CN219831700U - Be used for fixed frock of aircraft fuel controller test - Google Patents
Be used for fixed frock of aircraft fuel controller test Download PDFInfo
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- CN219831700U CN219831700U CN202321265553.0U CN202321265553U CN219831700U CN 219831700 U CN219831700 U CN 219831700U CN 202321265553 U CN202321265553 U CN 202321265553U CN 219831700 U CN219831700 U CN 219831700U
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- 238000012360 testing method Methods 0.000 title claims abstract description 50
- 239000000446 fuel Substances 0.000 title claims abstract description 44
- 230000000694 effects Effects 0.000 abstract description 9
- 230000003014 reinforcing effect Effects 0.000 description 4
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000000034 method 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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Abstract
The utility model discloses a test fixing tool for an aircraft fuel controller, which comprises a fixing platform plate, wherein a supporting corner frame is fixedly arranged at a corner of the bottom surface of the fixing platform plate, a fixing clamping side plate is fixedly arranged at the left side end of the top surface of the fixing platform plate, and a side bracket mechanism is fixedly arranged at the right side of the fixing platform plate. According to the utility model, the test carrier plate of the aircraft fuel controller is arranged as a bearing mechanism of the aircraft fuel controller for testing, the adjusting wheel group is transversely pulled to drive the threaded longitudinal shaft to spirally lift and move in the internal threaded pipe, so that the lifting or lowering of the test carrier plate of the aircraft fuel controller is realized, and the movable clamping side plate is driven to push the transverse telescopic frame mechanism to stretch by arranging the electric hydraulic push rod, so that the aircraft fuel controller for testing can be transversely clamped and fixed by the movable clamping side plate, the effect of flexibly supporting and bearing test equipment is achieved, the effect of conveniently adjusting according to actual requirements during testing is realized, and the flexibility and the adaptability are greatly improved.
Description
Technical Field
The utility model relates to the technical field of tooling equipment, in particular to a fixed tooling for testing an aircraft fuel controller.
Background
The aircraft fuel controller is a mechanism for adjusting the fuel supply of an aircraft engine to reasonably match the working state of the engine, and generally consists of a plurality of independent regulators, including a height regulator, a throttle regulator, an acceleration regulator, a slow-running controller, a temperature regulator, other auxiliary regulating devices and the like; in the test research activities of the aircraft fuel controllers, corresponding fixed tools are needed to fix the controllers, and the tools are process equipment.
The patent document of China with the publication number CN216030370U discloses a fixing tool for testing a seat heating controller, which relates to the technical field of electronics and comprises a test box, a base, a fixed positioning block, a movable positioning block, a pressing plate, a positioning column and a vertical driving mechanism thereof, wherein the fixed positioning block is arranged at the front end of the base, two symmetrically arranged track grooves are arranged on the base, and a rectangular groove … … is arranged below the track grooves. Aiming at the technical scheme, the following defects exist in use: the existing fixed tool for testing is very inflexible in supporting and bearing test equipment when being applied to an aircraft fuel controller, is difficult to adjust according to actual requirements during testing, and is poor in flexibility and adaptability.
Therefore, the fixed fixture for the test of the aircraft fuel controller is provided.
Disclosure of Invention
The utility model aims at: in order to solve the problems in the background art, the utility model provides a test fixture for an aircraft fuel controller.
The utility model adopts the following technical scheme for realizing the purposes:
the utility model provides a be used for aircraft fuel controller test fixture, includes the fixed platform board, the bight fixed mounting of fixed platform board bottom surface has a support angle frame, the left side fixed mounting of fixed platform board top surface has a fixed centre gripping curb plate, the right side fixed mounting of fixed platform board has a side support mechanism, the upper surface fixed mounting that side support mechanism is close to fixed platform board one side has a horizontal telescopic frame mechanism, the inside of horizontal telescopic frame mechanism is equipped with electric hydraulic push rod, horizontal telescopic frame mechanism keeps away from side support mechanism one side fixedly connected with activity centre gripping curb plate, the equal fixed mounting in opposite sides of fixed centre gripping curb plate and activity centre gripping curb plate has the centre gripping touch pad, fixed platform board face runs through and fixed grafting has internal thread pipe and longitudinal tube, and the internal thread pipe is located the middle part of fixed platform face, the internal thread connection of internal thread pipe has the screw axis, the top and the lower surface of screw axis all cup joint has the bearing, the aircraft fuel controller test carrier plate is installed through the bearing rotation to the screw axis top, aircraft fuel controller test carrier plate bottom surface is close to tip department fixed mounting has the centre gripping contact pad, the screw axis bottom surface mounting has the screw axis, the bottom surface mounting has the screw axis fixed with the bottom strap through the bottom end, the screw axis fixed mounting.
