CN213351580U - Fixture process device for matched drilling of aircraft nose landing gear assembly hole - Google Patents
Fixture process device for matched drilling of aircraft nose landing gear assembly hole Download PDFInfo
- Publication number
- CN213351580U CN213351580U CN202020569131.2U CN202020569131U CN213351580U CN 213351580 U CN213351580 U CN 213351580U CN 202020569131 U CN202020569131 U CN 202020569131U CN 213351580 U CN213351580 U CN 213351580U
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- Prior art keywords
- landing gear
- process device
- drilling
- hole
- top end
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- 238000005553 drilling Methods 0.000 title claims abstract description 37
- 238000000034 method Methods 0.000 title claims description 19
- 230000008569 process Effects 0.000 title claims description 19
- 238000009434 installation Methods 0.000 claims abstract description 29
- 230000007246 mechanism Effects 0.000 claims abstract description 13
- 241001074085 Scophthalmus aquosus Species 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 3
- 230000008859 change Effects 0.000 abstract description 2
- 238000003754 machining Methods 0.000 description 4
- 238000009966 trimming Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Abstract
The utility model discloses an aircraft nose landing gear pilot hole jig fixture device, relate to aircraft assembly technical field, including installation base, clamping mechanism, locating rack, grip block and mount, the location head of clamping mechanism's design has made things convenient for the installation to the aircraft landing gear, easy to operate, installs aircraft landing gear whole cooperation on the device simultaneously and carries out drilling processing, has guaranteed that some axle sleeve etc. rotating part's spare part combination link up bolt hole must cooperate the back together drilling in order to eliminate the assembly precision of the position error in hole; the rotating plate is convenient to rotate the undercarriage, operation is easy, the drilling positioning plate can change the position of the drill hole according to different manufacturer requirements, cost is saved, and practicability of the device is improved.
Description
Technical Field
The utility model relates to an aircraft assembly technical field specifically is an anchor clamps process units that aircraft nose landing gear pilot hole joined in marriage brill.
Background
With the coming of the opening of the national low-altitude field and the departure of the navigation policy, general-purpose airplanes are vigorously developed, particularly light airplanes with 2-4 seats. Compared with large-scale airplanes, the light airplane has quite different manufacturing and assembling processes, and the light airplane is simple in structure, small in number of components and not very strict in assembling requirement, so that the light airplane can be sold in a material sleeving mode according to national regulations and assembled by purchasers. However, the landing gear required for the aircraft to park, slide and take off and land on the ground is used as a device for supporting and moving the aircraft, and can bear larger impact load, vibration and the like, and in the process of assembling light aircraft sheathing, some important parts and components need to meet specific assembling requirements, so that a special technical device needs to be designed, the assembling requirements in the design can be met during assembling, meanwhile, the working time of the step is shortened, and the working quality and the working efficiency are improved.
SUMMERY OF THE UTILITY MODEL
To the problem that exists among the prior art, the utility model aims to provide an anchor clamps process units that aircraft nose gear pilot hole joined in marriage brill when undercarriage assembly, the bolt hole that has guaranteed that rotating parts such as some axle sleeves link up when the spare part combines must cooperate the back drilling together in order to eliminate the assembly precision in the position error in hole, and the equipment of device is simple simultaneously, and drilling operation easily operates, compromises the advantage that the cost is appropriate.
In order to achieve the above object, the utility model provides a following technical scheme: the clamping mechanism consists of a fixed column, an installation column and an adjusting stud, the bottom end of the fixed column is welded on the circular end part of the installation base, the installation column is welded at the top end of the fixed column, the diameter of the installation column is smaller than that of the fixed column, a threaded hole is formed in the top end of the installation column, the diameter of the threaded hole is the same as that of the adjusting stud and used for installing the adjusting stud, one end of the adjusting stud penetrates out of the threaded hole of the installation column, a groove is formed in the other end of the adjusting stud, a rotating bearing is fixedly installed in the groove, a rotating rod is rotatably connected in the rotating bearing, and a positioning head is welded at one end, far away from the rotating bearing, of the rotating rod; meanwhile, a symmetrically-installed positioning frame is welded at the middle position of the installation base through a first bolt, a threaded hole is formed in the side face of the top end of the positioning frame, the circle center of the threaded hole and the circle center of the adjusting stud are on the same straight line and used for clamping the rotating rod, and a drilling positioning block is installed at the top end of the positioning frame through the first bolt; meanwhile, symmetrical fixing frames are installed at the tail end of the installation base through a second bolt, and a circular through hole is formed in the side face of the top end of each fixing frame and used for installing and clamping a bolt to clamp the rear end assembly of the undercarriage.
