CN212047952U - Aircraft fuel accessory comprehensive test platform - Google Patents
Aircraft fuel accessory comprehensive test platform Download PDFInfo
- Publication number
- CN212047952U CN212047952U CN202020729494.8U CN202020729494U CN212047952U CN 212047952 U CN212047952 U CN 212047952U CN 202020729494 U CN202020729494 U CN 202020729494U CN 212047952 U CN212047952 U CN 212047952U
- Authority
- CN
- China
- Prior art keywords
- pressure
- test
- oil
- pressure gauge
- switch
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Abstract
An aircraft fuel accessory comprehensive test bed comprises a comprehensive pump station, a pressure refueling combined test oil tank, an electric centrifugal pump test bed, a mechanical control platform and an electrical control cabinet; the upper part of the comprehensive pump station is provided with a main oil tank of the comprehensive test system, and the lower part of the comprehensive pump station is provided with a pressure oil feeding pump set, a flow resistance test oil pump set and an oil return pump set; the front part of the pressure oiling combined test oil tank is provided with a glass window; the electric centrifugal pump test bench is an alternating current electric centrifugal pump test bench and a direct current electric centrifugal pump test bench; the mechanical control console comprises a box body, a control panel, an oil collecting pool, a control console, an oil collecting tank, various interfaces and various conduits; the electrical control cabinet is provided with a digital display instrument, a touch screen and an operation button thereof. The utility model discloses the realization is to the test requirement of performance index such as the pressure of fuel or air conditioning annex, flow, pressure differential loss, the valve open and close characteristic, inside and outside leakproofness, operating voltage and electric current, facilitates the use, and the function is various, has the practicality.
Description
Technical Field
The utility model relates to an aviation ground protects equipment technical field, especially relates to an aircraft fuel annex combined test platform.
Background
The test bed of the comprehensive test bed for the engine fuel accessories is designed on the basis of all the fuel accessories of a series of airplanes, can bear the test requirements of the special airplanes on the performance indexes before the regular inspection, the fault detection and the new product installation, and can realize the test requirements of the performance indexes of pressure, flow, pressure difference loss, opening and closing characteristics of a valve, internal and external sealing performance, working voltage, current and the like of the fuel or air conditioning accessories;
the conventional aircraft fuel accessory comprehensive test bed equipment is inconvenient to operate, difficult to realize the automation of the detection of the dynamic performance of key fuel accessories, single in function and to be improved.
SUMMERY OF THE UTILITY MODEL
Objects of the invention
For solving the technical problem that exists among the background art, the utility model provides an aircraft fuel annex integrated test platform can satisfy special type aircraft and examine surely, before fault detection and the new goods installation to the test requirement of whole performance index, can realize the test requirement to performance index such as the opening and closing characteristic, inside and outside leakproofness, operating voltage and the electric current of pressure, flow, pressure differential loss, valve of fuel or air conditioning annex, facilitates the use, and the function is various, has the practicality.
(II) technical scheme
The utility model provides an aircraft fuel accessory comprehensive test bed, which comprises a comprehensive pump station, a pressure refueling combined test oil tank, an electric centrifugal pump test board, a mechanical control console and an electrical control cabinet;
the upper part of the comprehensive pump station is provided with a main oil tank of the comprehensive test system, and the lower part of the comprehensive pump station is provided with a pressure oil feeding pump set, a flow resistance test oil pump set and an oil return pump set;
the front part of the pressure refueling combined test oil tank is provided with a glass window, the top part of the pressure refueling combined test oil tank is provided with an installation interface of a liquid level controller RHF-2A, and the bottom part of the pressure refueling combined test oil tank is provided with an installation interface of a refueling control valve RHF-1A and a quick-release clamp; an electric contact pressure gauge and a pressure sensor are arranged on the side surface;
the electric centrifugal pump test bench is an alternating current electric centrifugal pump test bench and a direct current electric centrifugal pump test bench, and two test pipelines are arranged on the electric centrifugal pump test bench;
the mechanical control console comprises a box body, a control panel, an oil collecting pool, a control console, an oil collecting tank, various interfaces and various conduits; the box body is provided with a hand pump, an aviation accessory electric socket and a ground charging connector; the control panel is provided with a pressure gauge, a fuel accessory electric control device, a control switch area and a test filler neck;
the electrical control cabinet is provided with a digital display instrument, a touch screen and an operation button thereof, and the electrical control cabinet is internally provided with a PLC (programmable logic controller) and an expansion module thereof, a frequency converter, a switching power supply and a contactor.