Further, the side support mechanism comprises a side support plate and a reinforcing bottom support arm, wherein the reinforcing bottom support arm is fixedly arranged at the bottom of the side face of the side support plate, and the other end of the reinforcing bottom support arm is fixedly connected with the bottom face of the fixed platform plate.
Further, the horizontal telescopic frame mechanism comprises a supporting frame and a sliding sleeve frame, the sliding sleeve frame is transversely sleeved on the surface of the supporting frame in a sliding manner, the cylinder body end of the electric hydraulic push rod is fixedly connected with the inner wall of the supporting frame, and the output end of the electric hydraulic push rod is fixedly connected with the inner wall of the sliding sleeve frame.
Further, the adjusting wheel group comprises a transverse support, a wrenching wheel rim and an anti-skidding wheel groove, wherein the wrenching wheel rim is fixedly sleeved at the side end of the transverse support, and the anti-skidding wheel groove is formed in the top surface and the bottom surface of the wrenching wheel rim.
Further, the cross support is of a cross-shaped frame body structure, the center of the top surface of the cross support is fixedly connected with the bottom end of the threaded longitudinal shaft, and the wrenching wheel rim is of a circular ring structure.
Further, the sliding of the vertical sliding shaft is inserted into the vertical ring pipe, the vertical sliding shaft is of a cylindrical structure, the vertical ring pipe is of a circular pipe structure, and the number of the vertical sliding shaft and the number of the vertical ring pipe are two.
The beneficial effects of the utility model are as follows:
according to the utility model, the test carrier plate of the aircraft fuel controller is arranged as a bearing mechanism of the aircraft fuel controller for testing, the threaded longitudinal shaft can be driven to spirally lift and move in the internal threaded pipe by transversely pulling and rotating the adjusting wheel group, so that the lifting or lowering of the test carrier plate of the aircraft fuel controller is realized, and the movable clamping side plate can be driven to transversely clamp and fix the aircraft fuel controller for testing by arranging the electric hydraulic push rod to drive and push the transverse telescopic frame mechanism to extend, so that the effect of flexibly supporting and bearing test equipment is achieved, the effect of conveniently adjusting according to actual requirements during testing is realized, and the flexibility and the adaptability are greatly improved.
Drawings
FIG. 1 is a perspective view of the structure of the present utility model;
FIG. 2 is a partial sectional perspective view of the present utility model;
FIG. 3 is a partially exploded perspective view of another embodiment of the present utility model;
reference numerals: the device comprises a fixed platform plate 1, a supporting angle frame 2, a fixed clamping side plate 3, a side support mechanism 4, a transverse telescopic frame mechanism 5, an electric hydraulic push rod 6, a movable clamping side plate 7, a clamping contact pad 8, an internal thread pipe 9, a longitudinal axis 10, a bearing 11, an aircraft fuel controller testing carrier plate 12, a longitudinal sliding shaft 13, a longitudinal ring pipe 14, a bottom strip frame 15, a regulating wheel group 16, a side support plate 401, a reinforced bottom support arm 402, a supporting frame 501, a sliding sleeve frame 502, a transverse support 1601, a 1602 wrenching wheel rim 1603 and an antiskid wheel groove.
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.
The electrical components are all connected with an external main controller and 220V mains supply, and the main controller can be conventional known equipment for controlling a computer and the like.