As a further aspect of the present invention: the clamping block is symmetrically welded between the clamping mechanism and the positioning frame, a rectangular groove is formed in the top end of the clamping block, the width of the groove is the same as the thickness of the rotating plate, and meanwhile threaded holes are formed in the two sides of the groove and used for fixing the rotating plate.
As a further aspect of the present invention: the rotating plate is designed to be wing-shaped, meanwhile, a round hole with the same diameter as that of the undercarriage front end assembly is formed in the middle of the rotating plate, a buckle is arranged on one side of the round hole and used for fixing the rotating plate on the undercarriage front end assembly to drive the undercarriage front end assembly to rotate, meanwhile, threaded holes are formed in two side wings of the rotating plate, the diameter of each threaded hole is the same as that of each threaded hole in the clamping block, and when the rotating plate does not rotate, the threaded holes in two sides of the rotating plate are located above the grooves of the clamping block.
As a further aspect of the present invention: the size of the rotating rod is the same as that of the middle-end component of the undercarriage, the rotating rod and the middle-end component of the undercarriage are matched with each other to be installed and then fixed on the positioning frame, the design of the rotating rod is adopted to ensure that through bolt holes must be matched and drilled together to eliminate the assembly precision of the position error of the holes when parts of rotating parts such as shaft sleeves are combined, meanwhile, the rotating rod is prevented from being used for replacing the middle-end component of the undercarriage, and the fixing pin of the positioning frame is prevented from generating scratches on the surface of the middle-end component of the undercarriage to influence the use of the undercarriage.
As a further aspect of the present invention: the top end of the positioning head is arranged to be conical and used for supporting the front end component of the undercarriage.
As a further aspect of the present invention: the installation base is arranged to be in a bowling shape, and simultaneously, the installation base is of a solid structure with a balancing weight.
As a further aspect of the present invention: the surface of drilling locating piece is opened there are four and is treated the drilling, treats that the drilling designs according to actual need, 1 treat that drilling and 2 treat that the drilling symmetry is seted up in the both sides of drilling locating piece, 3 treat simultaneously that drilling and 4 treat that the drilling is installed in the front end position in the centre of drilling locating piece, wherein 4 treat that the drilling is at the front end that 3 treat the drilling.
Compared with the prior art, the beneficial effects of the utility model are that: the utility model discloses an installation base, clamping mechanism, locating rack, grip block and mount are installed aircraft undercarriage global cooperation and are carried out drilling processing on the device, have guaranteed the cooperation precision of pilot hole, and the commentaries on classics board that sets up simultaneously has made things convenient for and has carried out the rotation operation with the undercarriage, easily operation to the position of drilling can be treated according to the producer demand change of difference to the drilling locating plate, has practiced thrift the cost, has increased the practicality of device.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a rear front view of the assembly to be processed according to the present invention.
Fig. 3 is a rear side view of the installation of the to-be-processed assembly of the present invention.
Fig. 4 is a top view of the section a-a of the utility model after the installation of the to-be-processed assembly.
Fig. 5 is a side view of the utility model with a section B-B after the installation of the components to be processed.
Fig. 6 is the utility model discloses a waiting to process subassembly installation rear axle and survey the intention.
Fig. 7 is a top partial cross-sectional view of the clamping mechanism of the present invention.
Fig. 8 is an axial direction view of the waiting-to-be-processed assembly when clockwise rotating to form a 45-degree hole.
Fig. 9 is an axial direction view of the to-be-processed component of the present invention when the to-be-processed component rotates counterclockwise for 45 degrees.
As shown in the figure: 1. the drilling device comprises a mounting base, 2, a fixing column, 3, a mounting column, 4, an adjusting stud, 5, a rotating bearing, 6, a rotating rod, 7, a positioning head, 8, a positioning frame, 9, a bolt I, 10, a drilling positioning block, 11, a clamping block, 12, a fixing frame, 13, a bolt II, 14, a rotating plate, 15, an undercarriage front end component, 16, a rotating rod, 17, an undercarriage rear end component, 18, 1 to-be-drilled, 19, 2 to-be-drilled, 20, 3 to-be-drilled, and 21, 4 to-be-drilled.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted", "provided", "sleeved/connected", "connected", and the like are to be understood in a broad sense, such as "connected", which may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Referring to fig. 1-9, in an embodiment of the present invention, an aircraft nose landing gear assembly hole drilling fixture process apparatus includes an installation base 1, a clamping mechanism, a positioning frame 8, a clamping block 11 and a fixing frame 12, where the installation base 1 is set to a "bowling ball" shape, the installation base 1 is a solid structure with a balancing block, the circular end of the installation base 1 is welded with the clamping mechanism, the clamping mechanism is composed of a fixed column 2, an installation column 3 and an adjusting stud 4, the bottom end of the fixed column 2 is welded on the circular end of the installation base 1, the top end of the fixed column 2 is welded with the installation column 3, the diameter of the installation column 3 is smaller than that of the fixed column 2, the top end of the installation column 3 is provided with a threaded hole, the diameter of the threaded hole is the same as that of the adjusting stud 4, and is used for installing the adjusting stud 4, one end of the adjusting stud 4 penetrates out of the, meanwhile, a groove is formed in the other end of the adjusting stud 4, a rotating bearing 5 is fixedly installed in the groove, a rotating rod 6 is rotatably connected in the rotating bearing 5, a positioning head 7 is welded at one end, far away from the rotating bearing 5, of the rotating rod 6, and the top end of the positioning head 7 is arranged to be conical and used for supporting a front end component 15 of the undercarriage; meanwhile, a symmetrically-installed positioning frame 8 is welded at the middle position of the installation base 1 through a first bolt 9, a threaded hole is formed in the side face of the top end of the positioning frame 8, the circle center of the threaded hole and the circle center of the adjusting stud 4 are on the same straight line and used for clamping a rotating rod 16, a drilling positioning block 10 is installed at the top end of the positioning frame 8 through the first bolt 9, four holes to be drilled are formed in the surface of the drilling positioning block 10, the holes to be drilled are designed according to actual needs, a hole to be drilled 18 No. 1 and a hole to be drilled 19 No. 2 are symmetrically formed in two sides of the drilling positioning block 10, a hole to be drilled 20 No. 3 and a hole to be drilled 21 No. 4 are installed at the front end of the middle of the drilling positioning block 10, and the hole to be drilled; meanwhile, a symmetrical fixing frame 12 is arranged at the tail end of the mounting base 1 through a second bolt 13, and a circular through hole is formed in the side face of the top end of the fixing frame 12 and used for installing a clamping bolt to clamp a rear end component 17 of the undercarriage.
Clamping blocks 11 are symmetrically welded between the clamping mechanism and the positioning frame 8, rectangular grooves are formed in the top ends of the clamping blocks 11, the width of each groove is equal to the thickness of the rotating plate 14, and threaded holes are formed in the two sides of each groove and used for fixing the rotating plate 14; the rotating plate 14 is designed to be wing-shaped, meanwhile, a round hole with the same diameter as that of the undercarriage front end assembly 15 is formed in the middle of the rotating plate 14, a buckle is arranged on one side of the round hole and used for fixing the rotating plate 14 on the undercarriage front end assembly 15 and driving the undercarriage front end assembly 15 to rotate, meanwhile, threaded holes are formed in two side wings of the rotating plate 14, the diameter of each threaded hole is the same as that of the threaded hole in the clamping block 11, and when the rotating plate 14 does not rotate, the threaded holes in two sides of the rotating plate 14 are located above the groove of the clamping block 11.
The rotating rod 16 and the undercarriage middle-end component are the same in size, and are mutually matched with the undercarriage front-end component 15 and the undercarriage rear-end component 17 to be mounted and then fixed on the positioning frame 8, the design of the rotating rod 16 ensures that through bolt holes must be matched and drilled together to eliminate the assembly precision of the position error of the holes when parts of rotating parts such as shaft sleeves are combined, meanwhile, the rotating rod 16 is prevented from being used for replacing the undercarriage middle-end component, and the situation that scratches are generated on the surface of the undercarriage middle-end component by fixing bolts of the positioning frame 8 to influence the use of the undercarriage is prevented.
When an operator uses the utility model to drill the assembly hole of the undercarriage, the operator firstly clamps the rotating plate 14 at the corresponding position of the front end of the undercarriage front end assembly 15, and simultaneously removes the drilling positioning block 10 and rotates the adjusting stud 4 to move back as far as possible so as to install the part to be processed; then, sleeving a rear end component of a front end component 15 of the undercarriage on a rotating rod 16, fixing the rotating rod 16 on a positioning frame 8 by using a pin, rotatably installing the rear end component 17 of the undercarriage at the tail end of the rotating rod 16, fixing the rear end component 17 of the undercarriage on a fixed frame 12 by using the pin, after the fixing is finished, rotating an adjusting stud 4 to prop a positioning head 7 on the front end surface of the front end component 15 of the undercarriage, clamping a machined part, then installing a drilling positioning plate 10 on the positioning frame 8, and then starting machining operation; firstly, the rotating plate is in a horizontal position, the machining of the No. 1 to-be-drilled hole 18 and the No. 2 to-be-drilled hole 19 is completed, the reamer is used for trimming, then the rotating plate 14 is fixed on the clamping block 11 after rotating clockwise by 45 degrees, the machining of the No. 3 to-be-drilled hole 20 is completed, the reamer is used for trimming, finally the rotating plate is fixed on the clamping block 11 after rotating anticlockwise by 135 degrees, the machining of the No. 4 to-be-drilled hole 21 is completed, the reamer is used for trimming, and finally the machined assembly is detached.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments or portions thereof without departing from the spirit and scope of the invention, and the following claims are therefore to be read in this light of the appended claims.
