CN220039794U - Aviation aircraft APU bleed valve observes and controls test bench - Google Patents
Aviation aircraft APU bleed valve observes and controls test bench Download PDFInfo
- Publication number
- CN220039794U CN220039794U CN202321043037.3U CN202321043037U CN220039794U CN 220039794 U CN220039794 U CN 220039794U CN 202321043037 U CN202321043037 U CN 202321043037U CN 220039794 U CN220039794 U CN 220039794U
- Authority
- CN
- China
- Prior art keywords
- device frame
- operation panel
- bleed valve
- wind
- detection structure
- 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.)
- Active
Links
- 238000001514 detection method Methods 0.000 claims abstract description 46
- 238000005259 measurement Methods 0.000 claims abstract description 23
- 230000000694 effects Effects 0.000 claims description 7
- 230000001681 protective effect Effects 0.000 claims description 7
- 238000009434 installation Methods 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 description 2
- 238000004378 air conditioning Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
Landscapes
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model discloses an aviation aircraft APU bleed valve measurement and control test bed which comprises a workbench, a device frame, an operation table, a pressure detection structure, a wind power detection structure, a power connection structure, a door frame and a current detector, wherein the device frame is arranged above the workbench, the operation table is arranged below the inner part of the device frame, the operation table is arranged above the middle part of the workbench, the pressure detection structure is arranged in the middle of the top end of the device frame, the wind power detection structure is arranged at the upper edge of one side of the outer part of the device frame, the power connection structure is arranged in the middle of one side of the outer wall of the device frame, the door frames are arranged on both sides of the surface of the device frame, and the current detector is arranged at one side of the surface edge of the workbench. According to the aeroplane APU bleed valve measurement and control test bed, the rotatable operation table is arranged, so that the angle adjustment can be performed after the bleed valve is put in, and the device is convenient for detecting the functional quality of the corresponding bleed valve.
Description
Technical Field
The utility model relates to the technical field of measurement and control of an aircraft APU bleed valve, in particular to an aircraft APU bleed valve measurement and control test bed.
Background
The APU bleed air system functions to provide pressurized air output by the APU load compressor to air conditioning systems, engine starting systems, and other aerodynamic components on the aircraft. In addition, the APU bleed system can reduce compressor surge when the aircraft is in flight and there is no bleed air load, and the bleed air valve controls the bleed air flow from the APU turbine cavity plenum to the aircraft pneumatic duct. The air entraining valve is arranged in an air entraining pipeline in front of the APU cabin and mainly comprises a butterfly main valve, an actuator, a change rate control valve and a switching valve, so that the quality of the aircraft APU air entraining valve is required to be detected, and a detection platform is required to be used for quality measurement and control experiments.
The conventional measurement and control test bed cannot more comprehensively carry out measurement and control tests on a part device in use, for example, an APU cooler performance test bed disclosed in application number CN202122471479.5 has the limitation of use on parts needing to be subjected to test detection, and only can carry out measurement and control tests on the side of the part from one aspect, so that the function of the device on the quality detection test of the part is greatly reduced, and all aspects of quality measurement and control on the part cannot be carried out more comprehensively.
Therefore, the utility model discloses an aviation aircraft APU bleed valve measurement and control test bed which is necessary to solve the problems.
Disclosure of Invention
The utility model aims to provide an aviation aircraft APU bleed valve measurement and control test bed, which solves the problem that the measurement and control test of a part device cannot be more comprehensively carried out in the technology, the existing detection test bed has the use limitation on parts needing to be subjected to test detection, and only the part side measurement and control test can be carried out from one aspect, so that the function of the device on the part quality detection test is greatly reduced, and the quality measurement and control of all aspects of the parts cannot be more comprehensively carried out.
