), on the pipeline branch pipe between filtrator (2) and the refrigeratory (4), be connected with safety valve (3), safety valve (3) feeds in the fuel tank (52) by pipeline branch pipe, on the pipeline branch pipe between refrigeratory (4) and the flowmeter (6), be connected with pressure-regulating valve (5), pressure-regulating valve (5) feeds in the fuel tank (52) by pipeline branch pipe, and first pressure transducer (7) and first temperature sensor (8) are installed on the pipeline between flowmeter (6) and the fuel feed interface (37).
4. fuel controller hydraulic test system according to claim 1, it is characterized in that: described actuator test loop (46) comprises actuator restriction device (9), actuator restriction device (9) is by pipeline first differential pressure pickup (10) in parallel, first differential pressure pickup (10) two ends are equipped with second pressure transducer (11) by actuator oil return opening (35) on the pipeline feeding fuel controller and the actuator oil-in (36) on the fuel controller on the pipeline between first differential pressure pickup (10) and the actuator oil-in (36).
5. fuel controller hydraulic test system according to claim 4, it is characterized in that: described actuator restriction device (9), is composed in parallel with second stop valve (55) of connecting and second throttling valve (56) with after first throttle valve (54) is connected by first stop valve (53) again.
6. fuel controller hydraulic test system according to claim 1, it is characterized in that: described backpressure circuit (47) comprises the back pressure test interface (39) that connects by pipeline successively, throttling valve (22), flow divider valve and orifice union (23), back pressure regulating valve (26) and flowmeter (27), on the pipeline between the back pressure test interface (39) on throttling valve (22) and the fuel controller three-temperature sensor (19) is installed, the 5th pressure transducer (20) and the 3rd differential pressure pickup (21), the 6th pressure transducer (24) is installed on the pipeline of described orifice union (23) and back pressure regulating valve (26), back pressure regulating valve (26) is in parallel with stop valve (25), and described flowmeter (27) feeds fuel tank (52) by pipeline.
7. fuel controller hydraulic test system according to claim 6, it is characterized in that: described flow divider valve and orifice union (23) are made up of flow divider valve (58), first segment head piece (59) and second restriction (60), the entrance point of flow divider valve (58) is connected with throttling valve (22), two outlets of the other end of flow divider valve (58) connect first segment head piece (59) and second restriction (60) respectively, and first segment head piece (59) and second restriction (60) are connected the 6th pressure transducer (24) after by the pipeline parallel connection.
8. fuel controller hydraulic test system according to claim 1, it is characterized in that: described pressure measurement loop (48) comprises second differential pressure pickup (18), the two ends of second differential pressure pickup (18) by pipeline successively respectively with fuel controller on pressure reduction test port (40) be connected with pressure test mouth (41), on the pipeline branch road between second differential pressure pickup (18) and the pressure test mouth (41) the 4th pressure transducer (17) is installed.
9. according to the described fuel controller hydraulic test system of claim 1, it is characterized in that: described pump break-in and performance test loop (50) comprise pump break-in and performance test interface (38), high pressure filter (12), the 3rd pressure transducer (13), second temperature sensor (14), flowmeter (15) and the counterbalance valve (16) that connects by pipeline, and described counterbalance valve (16) is connected with fuel tank (52) by pipeline.
CN2010205075209U 2010-08-27 2010-08-27 Hydraulic test system of fuel controller Expired - Fee Related CN201788411U (en)

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102954872A (en) * 2012-10-12 2013-03-06 湖北航达科技有限公司 High-temperature fuel test bed for aircraft hydraulic element
CN103511237A (en) * 2013-10-16 2014-01-15 合肥今典机械科技有限公司 Performance testing platform for automobile power steering oil pump
CN103592961A (en) * 2013-09-24 2014-02-19 中国科学院力学研究所 Kerosene flow control device for supersonic combustion test
CN104791831A (en) * 2014-10-28 2015-07-22 中国科学院力学研究所 Iso-butane feed system for supersonic combustion direct connection platform
CN105758646A (en) * 2016-03-01 2016-07-13 西安航空动力股份有限公司 Test device and test method for lubricating oil cut-off of aero-engine afterburner fuel regulator
CN106090395A (en) * 2016-08-18 2016-11-09 中国航空工业集团公司西安飞机设计研究所 Fuel charger pressure flow control device is used in a kind of test
CN106184814A (en) * 2016-08-18 2016-12-07 中国航空工业集团公司西安飞机设计研究所 Calculation of pressure method and device at a kind of back pressure regulating valve inlet
CN110329535A (en) * 2019-08-15 2019-10-15 成都富凯飞机工程服务有限公司 A kind of aircraft interaction fuel transfer system
CN110362067A (en) * 2019-07-20 2019-10-22 成都飞机工业（集团）有限责任公司 Actuator performance tester and test method on a kind of machine

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102954872A (en) * 2012-10-12 2013-03-06 湖北航达科技有限公司 High-temperature fuel test bed for aircraft hydraulic element
CN103592961B (en) * 2013-09-24 2016-05-25 中国科学院力学研究所 The kerosene oil flow control device of Supersonic combustion tests
CN103592961A (en) * 2013-09-24 2014-02-19 中国科学院力学研究所 Kerosene flow control device for supersonic combustion test
CN103511237A (en) * 2013-10-16 2014-01-15 合肥今典机械科技有限公司 Performance testing platform for automobile power steering oil pump
CN103511237B (en) * 2013-10-16 2015-11-25 合肥今典机械科技有限公司 For the performance testing platform of car power power steerig pump
CN104791831B (en) * 2014-10-28 2017-02-08 中国科学院力学研究所 Iso-butane feed system for supersonic combustion direct connection platform
CN104791831A (en) * 2014-10-28 2015-07-22 中国科学院力学研究所 Iso-butane feed system for supersonic combustion direct connection platform
CN105758646A (en) * 2016-03-01 2016-07-13 西安航空动力股份有限公司 Test device and test method for lubricating oil cut-off of aero-engine afterburner fuel regulator
CN105758646B (en) * 2016-03-01 2018-08-03 西安航空动力股份有限公司 The disconnected lubricating oil test method of aeroengine thrust augmentation fuel regulator
CN106090395A (en) * 2016-08-18 2016-11-09 中国航空工业集团公司西安飞机设计研究所 Fuel charger pressure flow control device is used in a kind of test
CN106184814A (en) * 2016-08-18 2016-12-07 中国航空工业集团公司西安飞机设计研究所 Calculation of pressure method and device at a kind of back pressure regulating valve inlet
CN106090395B (en) * 2016-08-18 2019-01-18 中国航空工业集团公司西安飞机设计研究所 A kind of test fuel charger pressure flow control device
CN110362067A (en) * 2019-07-20 2019-10-22 成都飞机工业（集团）有限责任公司 Actuator performance tester and test method on a kind of machine
CN110329535A (en) * 2019-08-15 2019-10-15 成都富凯飞机工程服务有限公司 A kind of aircraft interaction fuel transfer system
CN110329535B (en) * 2019-08-15 2024-04-26 成都富凯飞机工程服务有限公司 Interactive oil delivery system of aircraft

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