Claims (6)
1. The utility model provides an anchor clamps process units that aircraft nose landing gear pilot hole joined in marriage brill, includes installation base (1), clamping mechanism, locating rack (8), grip block (11) and mount (12), its characterized in that: the clamping mechanism is composed of a fixed column (2), a mounting column (3) and an adjusting stud (4), the bottom end of the fixed column (2) is welded on the circular end portion of the mounting base (1), the mounting column (3) is welded at the top end of the fixed column (2), the diameter of the mounting column (3) is smaller than that of the fixed column (2), a threaded hole is formed in the top end of the mounting column (3), the diameter of the threaded hole is the same as that of the adjusting stud (4), one end of the adjusting stud (4) penetrates out of the threaded hole of the mounting column (3), a groove is formed in the other end of the adjusting stud (4), a rotating bearing (5) is fixedly installed in the groove, a rotating rod (6) is rotatably connected in the rotating bearing (5), and a positioning head (7) is welded at one end, far away from the rotating bearing (5); meanwhile, a symmetrically-installed positioning frame (8) is welded at the middle position of the installation base (1) through a first bolt (9), a threaded hole is formed in the side face of the top end of the positioning frame (8), the circle center of the threaded hole and the circle center of the adjusting stud (4) are on the same straight line and used for clamping the rotating rod (16), and meanwhile, a drilling positioning block (10) is installed at the top end of the positioning frame (8) through the first bolt (9); meanwhile, a symmetrical fixing frame (12) is arranged at the tail end of the mounting base (1) through a second bolt (13), and a circular through hole is formed in the side face of the top end of the fixing frame (12).
2. The jig process device for the pilot hole matched drilling of the nose landing gear of the aircraft according to claim 1, wherein the jig process device comprises the following steps: the clamping block (11) is symmetrically welded between the clamping mechanism and the positioning frame (8), a rectangular groove is formed in the top end of the clamping block (11), the width of the groove is the same as the thickness of the rotating plate (14), and threaded holes are formed in two sides of the groove.
3. The jig process device for the pilot hole matched drilling of the nose landing gear of the aircraft according to claim 2, wherein the jig process device comprises the following steps: the rotating plate (14) is designed to be wing-shaped, meanwhile, a round hole with the same diameter as that of the undercarriage front end assembly (15) is formed in the middle of the rotating plate (14), a buckle is arranged on one side of the round hole, threaded holes are formed in two side wings of the rotating plate (14), and the diameter of each threaded hole is the same as that of each threaded hole in the clamping block (11).
4. The jig process device for the pilot hole matched drilling of the nose landing gear of the aircraft according to claim 1, wherein the jig process device comprises the following steps: the rotary rod (16) and the landing gear middle end assembly are the same in size.
5. The jig process device for the pilot hole matched drilling of the nose landing gear of the aircraft according to claim 1, wherein the jig process device comprises the following steps: the top end of the positioning head (7) is arranged to be conical.
6. The jig process device for the pilot hole matched drilling of the nose landing gear of the aircraft according to claim 1, wherein the jig process device comprises the following steps: the mounting base (1) is arranged in a bowling shape, and the mounting base (1) is of a solid structure with a balancing weight.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020569131.2U CN213351580U (en) | 2020-04-16 | 2020-04-16 | Fixture process device for matched drilling of aircraft nose landing gear assembly hole |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020569131.2U CN213351580U (en) | 2020-04-16 | 2020-04-16 | Fixture process device for matched drilling of aircraft nose landing gear assembly hole |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213351580U true CN213351580U (en) | 2021-06-04 |
Family
ID=76126427
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020569131.2U Expired - Fee Related CN213351580U (en) | 2020-04-16 | 2020-04-16 | Fixture process device for matched drilling of aircraft nose landing gear assembly hole |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213351580U (en) |
-
2020
- 2020-04-16 CN CN202020569131.2U patent/CN213351580U/en not_active Expired - Fee Related
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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: 20210604 |
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| CF01 | Termination of patent right due to non-payment of annual fee |