In order to achieve the above object, the present utility model provides the following technical solutions: the utility model provides an aeroplane APU bleed valve observes and controls test bench, includes workstation, device frame, operation panel, pressure detection structure, wind-force detection structure, power connection structure, portal and current detection appearance, the top of workstation is provided with the device frame, the inside below of device frame is provided with the operation panel, and the operation panel is located the middle part top of workstation, the top middle part of device frame is provided with pressure detection structure, outside one side top edge of device frame is provided with wind-force detection structure, outer wall one side mid-mounting of device frame has power connection structure, the surface both sides of device frame all are provided with the portal, surface edge one side of workstation is provided with the current detection appearance.
Preferably, one side of the surface of the workbench is provided with an inclined plane, an operation panel is arranged at the edge of one side of the inclined plane of the workbench, and a display screen is arranged at one side of the operation panel.
Preferably, the operation panel is circular setting, surface edge one side of operation panel is provided with the guardrail, the outer wall both sides of operation panel all are provided with the clamp strip, the slider is all installed to the bottom surface both sides of operation panel, the slide rail with slider slip size matching has been seted up to device frame inner wall below.
Preferably, a gasket is arranged on the surface of the operation table, the gasket is used for increasing the surface friction force of the operation table, the clamping band can move according to the shaft block at the connecting end, the operation table can move through the rotation of the sliding block in the sliding rail, and the operation table is used for placing an aircraft APU air entraining valve which needs to be detected.
Preferably, the pressure detection structure comprises a through hole, a pressurizing cylinder, a pressure sensor and a supporting frame, wherein the through hole is formed in the middle of the top end of the device frame, the pressurizing cylinder is arranged in the middle of the through hole in a penetrating mode, the pressure sensor is installed at the output end of the pressurizing cylinder, the pressurizing cylinder is fixed on the device frame to work through the supporting frame, the pressurizing cylinder applies pressure downwards, and the pressure which can be born by the air entraining valve is sensed through the pressure sensor, so that the use quality is determined.
Preferably, the wind power detection structure comprises an instrument panel, a connecting column, a wind sensor and a clamping groove, wherein the instrument panel is arranged at one side edge of the top of the device frame, the connecting column is arranged below the instrument panel, the wind sensor is connected to the lower side of the connecting column, the clamping groove is formed in the installation position of the connecting column and the wind sensor, and the wind sensor is used for detecting whether the wind speed quality of the air entraining valve of the APU of the airplane is qualified or not.
Preferably, the power connection structure comprises a motor, a protective sleeve and a port, wherein the motor is located in the middle of one side of the outer wall of the device frame, the protective sleeve is arranged on one side of the motor and located on one side of the inner wall of the device frame, the output end of the motor is provided with a port used for connection, the port penetrates through the middle of the protective sleeve, and the power connection structure is used for measuring and controlling an air entraining valve of an aircraft APU to provide a power starting connection function.
In the technical scheme, the utility model has the technical effects and advantages that:
this aeroplane APU bleed valve observes and controls test bench can carry out the angle modulation after bleed valve is put into through setting up rotatable operation panel, the device of being convenient for is to the function quality detection efficiency of corresponding bleed valve, the guardrail can be as the handle auxiliary rotation, and the clamp strap can go on upwards pressing after the operation panel stops rotating with the valve fixed or the effect that the operation panel was stabilized down pressing, pressure detection structure is through pressurizing down through the pressure boost cylinder, and through pressure sensor the pressure that the bleed valve can bear so confirm the quality of use, wind sensor sets up and uses the wind speed quality that can be used for detecting aircraft APU bleed valve to be qualified, the setting of power connection structure is used for aircraft APU bleed valve to provide the effect that the power starts the connection, and the electric current detector that is equipped with can detect the electric current that produces when inner structure detects the operation, whether this bleed valve can qualified use through the detection of electric current.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the present utility model;
FIG. 2 is a schematic view of the bottom view of the present utility model;
FIG. 3 is a schematic view of the structure of the console according to the present utility model;
FIG. 4 is a schematic view of a wind power detection structure according to the present utility model;
fig. 5 is a schematic view of a pressure detecting structure according to the present utility model.
Reference numerals illustrate:
1. a work table; 2. a device rack; 3. an operation table; 301. guard bars; 302. a clamping strap; 303. a slide block; 304. a slide rail; 305. a gasket; 4. a pressure detection structure; 401. a through hole; 402. a boost cylinder; 403. a pressure sensor; 404. a support frame; 5. a wind power detection structure; 501. a dashboard; 502. a connecting column; 503. a wind sensor; 504. a clamping groove; 6. a power supply connection structure; 601. a motor; 602. a protective sleeve; 603. a port; 7. a door frame; 8. a current detector; 9. an operation panel; 10. and a display screen.
Detailed Description
In order to make the technical scheme of the present utility model better understood by those skilled in the art, the present utility model will be further described in detail with reference to the accompanying drawings.
The utility model provides an aviation aircraft APU bleed valve measurement and control test bed as shown in figures 1-5, which comprises a workbench 1, a device frame 2, an operation table 3, a pressure detection structure 4, a wind power detection structure 5, a power connection structure 6, a portal 7 and a current detector 8, wherein the device frame 2 is arranged above the workbench 1, the operation table 3 is arranged below the inner part of the device frame 2, the operation table 3 is positioned above the middle part of the workbench 1, the operation table 3 is circularly arranged, one side of the surface edge of the operation table 3 is provided with a guardrail 301, both sides of the outer wall of the operation table 3 are provided with clamping straps 302, both sides of the bottom surface of the operation table 3 are provided with sliding blocks 303, sliding rails 304 matched with the sliding sizes of the sliding blocks 303 are arranged below the inner wall of the device frame 2, the surface of the operation table 3 is provided with a gasket 305, the gasket 305 is arranged for increasing the surface friction force of the operation table 3, the clamping strap 302 can move according to an axle block at a connecting end, the operation table 3 can move through the rotation of the sliding block 303 in the sliding rail 304, the operation table 3 is used for placing an aircraft APU air entraining valve which needs to be detected, a pressure detection structure 4 is arranged in the middle of the top end of the device frame 2, the pressure detection structure 4 comprises a through hole 401, a pressurizing cylinder 402, a pressure sensor 403 and a supporting frame 404, the through hole 401 is formed in the middle of the top end of the device frame 2, the pressurizing cylinder 402 is arranged in the middle of the through hole in a penetrating way, the pressure sensor 403 is installed at the output end of the pressurizing cylinder 402, the pressurizing cylinder 402 is fixed on the device frame 2 through the supporting frame 404 to work, the pressurizing cylinder 402 applies pressure downwards, and the pressure which can be born by the air entraining valve is sensed through the pressure sensor 403 so as to determine the use quality;
the outside one side top edge of device frame 2 is provided with wind-force detection structure 5, wind-force detection structure 5 includes panel board 501, spliced pole 502, wind sensor 503 and draw-in groove 504, panel board 501 installs at the top one side edge of device frame 2, spliced pole 502 is installed to the below of panel board 501, the below of spliced pole 502 is connected with wind sensor 503, the spliced pole 502 is provided with draw-in groove 504 with the installation department of wind sensor 503, wind sensor 503 sets up and uses the wind speed quality that can be used for detecting aircraft APU bleed valve, outer wall one side mid-mounting of device frame 2 has power connection structure 6, power connection structure 6 includes motor 601, lag 602 and port 603, motor 601 is located the outer wall one side middle part of device frame 2, one side of motor 601 is provided with lag 602, and be located the inner wall one side of device frame 2, the output of motor 601 is provided with port 603 that is used for connecting, and port 603 runs through the middle part of lag 602, the setting up of power connection structure 6 is used for aircraft bleed air measurement and control to provide the effect of power start-up connection, the surface both sides of device frame 2 all are provided with portal 7, surface side 1 edge one side is provided with current detection appearance 8, surface 1 side is provided with slope 9, surface 1 is provided with slope 9, one side of operation panel 9 is provided with slope 9.
The working principle of the utility model is as follows:
referring to fig. 1-5 of the specification, an APU bleed valve measurement and control test stand of an aeroplane of this type is firstly used to open a door frame 7 on the outer side of a device frame 2, the APU bleed valve to be measured and controlled is placed on an operation table 3 in the device frame 2, a handheld guardrail 301 is matched with a slide block 303 below to slide on a slide rail 304 to finish the adjustment of a detection angle, the device is convenient for the functional quality detection efficiency of the corresponding bleed valve, the guardrail 301 can be used as a handle to assist in rotating, a clamp strip 302 can press upwards after the operation table 3 stops rotating to fix the valve or press downwards to stabilize the operation table 3, the test wind power performance makes one side of the air outlet face of a wind sensor 503, the detected wind power data is transmitted to the device frame 501 through the starting power connection of a power connection structure 6 on one side, the pressure detection structure is pressed downwards, the pressure can be used for detecting the pressure borne by an air sensor through a pressurizing cylinder, the corresponding bleed valve can be used for determining the quality detection, the use of the air quality can be set, whether the air quality can be used for detecting the air quality of the APU bleed valve is qualified by the quality detection structure, and the quality of the air-guide valve can be used for detecting the quality of the aeroplane is judged by comparing whether the quality of the air-guide valve is connected through the power connection structure of the APU, and the air-guide valve is qualified by the quality detection structure, and the quality of the air-guide valve is tested through the quality detection, and the quality of the quality is judged by comparing with the quality of the air, and the quality of the air can be tested through the quality of the quality through the quality of the air.
Claims (7)
1. The utility model provides an aeroplane APU bleed valve observes and controls test bench, includes workstation (1), device frame (2), operation panel (3), pressure detection structure (4), wind-force detection structure (5), power connection structure (6), portal (7) and current detection appearance (8), a serial communication port, the top of workstation (1) is provided with device frame (2), the inside below of device frame (2) is provided with operation panel (3), and operation panel (3) are located the middle part top of workstation (1), the top middle part of device frame (2) is provided with pressure detection structure (4), outside one side top edge of device frame (2) is provided with wind-force detection structure (5), outer wall one side mid-mounting of device frame (2) has power connection structure (6), the surface both sides of device frame (2) all are provided with portal (7), surface edge one side of workstation (1) is provided with current detection appearance (8).
2. The aircraft APU bleed valve measurement and control test stand of claim 1, wherein: the surface of workstation (1) one side is the inclined plane setting, inclined plane one side edge of workstation (1) is provided with operation panel (9), one side of operation panel (9) is provided with display screen (10).
3. The aircraft APU bleed valve measurement and control test stand of claim 1, wherein: the operation panel (3) is circular setting, surface edge one side of operation panel (3) is provided with guardrail (301), the outer wall both sides of operation panel (3) all are provided with clamping strap (302), slider (303) are all installed to the bottom surface both sides of operation panel (3), slide rail (304) with slider (303) slip size matching have been seted up to device frame (2) inner wall below.
4. An aeroplane APU bleed valve measurement and control test stand according to claim 3, wherein: the surface of operation panel (3) is provided with gasket (305), the setting of gasket (305) is used for increasing operation panel (3) surface friction, clamp strip (302) can be according to the axle piece of link activity, operation panel (3) can be through the rotation of slider (303) in slide rail (304) activity, operation panel (3) are used for placing aircraft APU bleed air valve that needs to detect.
5. The aircraft APU bleed valve measurement and control test stand of claim 1, wherein: the pressure detection structure (4) comprises a through hole (401), a pressurizing cylinder (402), a pressure sensor (403) and a supporting frame (404), wherein the through hole (401) is formed in the middle of the top end of the device frame (2), the pressurizing cylinder (402) is arranged in the middle of the through hole (401), the pressure sensor (403) is arranged at the output end of the pressurizing cylinder (402), the pressurizing cylinder (402) is fixed on the device frame (2) through the supporting frame (404) to work, the pressurizing cylinder (402) applies pressure downwards, and the pressure born by the air entraining valve is sensed through the pressure sensor (403) so as to determine the use quality.
6. The test bed for measuring and controlling the air entraining valve of the APU of the aeroplane according to claim 5, wherein the test bed is characterized in that: the wind power detection structure (5) comprises an instrument panel (501), a connecting column (502), a wind sensor (503) and a clamping groove (504), wherein the instrument panel (501) is arranged at one side edge of the top of the device frame (2), the connecting column (502) is arranged below the instrument panel (501), the wind sensor (503) is connected below the connecting column (502), the clamping groove (504) is arranged at the installation position of the connecting column (502) and the wind sensor (503), and the wind sensor (503) is used for detecting whether the wind speed quality of an air entraining valve of an aircraft APU is qualified or not.
7. The aircraft APU bleed valve measurement and control test stand of claim 1, wherein: the power connection structure (6) comprises a motor (601), a protective sleeve (602) and a port (603), wherein the motor (601) is located in the middle of one side of the outer wall of the device frame (2), the protective sleeve (602) is arranged on one side of the motor (601) and located on one side of the inner wall of the device frame (2), the port (603) used for connection is arranged at the output end of the motor (601), the port (603) penetrates through the middle of the protective sleeve (602), and the power connection structure (6) is used for providing a power starting connection effect for measurement and control of an air entraining valve of an aircraft APU.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321043037.3U CN220039794U (en) | 2023-05-04 | 2023-05-04 | Aviation aircraft APU bleed valve observes and controls test bench |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321043037.3U CN220039794U (en) | 2023-05-04 | 2023-05-04 | Aviation aircraft APU bleed valve observes and controls test bench |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220039794U true CN220039794U (en) | 2023-11-17 |
Family
ID=88734397
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321043037.3U Active CN220039794U (en) | 2023-05-04 | 2023-05-04 | Aviation aircraft APU bleed valve observes and controls test bench |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220039794U (en) |
-
2023
- 2023-05-04 CN CN202321043037.3U patent/CN220039794U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107588957B (en) | A kind of electronic unmanned plane dynamical system multi-function test stand | |
| CN112975794B (en) | Positioning and clamping device for outer wing of airplane | |
| CN220039794U (en) | Aviation aircraft APU bleed valve observes and controls test bench | |
| CN218937197U (en) | Universal missile wing test bench | |
| CN220649944U (en) | Air tightness test device | |
| CN111811810A (en) | Performance test equipment of vehicle valve | |
| CN105043744A (en) | Performance test instrument of intake air bypass valve and using method thereof | |
| CN218524326U (en) | Rubber sleeve gap detection device | |
| CN112710870B (en) | Performance detection device for APU (auxiliary Power Unit) speed sensor | |
| CN215065066U (en) | Air tightness detection table for upper cover of automobile battery | |
| CN112505092B (en) | Heat-proof skirt gas flow test device | |
| CN209296257U (en) | A kind of modularization vehicle rear axle assembly air-leakage test platform | |
| CN205374039U (en) | High -speed testboard of engine phase place speed sensor | |
| CN210834054U (en) | Air tightness test device for through passage system | |
| CN207873603U (en) | A kind of device of riveting electronic throttle dish valve screw | |
| CN209043565U (en) | A kind of wind-tunnel inner section flowing field stability measuring device | |
| CN108362426B (en) | Aeroengine thrust detection equipment | |
| CN204831775U (en) | Bypass valve capability test appearance admits air | |
| CN219777031U (en) | Oil storage cylinder air tightness test device | |
| CN205438299U (en) | Rotating positioner | |
| CN117871020B (en) | Can dismantle passenger car wind tunnel test system fast | |
| CN210719665U (en) | Automobile sun visor rotation endurance test device | |
| CN216247509U (en) | Air outlet blade test pressure head and air outlet blade test equipment | |
| CN221006695U (en) | Be used for whole car controller gas tightness detection device of new energy automobile | |
| CN212134001U (en) | Internal pressure detector for automobile air conditioner shell |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |