CN219641134U - Be used for aircraft auxiliary power device testing arrangement - Google Patents
Be used for aircraft auxiliary power device testing arrangement Download PDFInfo
- Publication number
- CN219641134U CN219641134U CN202321265547.5U CN202321265547U CN219641134U CN 219641134 U CN219641134 U CN 219641134U CN 202321265547 U CN202321265547 U CN 202321265547U CN 219641134 U CN219641134 U CN 219641134U
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- Prior art keywords
- auxiliary power
- plate
- power device
- top surface
- aircraft
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- 238000012360 testing method Methods 0.000 title claims abstract description 29
- 238000013016 damping Methods 0.000 claims abstract description 20
- 230000003139 buffering effect Effects 0.000 claims description 3
- 230000035939 shock Effects 0.000 claims description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The utility model discloses a testing device for an auxiliary power device of an airplane, and relates to the technical field of testing devices. The utility model comprises an L-shaped mounting frame, wherein a guide mechanism is fixedly arranged on one side wall of the L-shaped mounting frame and the top surface of the L-shaped mounting frame, a step rod is fixedly arranged on the top surface of the guide mechanism, a rubber damping sleeve is sleeved on the surface of the step rod, and a spring is sleeved on the surface of the step rod and positioned outside the rubber damping sleeve. The utility model further enables the vibration force generated by the auxiliary power device of the airplane during operation to be buffered and absorbed through the rubber damping sleeve and the spring, and enables the movable plate, the mounting plate and the connecting rod to move transversely through the auxiliary power device of the airplane, so that the pressing plate is contacted with the pressure sensor, and the thrust of the auxiliary power device of the airplane detected by the pressure sensor is displayed through the display through the contact of the pressing plate and the pressure sensor.
Description
Technical Field
The utility model relates to the technical field of testing devices, in particular to a testing device for an auxiliary power device of an airplane.
Background
The auxiliary power device is an airborne power device, is mainly used for providing electric power and air entraining for the aircraft when the aircraft is parked in a large scale, is widely applied to small and medium-sized transportation aircraft, is a high-technology product, has high requirements on product reliability and technical indexes, and can be installed for use after being repaired and detected to be qualified after being failed according to the continuous navigable requirements of civil aviation regulations.
The thrust of the auxiliary power device of the airplane is very critical test data when the auxiliary power device of the airplane is detected, and the existing auxiliary power device of the airplane can generate larger vibration when being tested, and the service life of the test device can be influenced by the vibration force.
For this purpose, a test device for an auxiliary power unit of an aircraft is proposed.
Disclosure of Invention
The utility model aims at: in order to solve the problems in the prior art, the utility model provides a testing device for an auxiliary power device of an airplane.
The utility model adopts the following technical scheme for realizing the purposes:
the utility model provides a be used for aircraft auxiliary power device testing arrangement, includes L shape mounting bracket, a lateral wall of L shape mounting bracket and the top surface fixed mounting of L shape mounting bracket have guiding mechanism, guiding mechanism's top surface fixed mounting has the ladder pole, the surface cover of ladder pole is equipped with the rubber damping cover, and the surface of ladder pole just is located the outside cover of rubber damping cover and is equipped with the spring, the surface of ladder pole is provided with the fixed establishment who is used for fixing aircraft auxiliary power device, rubber damping cover and spring are used for carrying out shock attenuation buffering to fixed establishment, guiding mechanism's bottom surface and L shape mounting bracket's surface are provided with the testing mechanism who is used for carrying out the test to aircraft auxiliary power device's thrust.
Further, guiding mechanism includes the curb plate, the top surface fixed mounting of L shape mounting bracket has the curb plate, the relative face fixed mounting of curb plate and L shape mounting bracket has the guide bar, the surface slip cap of guide bar is equipped with the slider, the top surface fixed mounting of slider has the mounting panel, the top surface fixed mounting of mounting panel has the ladder pole.
Further, fixed establishment includes the fly leaf, the surface sliding mounting of ladder pole has the fly leaf, the bottom surface of fly leaf and the top of rubber damping cover and spring are fixed mounting setting, the top surface fixed mounting of fly leaf has the threaded rod, the surface sliding sleeve of threaded rod is equipped with the staple bolt, the top thread cover of threaded rod is equipped with the nut.
Further, the testing mechanism comprises a protruding block, the bottom surface of mounting panel fixedly mounted has protruding block and support, protruding block left side wall fixed mounting has the connecting rod, and connecting rod and support are grafting installation setting, the free end fixed mounting of connecting rod has the clamp plate, L shape mounting bracket lateral wall inlays and installs pressure sensor, the preceding lateral wall fixed mounting of L shape mounting bracket has the display.
Further, through holes are formed in the surface of the movable plate, and the movable plate is arranged in a sliding mode through the through holes in the surface of the movable plate and the step bars.
Further, the pressing plate and the pressure sensor are horizontally arranged, and the pressing plate and the pressure sensor are correspondingly arranged.
The beneficial effects of the utility model are as follows:
1. according to the utility model, the anchor ear is detached by detaching the nut, the aircraft auxiliary power device is placed on the top surface of the movable plate, the anchor ear is sleeved on the top surface of the aircraft auxiliary power device, the anchor ear is fixed by meshing the nut and the threaded rod, the mounting plate and the sliding block move along the surface of the guide rod by the aircraft auxiliary power device, the vibration force generated by the aircraft auxiliary power device during operation is buffered and absorbed by the rubber damping sleeve and the spring, the movable plate, the mounting plate and the connecting rod are transversely moved by the aircraft auxiliary power device, the pressing plate is contacted with the pressure sensor, and the thrust of the aircraft auxiliary power device detected by the pressure sensor is displayed by the display.
Drawings
FIG. 1 is a schematic perspective view of the present utility model;
FIG. 2 is a schematic diagram of the structure of a front view of the present utility model;
FIG. 3 is a schematic view in partial elevation and cross-section of the structure of the present utility model;
FIG. 4 is a schematic view of the structure of the present utility model in front cross section;
reference numerals: 1. an L-shaped mounting rack; 2. a guide mechanism; 201. a side plate; 202. a guide rod; 203. a slide block; 204. a mounting plate; 3. a step bar; 4. a rubber damping sleeve; 5. a spring; 6. a fixing mechanism; 601. a movable plate; 602. a threaded rod; 603. a hoop; 604. a nut; 7. a testing mechanism; 701. a bump; 702. a bracket; 703. a connecting rod; 704. a pressing plate; 705. a pressure sensor; 706. a display.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present utility model more apparent, the technical solutions of the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model, and it is apparent that the described embodiments are some embodiments of the present utility model, but not all embodiments of the present utility model. The components of the embodiments of the present utility model generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the utility model, as presented in the figures, is not intended to limit the scope of the utility model, as claimed, but is merely representative of selected embodiments of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures. Furthermore, the terms "first," "second," and the like, are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.
In describing embodiments of the present utility model, it should be noted that the directions or positional relationships indicated by the terms "inner", "outer", "upper", etc. are directions or positional relationships based on those shown in the drawings, or those that are conventionally put in place when the inventive product is used, are merely for convenience of description and simplification of description, and are not indicative or implying that the apparatus or element in question must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as limiting the present utility model.
As shown in fig. 1 to 4, a test device for an auxiliary power device of an aircraft comprises an L-shaped mounting frame 1, a side wall of the L-shaped mounting frame 1 and the top surface of the L-shaped mounting frame 1 are fixedly provided with a guide mechanism 2, the top surface of the guide mechanism 2 is fixedly provided with a step rod 3, the surface of the step rod 3 is sleeved with a rubber damping sleeve 4, the surface of the step rod 3 is sleeved with a spring 5 outside the rubber damping sleeve 4, the surface of the step rod 3 is provided with a fixing mechanism 6 for fixing the auxiliary power device of the aircraft, the rubber damping sleeve 4 and the spring 5 are used for damping and buffering the fixing mechanism 6, and the bottom surface of the guide mechanism 2 and the surface of the L-shaped mounting frame 1 are provided with a test mechanism 7 for testing the thrust of the auxiliary power device of the aircraft; specifically, the auxiliary power device of the aircraft is fixed through the fixing mechanism 6, the auxiliary power device of the aircraft is started to move transversely under the action of thrust, the vibration force generated by the auxiliary power device of the aircraft during operation is buffered and absorbed through the rubber damping sleeve 4 and the spring 5, and the thrust of the auxiliary power device of the aircraft is measured through the testing mechanism 7.
As shown in fig. 1, 2, 3 and 4, the guide mechanism 2 comprises a side plate 201, the top surface of the L-shaped mounting frame 1 is fixedly provided with the side plate 201, the opposite surfaces of the side plate 201 and the L-shaped mounting frame 1 are fixedly provided with guide rods 202, the surfaces of the guide rods 202 are slidably sleeved with sliding blocks 203, the top surface of each sliding block 203 is fixedly provided with a mounting plate 204, and the top surface of each mounting plate 204 is fixedly provided with a ladder rod 3; specifically, the mounting plate 204 and the slider 203 are moved along the surface of the guide bar 202 by the aircraft auxiliary power unit.
As shown in fig. 1, 2 and 3, the fixing mechanism 6 comprises a movable plate 601, the movable plate 601 is slidably mounted on the surface of the step rod 3, the bottom surface of the movable plate 601 and the top ends of the rubber damping sleeve 4 and the spring 5 are fixedly mounted, a threaded rod 602 is fixedly mounted on the top surface of the movable plate 601, a hoop 603 is slidably sleeved on the surface of the threaded rod 602, and a nut 604 is sleeved on the top thread of the threaded rod 602; specifically, the anchor ear 603 is detached by detaching the nut 604, the aircraft auxiliary power device is placed on the top surface of the movable plate 601, the anchor ear 603 is sleeved on the top surface of the aircraft auxiliary power device, and the anchor ear 603 is fixed by meshing the nut 604 with the threaded rod 602.
As shown in fig. 1, 3 and 4, the testing mechanism 7 comprises a bump 701, the bottom surface of the mounting plate 204 is fixedly provided with the bump 701 and a bracket 702, the left side wall of the bump 701 is fixedly provided with a connecting rod 703, the connecting rod 703 and the bracket 702 are arranged in a plugging manner, the free end of the connecting rod 703 is fixedly provided with a pressing plate 704, one side wall of the L-shaped mounting frame 1 is embedded and provided with a pressure sensor 705, and the front side wall of the L-shaped mounting frame 1 is fixedly provided with a display 706; specifically, the movable plate 601, the mounting plate 204 and the connecting rod 703 are further moved laterally by the auxiliary power device of the aircraft, the pressure plate 704 is in contact with the pressure sensor 705, the pressure sensor 705 is in contact with the pressure plate 704, and the thrust of the auxiliary power device of the aircraft detected by the pressure sensor 705 is further displayed by the display 706.
As shown in fig. 1, 2 and 3, the surface of the movable plate 601 is provided with a through hole, and the movable plate 601 is arranged in a sliding manner through the through hole on the surface and the step bar 3; specifically, the step bar 3 corresponds to the through hole on the surface of the movable plate 601, so that the movable plate 601 is limited.
As shown in fig. 1 and 4, the pressing plate 704 and the pressure sensor 705 are horizontally arranged, and the pressing plate 704 and the pressure sensor 705 are correspondingly arranged; specifically, the pressing plate 704 and the pressure sensor 705 are horizontally and correspondingly arranged, so that the pressing plate 704 can be in contact with the pressure sensor 705.
To sum up: make dismantling staple bolt 603 through dismantling nut 604, place aircraft auxiliary power device at the top surface of fly leaf 601, establish the top surface at aircraft auxiliary power device through staple bolt 603 cover, fix staple bolt 603 through nut 604 and threaded rod 602 meshing, then make mounting panel 204 and slider 203 remove along the surface of guide bar 202 through aircraft auxiliary power device, then make the vibrations that produces aircraft auxiliary power device when the operation absorb through rubber damping cover 4 and spring 5, then make fly leaf 601, mounting panel 204 and connecting rod 703 lateral shifting through aircraft auxiliary power device, make clamp plate 704 and pressure sensor 705 contact, contact through clamp plate 704 and pressure sensor 705, then make the thrust of aircraft auxiliary power device that detects pressure sensor 705 show through display 706.
The foregoing has shown and described the basic principles, principal features and advantages of the utility model. It will be understood by those skilled in the art that the present utility model is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present utility model, and various changes and modifications may be made therein without departing from the spirit and scope of the utility model, which is defined by the appended claims. The scope of the utility model is defined by the appended claims and equivalents thereof.
Claims (6)
1. A be used for aircraft auxiliary power device testing arrangement, a serial communication port, including L shape mounting bracket (1), a lateral wall of L shape mounting bracket (1) and the top surface fixed mounting of L shape mounting bracket (1) have guiding mechanism (2), the top surface fixed mounting of guiding mechanism (2) has ladder pole (3), the surface cover of ladder pole (3) is equipped with rubber damping cover (4), and the outside cover that just is located rubber damping cover (4) of surface of ladder pole (3) is equipped with spring (5), the surface of ladder pole (3) is provided with fixed establishment (6) that are used for carrying out fixed to aircraft auxiliary power device, rubber damping cover (4) and spring (5) are used for carrying out shock attenuation buffering to fixed establishment (6), the bottom surface of guiding mechanism (2) and the surface of L shape mounting bracket (1) are provided with and are used for carrying out test mechanism (7) that test to aircraft auxiliary power device's thrust.
2. The test device for the auxiliary power unit of the airplane according to claim 1, wherein the guide mechanism (2) comprises a side plate (201), the side plate (201) is fixedly arranged on the top surface of the L-shaped mounting frame (1), the guide rod (202) is fixedly arranged on the opposite surfaces of the side plate (201) and the L-shaped mounting frame (1), the sliding sleeve on the surface of the guide rod (202) is provided with a sliding block (203), the mounting plate (204) is fixedly arranged on the top surface of the sliding block (203), and the ladder rod (3) is fixedly arranged on the top surface of the mounting plate (204).
3. The test device for the auxiliary power device of the airplane according to claim 1, wherein the fixing mechanism (6) comprises a movable plate (601), the movable plate (601) is slidably installed on the surface of the step rod (3), the bottom surface of the movable plate (601) and the top ends of the rubber damping sleeve (4) and the spring (5) are fixedly installed, a threaded rod (602) is fixedly installed on the top surface of the movable plate (601), a hoop (603) is sleeved on the surface of the threaded rod (602), and a nut (604) is sleeved on the top thread of the threaded rod (602).
4. The test device for the auxiliary power unit of the airplane according to claim 2, wherein the test mechanism (7) comprises a bump (701), the bottom surface of the mounting plate (204) is fixedly provided with the bump (701) and a bracket (702), the left side wall of the bump (701) is fixedly provided with a connecting rod (703), the connecting rod (703) and the bracket (702) are arranged in a plugging manner, the free end of the connecting rod (703) is fixedly provided with a pressing plate (704), one side wall of the L-shaped mounting frame (1) is inlaid with a pressure sensor (705), and the front side wall of the L-shaped mounting frame (1) is fixedly provided with a display (706).
5. A test device for an auxiliary power unit of an aircraft according to claim 3, characterized in that the surface of the movable plate (601) is provided with a through hole, and the movable plate (601) is slidably mounted through the through hole on the surface and the step bar (3).
6. The test device for an aircraft auxiliary power unit according to claim 4, wherein the pressure plate (704) and the pressure sensor (705) are horizontally arranged, and the pressure plate (704) and the pressure sensor (705) are correspondingly arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321265547.5U CN219641134U (en) | 2023-05-24 | 2023-05-24 | Be used for aircraft auxiliary power device testing arrangement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321265547.5U CN219641134U (en) | 2023-05-24 | 2023-05-24 | Be used for aircraft auxiliary power device testing arrangement |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219641134U true CN219641134U (en) | 2023-09-05 |
Family
ID=87817263
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321265547.5U Active CN219641134U (en) | 2023-05-24 | 2023-05-24 | Be used for aircraft auxiliary power device testing arrangement |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219641134U (en) |
-
2023
- 2023-05-24 CN CN202321265547.5U patent/CN219641134U/en active Active
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