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. 1-3, a test fixture for an aircraft fuel controller comprises a fixed platform plate 1, wherein a supporting angle frame 2 is fixedly arranged at the corner of the bottom surface of the fixed platform plate 1, a fixed clamping side plate 3 is fixedly arranged at the left side end of the top surface of the fixed platform plate 1, a side support mechanism 4 is fixedly arranged on the right side of the fixed platform plate 1, a transverse telescopic frame mechanism 5 is fixedly arranged on the upper surface of one side of the side support mechanism 4, an electric hydraulic push rod 6 is arranged in the transverse telescopic frame mechanism 5, a movable clamping side plate 7 is fixedly connected to one side of the transverse telescopic frame mechanism 5 far from the side support mechanism 4, clamping contact pads 8 are fixedly arranged on opposite side surfaces of the fixed clamping side plate 3 and the movable clamping side plate 7, an internal threaded pipe 9 and a longitudinal ring pipe 14 are longitudinally penetrated and fixedly inserted in the middle of the surface of the fixed platform plate 1, a threaded longitudinal shaft 10 is connected to the internal threads of the internal threaded pipe 9, bearings 11 are respectively arranged on the top end and bottom surfaces of the threaded longitudinal shaft 10, a test carrier plate 12 of the aircraft fuel controller is rotatably arranged on the longitudinal shaft 10 through bearings 11, a bottom surface of the longitudinal shaft 13 is fixedly connected to the bottom surface of the fixed clamping contact pads 15 through the longitudinal shaft 13, and the bottom surface of the fixed threaded shaft 13 is fixedly connected to the bottom surface of the fixed support, and the bottom surface of the vertical shaft 13 is fixedly connected to the threaded carrier 13 through the threaded shaft, and the bottom surface of the vertical shaft is fixedly connected to the threaded carrier, and the bottom surface of the vertical carrier is fixedly connected to the bottom surface of the aircraft controller; more specifically, when the aircraft fuel controller to be tested is fixed, the tested aircraft fuel controller is placed on the top surface of the aircraft fuel controller test carrier plate 12, the adjusting wheel set 16 is transversely turned to drive the screw thread longitudinal shaft 10 to rotate, namely, the screw thread longitudinal shaft 10 moves longitudinally in the internal screw thread pipe 9 in a screw mode, so that the internal screw thread pipe 9 drives the aircraft fuel controller test carrier plate 12 to lift or lower and adjust through the bearing 11, and drives the longitudinal sliding shaft 13 to slide longitudinally in the longitudinal ring pipe 14, namely, the aircraft fuel controller carried by the aircraft fuel controller test carrier plate 12 and the top surface thereof lifts or lowers; and then the electric hydraulic push rod 6 is started to drive the transverse telescopic frame mechanism 5 to extend, so that the movable clamping side plate 7 is driven to move transversely, and the tested aircraft fuel controller can be clamped and fixed laterally.
As shown in fig. 1, the side bracket mechanism 4 comprises a side support plate 401 and a reinforced bottom support arm 402, wherein the reinforced bottom support arm 402 is fixedly arranged at the bottom of the side surface of the side support plate 401, and the other end of the reinforced bottom support arm 402 is fixedly connected with the bottom surface of the fixed platform plate 1; more specifically, by providing the reinforcing bottom arms 402 fixed to the bottoms of the side stay 401 and the fixed platform plate 1, the structural stability is made better.
As shown in fig. 1 and 3, the transverse telescopic frame mechanism 5 comprises a supporting frame 501 and a sliding sleeve frame 502, the sliding sleeve frame 502 is transversely sleeved on the surface of the supporting frame 501 in a sliding manner, the cylinder end of the electro-hydraulic push rod 6 is fixedly connected with the inner wall of the supporting frame 501, and the output end of the electro-hydraulic push rod 6 is fixedly connected with the inner wall of the sliding sleeve frame 502; more specifically, by providing a sliding fit of the support frame 501 and the sliding sleeve 502, stability is better when the structure moves, and isolation and protection are provided for the electro-hydraulic push rod 6.
As shown in fig. 1-2, the adjusting wheel set 16 comprises a transverse frame 1601, a turning wheel rim 1602 and an anti-skidding wheel groove 1603, the turning wheel rim 1602 is fixedly sleeved at the side end of the transverse frame 1601, and the anti-skidding wheel groove 1603 is arranged on the top surface and the bottom surface of the turning wheel rim 1602; more specifically, by providing the anti-skid wheel groove 1603 on the surface of the wrenching wheel rim 1602, the adjustment of the transverse rotation is more convenient, and the hand is not easy to slip.
As shown in fig. 1-2, the cross support 1601 is in a cross-shaped frame structure, and the center of the top surface of the cross support 1601 is fixedly connected with the bottom end of the threaded longitudinal shaft 10, and the wrenching rim 1602 is in a circular ring-shaped structure; more specifically, the wrenching rim 1602 is provided with a circular ring structure, so that the wrench is more convenient to hold during wrenching.
As shown in fig. 1-2, the sliding of the longitudinal sliding shaft 13 is inserted into the longitudinal ring pipe 14, the longitudinal sliding shaft 13 is in a cylindrical structure, the longitudinal ring pipe 14 is in a circular pipe structure, and the number of the longitudinal sliding shafts 13 and the number of the longitudinal ring pipes 14 are two; more specifically, by providing two cylindrical longitudinal sliding shafts 13 in sliding fit with two circular tubular longitudinal collars 14, the structural movement is more stable.
To sum up: according to the test fixing tool for the aircraft fuel controller, the aircraft fuel controller test carrier plate 12 is arranged to serve as a bearing mechanism of the aircraft fuel controller for testing, the adjusting wheel group 16 can be transversely pulled to drive the screw thread longitudinal shaft 10 to spirally lift and move in the internal screw thread pipe 9, so that the lifting or lowering of the aircraft fuel controller test carrier plate 12 is realized, the electric hydraulic push rod 6 is arranged to drive and push the transverse telescopic frame mechanism 5 to stretch, the movable clamping side plate 7 can be pushed to transversely clamp and fix the aircraft fuel controller for testing, the effect of being convenient for flexible supporting and bearing of test equipment is achieved, the effect of being convenient for adjusting according to actual requirements during testing is realized, and the flexibility and the adaptability are greatly improved; the problem that the support and the bearing of test equipment are very inflexible, are difficult to adjust according to the actual requirements during testing, and are poor in flexibility and adaptability is solved.