Preferably, the power supply also comprises an intermediate frequency power supply control box; the intermediate frequency power supply output by the intermediate frequency power supply control box is 115V and 400 Hz.
Preferably, the tool box is further included; the interior of the tool box is divided into three layers.
Preferably, the device also comprises a gas cylinder; the air bottle is a ground compressed air bottle which is generally distributed in each airport and has the capacity of 50L and the working pressure of 15 MPa.
Preferably, the top of the main oil tank is provided with a gravity oil filling port, the side door is provided with an oil temperature meter and a liquid level meter, and each oil outlet and each oil return port are arranged inside the side door.
Preferably, two rows of pressure gauges are arranged on the control panel, the upper row of pressure gauges are respectively a cold air pressure gauge of 1.6MPa, a cold air pressure gauge of 0.6MPa, a static pressure gauge of 6MPa, a static pressure gauge of 1.6MPa, a static pressure gauge of 0.6MPa and a static pressure gauge of 0.25MPa, and the lower row of pressure gauges are respectively a gas source pressure gauge of 16MPa, a cold air pressure gauge of 6MPa, a cold air pressure gauge of 0.25MPa, an oil filter inlet pressure gauge, an oil filter outlet pressure gauge and a flow resistance differential pressure gauge.
Preferably, three rows of fuel accessory electric control devices are arranged on the operating panel, the upper rows of fuel accessory electric control devices are respectively an alternating current voltmeter, a direct current ammeter and a work timer, the middle row of signal lamps are respectively an alternating current power supply, a direct current power supply, a signaler is switched on, RDF-12 is switched off, RDK-1A is switched on, RDK-1A is switched off, FDG-19 is switched on, RDF-13 is switched off, a communicating valve is switched on, a communicating valve is switched off, RDK-50 is switched on, FR-343 is switched on, RDK-92 is switched off, RYF-32 is switched on and RYF-32 is switched off, and the lower row of electric gates are respectively an alternating current power supply, a direct current power supply, a fluorescent lamp, manual timing, a signaler, RDF-12, RDF-1A, RDF-13/13A, a fire-proof switch RDK-92 and an oil quantity balance valve RYF-32.
Preferably, two rows of switches are arranged on the control panel, the upper row of switches are respectively an air source switch, a 6MPa air inlet switch, a cold air pressure regulating switch, a 6MPa air outlet switch, a differential gauge left oil inlet switch, a differential gauge balancing switch and a differential gauge right oil inlet switch, and the lower row of switches are respectively a cold air 1.6MPa pressure gauge switch, a cold air 0.6MPa pressure gauge switch, a cold air 0.25MPa pressure gauge switch, a static pressure regulating switch, a static pressure 1.6MPa pressure gauge switch, a static pressure 0.6MPa pressure gauge switch and a static pressure 0.25MPa pressure gauge switch.
Preferably, the test filler neck arranged on the control panel comprises a cold air 6MPa air inlet joint, a cold air 1.6MPa air inlet joint I, a cold air 1.6MPa air inlet joint II, a fuel static pressure test joint I, a fuel static pressure test joint II, an oil filter inlet pressure test joint and an oil filter outlet pressure test joint.
Preferably, a guide pipe used for connecting the pressure gauge on the mechanical control console is an aviation aluminum guide pipe, and a guide pipe of the fuel oil flow resistance testing part is a stainless steel pipe.
The above technical scheme of the utility model has following profitable technological effect:
the utility model discloses can satisfy special type aircraft and examine surely, before fault detection and the new product installation to the test requirement of whole performance index, can realize the test requirement to performance index such as the opening and closing characteristic of pressure, flow, pressure loss, valve, inside and outside leakproofness, operating voltage and the electric current of fuel or air conditioning annex, facilitate the use, the function is various, has the practicality.
Drawings
Fig. 1 is a schematic structural diagram of the aircraft fuel accessory comprehensive test bed provided by the utility model.
Reference numerals: 1. a comprehensive pump station; 2. a pressure refueling combined test oil tank; 3. an electric centrifugal pump test bench; 4. a mechanical console; 5. an electrical control cabinet; 6. a medium frequency power supply control box; 7. a tool box; 8. a gas cylinder.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in detail with reference to the accompanying drawings. It should be understood that the description is intended to be illustrative only and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
As shown in fig. 1, the utility model provides an aircraft fuel accessory comprehensive test bed, which comprises a comprehensive pump station 1, a pressure refueling combined test oil tank 2, an electric centrifugal pump test bed 3, a mechanical control platform 4 and an electrical control cabinet 5;
the upper part of the comprehensive pump station 1 is provided with a main oil tank of a comprehensive test system, and the lower part is provided with a pressure oil feeding pump set, a flow resistance test oil pump set and an oil return pump set;
the front part of a pressure refueling combined test oil tank 2 (which performs combined test by using an RHF-1A/2A type accessory) is provided with a glass window, the top part is provided with an installation interface of a liquid level controller RHF-2A, and the bottom part is provided with an installation interface of a refueling control valve RHF-1A and a quick-release clamp; the side surface is provided with an electrical contact pressure gauge and a pressure sensor which are convenient for the PLC to interpret and are used for the operation of the oil and magnetic floats; the distance between the combined oil tank and the main oil tank is 600mm, the height is 1.4m, the diameter is 0.6m, and the volume is 0.5m3(ii) a A steel plate ruler convenient for observing the liquid level height is further arranged on the pressure refueling combined test oil tank 2;
the electric centrifugal pump test board 3 is an alternating current and direct current electric centrifugal pump test board, the alternating current and direct current electric centrifugal pump tests share the test board, two test pipelines are arranged on the electric centrifugal pump test board 3 (the performance detection work of the alternating current and direct current electric centrifugal pumps is completed by using the two test pipelines through different mounting seats on the end cover of the oil tank, the dynamic performance tests of the direct current electric centrifugal pumps LB-21/22, RLB-39/83 and the alternating current electric centrifugal pump RLB-40, namely the tests of parameters such as flow, pressure, current, voltage and the like, and the electric centrifugal pump test board is composed of a tested oil pump, the oil tank, flow and pressure sensors, a servo regulating valve, a pipe fitting and the like;
the mechanical control platform 4 comprises a box body, a control panel, an oil collecting pool, a control platform, an oil collecting tank, various interfaces and various conduits; a pump station and a pressure and flow testing part of a fuel system are arranged in the mechanical control platform 4; the rear part of the mechanical console 4 is provided with two large open-type back doors, which can facilitate the dismounting of the catheter, the accessories and the tightness of the inspection system; in addition, to facilitate the movement of the mechanical console 4, four steerable wheels are mounted at the bottom of the mechanical console 4; a hand-operated pump (used as a pump source of a static pressure test part) and an aviation accessory electrical socket are arranged on the box body (when the test platform tests fuel accessories, the hand-operated pump and the aviation accessory electrical socket are connected by a special cable to respectively realize electrical input and output control on RDF-13/13A (DG-12), a communication/fire-proof switch (DG-15), RDK-1A (DG-34), RDF-12, an electromagnetic switch RDK-50, an oil quantity balance valve RYF-32, a pre-detection switch FR-343 and a annunciator) and a ground inflating nozzle (when the test platform carries out cold air static pressure test, the test platform is connected with a large cold air bottle by a high-pressure hose to realize air supply to; the control panel is provided with a pressure gauge, a fuel accessory electric control device, a control switch area and a test filler neck;
the electrical control cabinet 5 is provided with a digital display instrument (comprising a current, voltage, pressure, differential pressure and flow digital display instrument), a touch screen and an operation button thereof, and is internally provided with a PLC (programmable logic controller) and an expansion module thereof, a frequency converter, a switching power supply and a contactor, and is used for completing the performance test of fuel accessories and a fuel centrifugal pump;
