CN205290796U - Guided missile airvane launches component Assembly frock - Google Patents
Guided missile airvane launches component Assembly frock Download PDFInfo
- Publication number
- CN205290796U CN205290796U CN201521050911.1U CN201521050911U CN205290796U CN 205290796 U CN205290796 U CN 205290796U CN 201521050911 U CN201521050911 U CN 201521050911U CN 205290796 U CN205290796 U CN 205290796U
- Authority
- CN
- China
- Prior art keywords
- airvane
- depression bar
- bearing pin
- guided missile
- bottom plate
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
The utility model relates to a guided missile airvane launches component Assembly frock both ends is equipped with closing device respectively and from positioner at the bottom plate about, wherein does from the positioner structure, and the bottom plate upper surface has welded a little sleeve pipe, is equipped with the round pin axle in the counter sink of bottom plate bottom, and the bottom plate upper surface stretches out in round pin crown of roll portion to with the coaxial setting of little sleeve pipe, the closing device structure does, is equipped with upright wall at the upper surface of bottom plate, founds the upper end swing joint depression bar of wall, is equipped with locating hole, the center and a round pin coaxial setting of locating hole at the center of depression bar. Should launch component Assembly frock simple structure, the location is accurate moreover to improve rudder axle marking off airvane and launched the production efficiency and the product quality of component Assembly process.
Description
Technical field
This utility model relates to a kind of guided missile airvane and launches assembly assembly tooling, belongs to a kind of tool structure.
Background technology
It is known that according to drawing requirement by single several assembling parts together, be called assembling. Assembly work is an important step in machining, as the saying goes that volume basket is compiled basket and entirely closed up. Conventional assembly tool is various spanner, pliers, hammer, jaws of vise, screwdriver etc., but common tool can not meet the requirement of some assembly works sometimes, need to complete by other equipment or special tooling.
In the past, when not design, manufacture guided missile airvane launch assembly assembly tooling, launch the assembling of assembly to compress stop pin I completely by hand and complete, two stage clips are had in assembly owing to launching, to upper lifting force, stop pin I face area is little more greatly, in addition and has smooth bevel on cylindrical, wanting to compress stop pin I makes pinning screw thread expose so that nutting, wastes time and energy very much. Careless slightly very easily pinning touched curved or touch folding, directly affecting total packing quality of whole airvane, thus the assembling progress of whole body when affecting general assembly. Therefore, causing the waste of manpower and materials, also had a strong impact on manufacturing schedule, meanwhile, the production efficiency of assembly process is relatively low.
Summary of the invention
The technical problems to be solved in the utility model is to provide a kind of guided missile airvane and launches assembly assembly tooling, this launches assembly assembly tooling simple in construction, and accurate positioning, thus improve rudderpost line airvane to launch production efficiency and the product quality of assembly assembly process.
For solving problem above, concrete technical scheme of the present utility model is as follows: a kind of guided missile airvane launches assembly assembly tooling, hold down gag and self locating device it is respectively arranged at two ends with in the left and right of base plate, wherein self locating device structure is, plate upper surface is welded with a small casing, being provided with bearing pin in counter sink bottom base plate, plate upper surface is stretched out at bearing pin top, and is coaxially disposed with small casing; Hold down gag structure is, the upper surface at base plate is provided with wall, and the upper end of wall is flexibly connected depression bar, is provided with hole, location at the center of depression bar, and the center in hole, location is coaxially disposed with bearing pin.
The end strip hole that described depression bar is flexibly connected with wall, the rotating shaft that depression bar is connected with wall is positioned at strip hole.
Described hole, location is made up of cylindrical set and inner circle set, and inner circle set excircle is symmetrical arranged bearing pin, and inner circle set is flexibly connected with cylindrical set by bearing pin, and the axis of bearing pin is vertically arranged in the horizontal plane with depression bar axis.
This guided missile airvane launches assembly assembly tooling and adopts elastic parts self locating device to be undertaken spacing by part to be assembled, then pass through hold down gag the assembly after assembling is compressed, then pass through hole, location to expose screw rod and pass through nut check, thus completing the assembling of black box, this frock is adopted to improve work efficiency.
In depression bar end strip hole structure, it is possible to regulate the lateral separation in hole, location and bearing pin.
Hole, location adopts inner circle set and cylindrical nested structure, it is possible to regulate the fore-and-aft distance in hole, location.
Accompanying drawing explanation
Fig. 1 is the sectional plan view that guided missile airvane launches assembly assembly tooling.
Fig. 2 is depression bar front view.
Fig. 3 is depression bar top view.
Fig. 4 is that guided missile airvane launches assembly assembly tooling working state schematic representation.
Detailed description of the invention
As shown in Figure 1, a kind of guided missile airvane launches assembly assembly tooling, hold down gag 10 and self locating device 20 it is respectively arranged at two ends with in the left and right of base plate 1, wherein self locating device 20 structure is, base plate 1 upper surface is welded with a small casing 2, being provided with bearing pin 3 in counter sink bottom base plate 1, base plate 1 upper surface is stretched out at bearing pin 3 top, and is coaxially disposed with small casing 2; Hold down gag 10 structure is, the upper surface at base plate 1 is provided with wall 4, and the upper end of wall 4 is flexibly connected depression bar 5, is provided with hole 30, location at the center of depression bar 5, and the center in hole 30, location is coaxially disposed with bearing pin 3.
The end strip hole 6 that described depression bar 5 is flexibly connected with wall 4, the rotating shaft that depression bar 5 is connected with wall 4 is positioned at strip hole 6.
As shown in Figures 2 and 3, described hole, location 30 is made up of cylindrical set 7 and inner circle set 8, and inner circle is overlapped and is symmetrical arranged bearing pin 9 on 8 excircles, and inner circle set 8 overlaps 7 by bearing pin 9 with cylindrical and is flexibly connected, and the axis of bearing pin and depression bar 5 axis are vertically arranged in the horizontal plane.
As shown in Figure 4, guided missile airvane launches the work process of assembly assembly tooling: when launching assembly assembling, the shell bottom launching assembly is inserted from small casing 2 hole of positioner 20, grasp depression bar 5 handle, adjust inner circle on depression bar to overlap 8 centers alignments and launch assembly parts center, and overlap 8 workpiece pressings by inner circle, so that pinning screw thread exposes, Quick fastening nut and then reach the purpose quick and precisely assembled, improve guided missile airvane and launch quality and the progress that assembly produces.
Claims (3)
1. a guided missile airvane launches assembly assembly tooling, it is characterized in that: be respectively arranged at two ends with hold down gag (10) and self locating device (20) in the left and right of base plate (1), wherein self locating device (20) structure is, base plate (1) upper surface is welded with a small casing (2), it is provided with bearing pin (3) in the counter sink of base plate (1) bottom, base plate (1) upper surface is stretched out at bearing pin (3) top, and is coaxially disposed with small casing (2); Hold down gag (10) structure is, upper surface at base plate (1) is provided with wall (4), the upper end of wall (4) is flexibly connected depression bar (5), is provided with hole, location (30) at the center of depression bar (5), and the center of hole, location (30) and bearing pin (3) are coaxially disposed.
2. guided missile airvane as claimed in claim 1 launches assembly assembly tooling, it is characterised in that: the end strip hole (6) that described depression bar (5) is flexibly connected with wall (4), the rotating shaft that depression bar (5) is connected with wall (4) is positioned at strip hole (6).
3. guided missile airvane as claimed in claim 1 launches assembly assembly tooling, it is characterized in that: described hole, location (30) is made up of cylindrical set (7) and inner circle set (8), inner circle set (8) excircle is symmetrical arranged bearing pin (9), inner circle set (8) is flexibly connected with cylindrical set (7) by bearing pin (9), and the axis of bearing pin is vertically arranged in the horizontal plane with depression bar (5) axis.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521050911.1U CN205290796U (en) | 2015-12-16 | 2015-12-16 | Guided missile airvane launches component Assembly frock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521050911.1U CN205290796U (en) | 2015-12-16 | 2015-12-16 | Guided missile airvane launches component Assembly frock |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205290796U true CN205290796U (en) | 2016-06-08 |
Family
ID=56431905
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521050911.1U Expired - Fee Related CN205290796U (en) | 2015-12-16 | 2015-12-16 | Guided missile airvane launches component Assembly frock |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205290796U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106425926A (en) * | 2016-10-20 | 2017-02-22 | 成都久欣时代科技有限公司 | Pressing type guided missile warhead fixture |
| CN110587538A (en) * | 2019-09-30 | 2019-12-20 | 北京航天新风机械设备有限责任公司 | Cover extracting tool behind air vane |
-
2015
- 2015-12-16 CN CN201521050911.1U patent/CN205290796U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106425926A (en) * | 2016-10-20 | 2017-02-22 | 成都久欣时代科技有限公司 | Pressing type guided missile warhead fixture |
| CN106425926B (en) * | 2016-10-20 | 2018-07-24 | 成都久欣时代科技有限公司 | A kind of top-closed structure guided missile head frock clamp |
| CN110587538A (en) * | 2019-09-30 | 2019-12-20 | 北京航天新风机械设备有限责任公司 | Cover extracting tool behind air vane |
| CN110587538B (en) * | 2019-09-30 | 2024-04-19 | 北京新风航天装备有限公司 | Air rudder rear cover detaching tool |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160608 Termination date: 20201216 |