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. The utility model provides a be used for aircraft fuel controller test fixed frock, its characterized in that includes fixed platform board (1), the bight fixed mounting of fixed platform board (1) bottom surface has support angle frame (2), fixed clamping curb plate (3) are fixed to the left side fixed mounting of fixed platform board (1) top surface, fixed platform board (1) right side fixed mounting has side support mechanism (4), the upper surface fixed mounting of side support mechanism (4) near fixed platform board (1) one side has horizontal telescopic frame mechanism (5), the inside of horizontal telescopic frame mechanism (5) is equipped with electric hydraulic ram (6), side fixed connection movable clamping curb plate (7) are kept away from to horizontal telescopic frame mechanism (5), fixed clamping curb plate (3) and the opposite side of movable clamping curb plate (7) all fixed mounting contact pad (8), fixed platform board (1) face is vertically run through and fixed grafting have internal thread pipe (9) and vertical flat collar (14), and internal thread pipe (9) are located fixed middle part (1) face, the screw thread of vertical axis (10) and thread bearing (10) are all cup jointed on the inside of vertical axis (10), the device is characterized in that an aircraft fuel controller test carrier plate (12) is rotatably mounted at the top end of a threaded longitudinal shaft (10) through a bearing (11), a longitudinal sliding shaft (13) is fixedly mounted at the bottom surface of the aircraft fuel controller test carrier plate (12) close to the end part, a bottom strip frame (15) is fixedly mounted at the bottom end of the longitudinal sliding shaft (13), the lower surface of the threaded longitudinal shaft (10) is rotatably connected with the bottom strip frame (15) through the bearing (11), and an adjusting wheel set (16) is fixedly mounted at the bottom end of the threaded longitudinal shaft (10).
2. The fixed fixture for testing the aircraft fuel controller according to claim 1, wherein the side bracket mechanism (4) comprises a side support plate (401) and a reinforced bottom support arm (402), the reinforced bottom support arm (402) is fixedly arranged at the bottom of the side surface of the side support plate (401), and the other end of the reinforced bottom support arm (402) is fixedly connected with the bottom surface of the fixed platform plate (1).
3. The fixed frock of a test for aircraft fuel controller according to claim 1, characterized in that, horizontal telescopic frame mechanism (5) include braced frame (501) and slip cover frame (502), slip cover frame (502) transversely slide and cup joint in braced frame (501) surface, and the cylinder body end and braced frame (501) inner wall fixed connection of electric hydraulic push rod (6), the output of electric hydraulic push rod (6) and slip cover frame (502) inner wall fixed connection.
4. The tool for testing and fixing the aircraft fuel controller according to claim 1, wherein the adjusting wheel set (16) comprises a transverse bracket (1601), a wrenching wheel rim (1602) and an anti-skidding wheel groove (1603), the wrenching wheel rim (1602) is fixedly sleeved at the side end of the transverse bracket (1601), and the anti-skidding wheel groove (1603) is formed in the top surface and the bottom surface of the wrenching wheel rim (1602).
5. The fixture for testing and fixing the fuel controller of the aircraft according to claim 4, wherein the cross bracket (1601) is of a cross-shaped bracket body structure, the center of the top surface of the cross bracket (1601) is fixedly connected with the bottom end of the threaded longitudinal shaft (10), and the wrenching rim (1602) is of a ring-shaped structure.
6. The fixed fixture for testing the aircraft fuel controller according to claim 1, wherein the sliding of the longitudinal sliding shaft (13) is inserted into the longitudinal annular pipe (14), the longitudinal sliding shaft (13) is of a cylindrical structure, the longitudinal annular pipe (14) is of a circular pipe structure, and the number of the longitudinal sliding shafts (13) and the number of the longitudinal annular pipes (14) are two.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321265553.0U CN219831700U (en) | 2023-05-24 | 2023-05-24 | Be used for fixed frock of aircraft fuel controller test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321265553.0U CN219831700U (en) | 2023-05-24 | 2023-05-24 | Be used for fixed frock of aircraft fuel controller test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219831700U true CN219831700U (en) | 2023-10-13 |
Family
ID=88252091
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321265553.0U Active CN219831700U (en) | 2023-05-24 | 2023-05-24 | Be used for fixed frock of aircraft fuel controller test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219831700U (en) |
-
2023
- 2023-05-24 CN CN202321265553.0U patent/CN219831700U/en active Active
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