the aircraft fuel accessory comprehensive test system is composed of 8 parts in total from the aspect of functions, namely a cold air pressurization test system, a fuel accessory static pressure test system, an oil return part, a fuel flow resistance test system, a pressure refueling combined test system, an electric centrifugal pump test system, a fuel electromechanical accessory test system and an automatic test control system;
cold air pressure boost test system: the fuel accessories are tested for static pressure sealing performance by taking cold air and nitrogen as media, valve opening pressure and cold air fuel combined oil leakage quantity, and the direction conversion of a system pipeline is comprehensively tested; during system design, a pressure reducing valve and a pressure regulating valve are adopted to meet the pressure required by the test, the connection between different fuel accessories and a test bed is realized in the form of a standard interface and a switching port, and the design of a cold air system test part of the test bed is composed of a pressure test part and a medium-small flow conversion control part in functional design, so that the realization, safety and reliability of system functions can be ensured, and the system design is scientific, reasonable, simple and feasible;
the static pressure test system of the fuel accessory: the detection of mechanical properties such as static pressure, flow, sealing performance and the like of accessories such as various one-way valves, various switches, various valves and the like is mainly completed; the fuel static pressure test system can complete the product tightness test of all fuel accessories of the airplane, the opening and closing working performance test of the refueling valve and the signal indication test of the annunciator product, and the pressure range of the sealing test is 0-2.5 MPa; when the system is designed, a hand-operated pump is used as a power source of the system, and the system and the fuel small flow test system share an oil collecting tank and an oil collecting pool; a static pressure regulating switch is adopted to regulate the pressure so as to meet the pressure condition required by the test; considering the requirement on the system tightness during static pressure testing, a one-way valve is adopted to ensure the high tightness of the system in the testing process; the test system adopts a standard interface and a switching port to realize convenient and quick connection between a tested piece and the test system;
fuel flow resistance test system: the dynamic and static performance test of accessories with medium and small flow rates is mainly finished, the dynamic and static performance test device comprises a pump source part, a flow rate and pressure control part and a differential pressure test part, wherein the fuel flow resistance test part mainly finishes the performance test of accessories such as a fuel filter YL-29/31/40, a one-way check valve RXF-69, a fire prevention switch RDK-92, an oil mass balance valve RYF-32 and the like; the fuel flow resistance testing part completes the flow resistance test of 3 products of the fuel filter, namely the pressure difference before and after the fuel filter is detected when the fuel filter passes the specified flow; the fuel flow resistance testing part can also complete the flow resistance test of the one-way valve product, namely the pressure difference between the front and the back of the product is detected when the product passes through the specified flow;
fuel electric centrifugal pump test system: the test system of the fuel oil centrifugal pump is mainly used for completing the performance verification of the aircraft fuel oil centrifugal pump and functionally consists of an oil supply and delivery power supply part, an oil pump test part and an electrical control part; the fuel pump test system can test LB-21, LB-22, RLB-39, RLB-83 and RLB-40 type aviation fuel pumps in an automatic mode and a manual mode, and can respectively detect basic performance parameters such as working current, working voltage, fuel pressure, fuel flow and the like of the fuel pump;
pressure refuels and unites test system: the aircraft pressure refueling accessory mainly comprises a pressure refueling control valve RHF-1A, an oil level controller RHF-2A, a pre-detection switch and the like; the pressure refueling control valve RHF-1A is matched with the oil level controller RHF-2A for use and is used for controlling the ground pressure refueling of the airplane to ensure the airplane to refuel quickly and safely, and the pressure refueling control valve RHF-1A and the oil level controller RHF-2A are arranged in 13 sets of left 1A complete machines in the oil tank; the pressure refueling combined test system mainly completes the tests of the flow resistance, the valve opening and closing time, the voltage, the current and other performances of fuel accessories such as a pressure refueling control valve, a fuel level controller and the like, and the pre-detection function test;
fuel electromechanical accessory test system: the electric control system of the common aircraft fuel accessories is mainly used for detecting and controlling the performances of fuel electrical accessories such as RDF-12, RDK-1A (DG-34), annunciators, RDF-13/13A (DG-12), a communication and fire-proof switch (DG-15), an electromagnetic switch RDK-50, a fuel balance valve RYF-32, a fire-proof switch RDK-92, a pre-detection switch FR-343 and the like; the fuel oil common accessory electric control system consists of a 27V direct-current power supply and a fuel oil electric accessory test system;
automatic measurement and control system: because the special-shaped part of the airplane is a key accessory of a fuel system, the special-shaped part not only has multiple test items, relatively complex procedures and strict standards, but also has quite high failure rate in use, the design of a test loop and the automatic control program of the special-shaped part are two key points of the test bench; the industrial control system has the functions as follows: automatically completing the performance test of the fuel accessory under the control of an industrial personal computer; the general design idea of the industrial control test system is as follows: the fuel test bed adopts a Programmable Logic Controller (PLC) with reliable performance and high stability as a controller; the detection of analog quantity data is completed by selecting a pressure transmitter, a differential pressure transmitter and a flow transmitter which meet the precision requirement; the main actuators in the system comprise a frequency converter, a regulating valve, an electromagnetic valve and the like, and the execution of control instructions is completed through the main actuators; the touch screen is adopted as a human-computer interface, so that the interface is friendly and the operation is simple and convenient;
an oil return part: collecting oil leakage when the accessories are disassembled and assembled, and pumping fuel oil in the pressure refueling combined test oil tank and the oil collecting tank of the mechanical control console back to the main oil tank.
In an optional embodiment, the system further comprises an intermediate frequency power supply control box 6; the intermediate frequency power supply output by the intermediate frequency power supply control box 6 is 115V and 400Hz and is used for outputting 115V and 400Hz intermediate frequency power supply to the RLB-40 alternating current electric oil pump.
In an alternative embodiment, a tool box 7 is also included; the tool box 7 is divided into three layers, the tool box is auxiliary equipment, the upper surface of the tool box is used for placing various fuel accessories, and spare parts, cables, technical data, special tools, clamps and the like are stored in the tool box.
In an alternative embodiment, a gas cylinder 8 is also included; the gas cylinder 8 is a ground compressed air cylinder which is distributed in each airport and has the capacity of 50L and the working pressure of 15MPa, and provides a compressed air (nitrogen) total gas source with sufficient pressure and flow for each part of test loop.
In an alternative embodiment, the top of the main oil tank is provided with a gravity oil filling port, the side door is provided with an oil temperature meter and a liquid level meter, and each oil outlet and each oil return port are arranged inside the side door.
In an optional embodiment, two rows of pressure gauges are arranged on the control panel, the upper row is respectively a cold air 1.6MPa pressure gauge, a cold air 0.6MPa pressure gauge, a static pressure 6MPa pressure gauge, a static pressure 1.6MPa pressure gauge, a static pressure 0.6MPa pressure gauge and a static pressure 0.25MPa pressure gauge, and the lower row is respectively a gas source 16MPa pressure gauge, a cold air 6MPa pressure gauge, a cold air 0.25MPa pressure gauge, an oil filter inlet pressure gauge (0-1.6 MPa), an oil filter outlet pressure gauge (0-1.6 MPa) and a flow resistance differential pressure gauge (0-60 KPa).
In an optional embodiment, three rows of fuel accessory electric control devices are arranged on the control panel, the upper row of the fuel accessory electric control devices are respectively an alternating current voltmeter, a direct current ammeter and a work timer, the middle row of signal lamps are respectively an alternating current power supply, a direct current power supply, a signaler is switched on, RDF-12 is switched off, RDK-1A is switched on, RDK-1A is switched off, FDG-19 is switched on, RDF-13 is switched off, a communication valve is switched on, RDK-50 is switched on, FR-343 is switched on, RDK-92 is switched off, RYF-32 is switched on, and RYF-32 is switched off, and the lower row of electric gates are respectively an alternating current power supply, a direct current power supply, a fluorescent lamp, manual timing, a signaler, RDF-12, RDF-1, A communication/fire-proof switch (DG-15), electromagnetic switches RDK-50, FR-343, a fire-proof switch RDK-92 (an electric mechanism) and an oil quantity balance valve RYF-32 (an electric mechanism).
In an optional embodiment, two rows of switches are arranged on the control panel, the upper row of switches are respectively an air source switch, a 6MPa air inlet switch, a cold air pressure regulating switch, a 6MPa air outlet switch, a differential gauge left oil inlet switch, a differential gauge balancing switch and a differential gauge right oil inlet switch, and the lower row of switches are respectively a cold air 1.6MPa pressure gauge switch, a cold air 0.6MPa pressure gauge switch, a cold air 0.25MPa pressure gauge switch, a static pressure regulating switch, a static pressure 1.6MPa pressure gauge switch, a static pressure 0.6MPa pressure gauge switch and a static pressure 0.25MPa pressure gauge switch.
In an optional embodiment, the test filler neck arranged on the control panel comprises a cold air 6MPa air inlet joint, a cold air 1.6MPa air inlet joint I, a cold air 1.6MPa air inlet joint II, a fuel static pressure test joint I, a fuel static pressure test joint II, an oil filter inlet pressure measuring joint and an oil filter outlet pressure measuring joint.
In an alternative embodiment, the conduit on the mechanical console 4 for connecting the pressure gauge is an aircraft aluminum conduit; the pipe of the cold air static pressure test system pipeline has a high and bottom pressure of over 4.9MPa (50 kg/cm)2) The high-pressure guide pipes are high-quality aviation stainless steel guide pipes, the guide pipes lower than 4.9MPa (50kg/cm2) are low-pressure guide pipes and are high-quality copper-aluminum guide pipes, and a 5MPa pressure reducer is used as a boundary on each pipe; the pipes of the fuel static pressure test system pipeline are all high-quality copper-aluminum pipes, and the pressure resistance can bear the pressure of 6 MPa; the guide pipe of the fuel flow resistance testing part is a stainless steel pipe, and the pressure resistance can bear the pressure of 1.6 MPa.
In the utility model, the design of the fuel oil system takes safety, stability, reliability and economy as basic principles, accurately provides the test conditions such as flow and pressure necessary for testing the fuel oil accessories, and takes the factors of safety and reliability, convenient operation and maintenance, moderate size of a main body operation platform, vibration prevention, explosion prevention and the like into consideration, so that an oil tank assembly, a pump unit, a functional part with larger size and the like form two integral structures; considering the characteristics of volatility and inflammability of a fuel medium, large working current and voltage of an electrical control system and more electrical elements such as a switch and a motor mechanism, the electrical control elements and most instruments are integrated on an industrial control electrical cabinet, and the explosion-proof and anti-static design runs through the whole fuel system design;
the utility model discloses can satisfy special type aircraft and examine surely, before fault detection and the new product installation to the test requirement of whole performance index, can realize the test requirement to performance index such as the opening and closing characteristic of pressure, flow, pressure loss, valve, inside and outside leakproofness, operating voltage and the electric current of fuel or air conditioning annex, facilitate the use, the function is various, has the practicality.
It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explaining the principles of the invention and are not to be construed as limiting the invention. Therefore, any modification, equivalent replacement, improvement and the like made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. Further, it is intended that the appended claims cover all such variations and modifications as fall within the scope and boundaries of the appended claims or the equivalents of such scope and boundaries.
Claims (10)
1. An aircraft fuel accessory comprehensive test bed is characterized by comprising a comprehensive pump station (1), a pressure refueling combined test oil tank (2), an electric centrifugal pump test bed (3), a mechanical control console (4) and an electrical control cabinet (5);
the upper part of the comprehensive pump station (1) is provided with a main oil tank of a comprehensive test system, and the lower part of the comprehensive pump station is provided with a pressure oil feeding pump set, a flow resistance test oil pump set and an oil return pump set;
the front part of the pressure refueling combined test oil tank (2) is provided with a glass window, the top part is provided with an installation interface of a liquid level controller RHF-2A, and the bottom part is provided with an installation interface and a quick release clamp of a refueling control valve RHF-1A; an electric contact pressure gauge and a pressure sensor are arranged on the side surface;
the electric centrifugal pump test bench (3) is an alternating current electric centrifugal pump test bench and a direct current electric centrifugal pump test bench, and two test pipelines are arranged on the electric centrifugal pump test bench (3);
the mechanical control console (4) comprises a box body, a control panel, an oil collecting pool, a control console, an oil collecting tank, various interfaces and various conduits; the box body is provided with a hand pump, an aviation accessory electric socket and a ground charging connector; the control panel is provided with a pressure gauge, a fuel accessory electric control device, a control switch area and a test filler neck;
the electrical control cabinet (5) is provided with a digital display instrument, a touch screen and an operation button thereof, and a PLC controller and an expansion module thereof, a frequency converter, a switching power supply and a contactor are arranged inside the electrical control cabinet.
2. An aircraft fuel accessory comprehensive test bed according to claim 1, further comprising a medium frequency power supply control box (6); the intermediate frequency power supply output by the intermediate frequency power supply control box (6) is 115V and 400 Hz.
3. An aircraft fuel accessory comprehensive test bed according to claim 1, further comprising a tool box (7); the interior of the tool box (7) is divided into three layers.
4. An aircraft fuel accessory comprehensive test bed according to claim 1, further comprising a gas cylinder (8); the air bottle (8) is a ground compressed air bottle which is generally distributed at each airport and has the capacity of 50L and the working pressure of 15 MPa.
5. An aircraft fuel accessory comprehensive test bed according to claim 1, wherein a gravity oil filling port is formed in the top of a main oil tank, an oil temperature meter and a liquid level meter are arranged on a side door, and oil outlets and oil return ports are formed in the side door.
6. An aircraft fuel accessory comprehensive test bed as claimed in claim 1, wherein the control panel is provided with two rows of pressure gauges, the upper row is respectively a cold air 1.6MPa pressure gauge, a cold air 0.6MPa pressure gauge, a static pressure 6MPa pressure gauge, a static pressure 1.6MPa pressure gauge, a static pressure 0.6MPa pressure gauge and a static pressure 0.25MPa pressure gauge, and the lower row is respectively a gas source 16MPa pressure gauge, a cold air 6MPa pressure gauge, a cold air 0.25MPa pressure gauge, an oil filter inlet pressure gauge, an oil filter outlet pressure gauge and a flow resistance differential pressure gauge.
7. An aircraft fuel accessory comprehensive test bed as claimed in claim 1, wherein three rows of fuel accessory electrical control devices are arranged on the operating panel, the upper row is respectively an alternating current voltmeter, a direct current ammeter and a work timer, the middle row of signal lamps are respectively an alternating current power supply, a direct current power supply, a signaler is switched on, RDF-12 is switched off, RDK-1A is switched on, RDK-1A is switched off, FDG-19 is switched on, RDF-13 is switched off, a communicating valve is switched on, RDK-50 is switched on, FR-343 is switched on, RDK-92 is switched off, RYF-32 is switched on, and RYF-32 is switched off, and the lower row of electric doors are respectively an alternating current power supply, a direct current power supply, a fluorescent lamp, a manual timer, a signaler, RDF-12, RDF-1A, RDF-13/13A, A communication/fire prevention switch, electromagnetic switches RDK-50, FR-343, a fire prevention switch RDK-92 and an oil quantity balance valve RYF-32.
8. The aircraft fuel accessory comprehensive test bed according to claim 1, wherein two rows of switches are arranged on the control panel, an upper row of switches are respectively an air source switch, a 6MPa air inlet switch, a cold air pressure regulating switch, a 6MPa air outlet switch, a differential gauge left oil inlet switch, a differential gauge balancing switch and a differential gauge right oil inlet switch, and a lower row of switches are respectively a cold air 1.6MPa pressure gauge switch, a cold air 0.6MPa pressure gauge switch, a cold air 0.25MPa pressure gauge switch, a static pressure regulating switch, a static pressure 1.6MPa pressure gauge switch, a static pressure 0.6MPa pressure gauge switch and a static pressure 0.25MPa pressure gauge switch.
9. An aircraft fuel accessory comprehensive test bed as claimed in claim 1, wherein the test filler neck provided on the control panel comprises a cold air 6MPa inlet connector, a cold air 1.6MPa inlet connector I, a cold air 1.6MPa inlet connector II, a fuel static pressure test connector I, a fuel static pressure test connector II, an oil filter inlet pressure test connector and an oil filter outlet pressure test connector.
10. The aircraft fuel accessory comprehensive test bed as claimed in claim 1, wherein a conduit for connecting a pressure gauge on the mechanical control console (4) is an aviation aluminum conduit, and a conduit of the fuel flow resistance test part is a stainless steel pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020729494.8U CN212047952U (en) | 2020-05-07 | 2020-05-07 | Aircraft fuel accessory comprehensive test platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020729494.8U CN212047952U (en) | 2020-05-07 | 2020-05-07 | Aircraft fuel accessory comprehensive test platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212047952U true CN212047952U (en) | 2020-12-01 |
Family
ID=73526454
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020729494.8U Expired - Fee Related CN212047952U (en) | 2020-05-07 | 2020-05-07 | Aircraft fuel accessory comprehensive test platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212047952U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112807582A (en) * | 2021-02-20 | 2021-05-18 | 凌云(宜昌)航空装备工程有限公司 | Airplane fire extinguishing bottle comprehensive test and intelligent filling detection device and use method |
-
2020
- 2020-05-07 CN CN202020729494.8U patent/CN212047952U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112807582A (en) * | 2021-02-20 | 2021-05-18 | 凌云(宜昌)航空装备工程有限公司 | Airplane fire extinguishing bottle comprehensive test and intelligent filling detection device and use method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102589860B (en) | Integrated testing system for aviation fuel accessories | |
| CN100588938C (en) | Hydrogen storing container hydrogen environment fatigue test system | |
| CN201417199Y (en) | Leak detection device for aircraft oil tank | |
| CN204301824U (en) | A kind of aircraft oil scale in situ detection device | |
| CN212047952U (en) | Aircraft fuel accessory comprehensive test platform | |
| CN202393590U (en) | Aviation fuel accessory integrated test system | |
| CN103903660A (en) | Halogen generator | |
| CN2938132Y (en) | Dynamic performance test stage for quick oil pressure relay of transformer | |
| CN206638397U (en) | A kind of batteries of electric automobile bag air-tightness detection device | |
| CN201876391U (en) | Test bench for testing water pressure strength of cylinder | |
| CN201159693Y (en) | Hydrogen surroundings fatigue test system of hydrogen storage container | |
| CN102513774B (en) | Overhauling line of water supply and drainage system | |
| CN202494561U (en) | Portable safety valve calibrator | |
| CN102501793B (en) | Moving detection vehicle | |
| CN218865235U (en) | Simulation oil tank test device | |
| CN209639947U (en) | A kind of gas-liquid mixed lower-grade fuel multi-function test stand | |
| CN205138764U (en) | Be used for aviation pneumatic valve high temperature, large -traffic combined test platform | |
| CN103292834B (en) | Aircraft fuel liquid level fluidic sensor test system | |
| CN212963876U (en) | Test device for suppressing aircraft engine accessory shell | |
| CN204984833U (en) | Vacuum pump performance testing platform | |
| CN206738302U (en) | A kind of airline carriers of passengers is counter to push away hydraulic actuation system testboard | |
| CN107100914A (en) | A kind of airline carriers of passengers is counter to push away hydraulic actuation system testboard | |
| CN210664925U (en) | Integrated test system for aircraft refueling joint | |
| CN101979986A (en) | System for testing parts of air compression system of special vehicle | |
| CN207336004U (en) | A kind of low temperature valve cryogenic property tests system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20201201 Termination date: 20210507 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |