CN106392720A - Missile rudder piece tool fixture - Google Patents
Missile rudder piece tool fixture Download PDFInfo
- Publication number
- CN106392720A CN106392720A CN201610914132.4A CN201610914132A CN106392720A CN 106392720 A CN106392720 A CN 106392720A CN 201610914132 A CN201610914132 A CN 201610914132A CN 106392720 A CN106392720 A CN 106392720A
- Authority
- CN
- China
- Prior art keywords
- block
- rudder piece
- missile rudder
- guided missile
- trapezoid
- 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.)
- Granted
Links
- 241000826860 Trapezium Species 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims 1
- 230000009286 beneficial effect Effects 0.000 abstract 1
- 238000000034 method Methods 0.000 description 3
- 230000007717 exclusion Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q3/00—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
- B23Q3/02—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine for mounting on a work-table, tool-slide, or analogous part
- B23Q3/06—Work-clamping means
- B23Q3/08—Work-clamping means other than mechanically-actuated
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Carbon And Carbon Compounds (AREA)
- Toys (AREA)
Abstract
The invention discloses a missile rudder piece tool fixture. The missile rudder piece tool fixture comprises a bottom plate, a stop block, a trapezoid block and an air cylinder. The bottom plate comprises a first part and a second part, the second part is arranged on the right side of the first part and is lower than the first part, and the upper surface of the first part is provided with a tenon-shaped groove which completely penetrates through the right side of the first part and does not penetrate through the left side of the first part; the stop block is arranged in the tenon-shaped groove; a spring A is arranged between the stop block and the left side of the first part in the horizontal direction; a trapezoid cavity is formed in the position, close to the lower portion of the right end of the tenon-shaped groove, of the interior of the first part; the trapezoid block is placed in the trapezoid cavity; a spring B is fixed under the trapezoid block and is connected to a first part body in the bevel direction of the trapezoid cavity; a push plate is arranged on the right side of the trapezoid block and penetrates through the first part through a push rod to be connected with the air cylinder; the air cylinder is arranged on the upper surface of the second part; and a through hole is formed in the position, corresponding to the push rod, of the first part. The missile rudder piece tool fixture has the beneficial effects that the automation degree and the production efficiency are high, and the labor intensity is relieved.
Description
Technical field
The present invention relates to the technical field of missile weapon system centered rudder piece processing, particularly guided missile rudder piece frock clamp.
Background technology
Clamping on lathe for the guided missile rudder piece is relatively difficult process at present, and staff, when being operated, needs
Using various supports and backing plate, operation is wasted time and energy, and leads to production efficiency not high, and when operated by personnel is unfamiliar with,
Often make the clamping force of guided missile rudder piece not, not only affect the crudy of next step, be also easy to cause danger.
Content of the invention
It is an object of the invention to overcoming the shortcoming of prior art, providing that automaticity is higher, production efficiency is high, reducing work
The guided missile rudder piece frock clamp of intensity.
The purpose of the present invention is achieved through the following technical solutions：Guided missile rudder piece frock clamp, including base plate, block, ladder
Shape block and cylinder, described base plate includes I and II, II right side being arranged on I and I ratio II is high, I upper surface
Have tenon shape groove, tenon shape groove completely through the right side of I and does not run through the left side of I, in tenon shape groove, be provided with block, block with
Horizontally disposed between I left side have spring A, is provided with trapezoidal chamber, in trapezoidal chamber in I below tenon shape groove right-hand member
It is placed with trapezoid block, below trapezoid block, is fixed with spring B, spring B is connected on I body along the bevel direction in trapezoidal chamber, ladder
The right side of shape block is provided with push pedal, and push pedal passes through I and cylinders by push rod, and cylinder is arranged on the upper surface of II, I
Corresponding push rod position has through hole.
The bottom surface of described block is adapted with tenon shape groove.
Described trapezoidal chamber and trapezoid block are right-angled trapezium, and the inclined-plane of trapezoidal chamber and trapezoid block contacts.
I left side of described base plate is provided with rotating shaft.
Described rotating shaft is fixed on lathe by chuck.
The present invention has advantages below：Automaticity is higher, production efficiency is high, reduce labour intensity.
Brief description
Fig. 1 is the structural representation of the present invention；
Fig. 2 is the right view of invention；
In figure, 1 base plate, 2 blocks, 3 trapezoid blocks, 4 cylinders, 5 tenon shape grooves, 6 spring A, 7 trapezoidal chambeies, 8 bullets
Spring B, 9 push pedals, 10 rotating shafts.
Specific embodiment
The present invention will be further described below in conjunction with the accompanying drawings, and protection scope of the present invention is not limited to described below：
As depicted in figs. 1 and 2, guided missile rudder piece frock clamp, including base plate 1, block 2, trapezoid block 3 and cylinder 4, described base plate
1 includes I and II, and II right side being arranged on I and portion are high, and I upper surface is provided with tenon shape groove 5, and tenon shape groove 5 passes through completely
The right side wearing I and the left side not running through I, are placed with guided missile rudder piece in tenon shape groove 5, be provided with block 2 in tenon shape groove 5, gear
Block 2 is located at the left side of guided missile rudder piece, and the bottom surface of block 2 is adapted with tenon shape groove 5, between block 2 and I left side in the horizontal direction
It is provided with spring A6, spring A6 makes baffle plate 2 produce a power to the right to guided missile rudder piece, in I under tenon shape groove 5 right-hand member
Side is provided with trapezoidal chamber 7, is placed with trapezoid block 3, trapezoidal chamber 7 and trapezoid block 3 are right-angled trapezium and trapezoidal chamber 7 in trapezoidal chamber 7
Contact with the inclined-plane of trapezoid block 3, below trapezoid block 3, the bevel direction along trapezoidal chamber 7 is provided with spring B 8, the two ends of spring B 8
It is connected on trapezoid block 3 and I body, the right side of trapezoid block 3 is provided with push pedal 9, push pedal 9 and trapezoid block 3 sliding contact,
Push pedal 9 is fixed on one end of push rod, and the other end of push rod is connected on cylinder 4 through I, and cylinder 4 is located at the upper surface of II,
I corresponding push rod position has through hole, and I left end of base plate 1 is fixed with rotating shaft 10, and rotating shaft 10 is fixed on lathe by chuck
On.
During work, cylinder 4 drives push pedal 9 to move to the right side in trapezoidal chamber 7, and trapezoid block 3 is in the lower section in trapezoidal chamber 7, will
Guided missile rudder piece is put in tenon shape groove 5 by manipulator, now guided missile rudder piece be located at trapezoidal chamber 7 upper left side, the one of guided missile rudder piece
Part is located at the top in trapezoidal chamber 7 and another part is not in the top in trapezoidal chamber 7, and guided missile rudder piece is not contacted with block 2；
Push pedal 9 is promoted to be moved to the left by cylinder 4 again, push pedal 9 promotes trapezoid block 3 to be moved to the left along the inclined-plane in trapezoidal chamber 7, trapezoid block
3 are contacted with guided missile rudder piece in moving process and promote guided missile rudder piece to be moved to the left, and guided missile rudder piece drives baffle plate 2 to moving to left
Move so that spring A6 is in compressive state and produces a power to the right, it is achieved thereby that baffle plate 2 and push pedal 9 are to guided missile rudder piece
Clamping, now spring B 8 be in extended state；Rotating shaft 10 is driven to rotate by lathe, coplanar does not enter to the guided missile rudder piece clamping
Row processing, after completion of processing, cylinder 4 drives push pedal 9 to move right, and trapezoid block 3 is in the presence of spring B 8 along trapezoidal chamber 7
Inclined-plane moves right, and is finally moved to the lower right in trapezoidal chamber 7, guided missile rudder piece in the presence of spring A6 pass through baffle plate 2 by its
Release, when guided missile rudder piece does not move to specified location in tenon shape groove 5, manually moved, then pass through mechanical arm
Guided missile rudder piece is removed；Mechanical arm, cylinder are all that manual steps are few by controller control, high degree of automation, dress
Clip process is quick, improves production efficiency, reduces labour intensity.
The above be only the preferred embodiment of the present invention it should be understood that the present invention be not limited to described herein
Form, is not to be taken as the exclusion to other embodiment, and can be used for various other combinations, modification and environment, and can be at this
In the described contemplated scope of literary composition, it is modified by the technology or knowledge of above-mentioned teaching or association area.And those skilled in the art are entered
The change of row and change, then all should be in the protection domains of claims of the present invention without departing from the spirit and scope of the present invention
Interior.
Claims (5)
1. guided missile rudder piece frock clamp it is characterised in that：Including base plate（1）, block（2）, trapezoid block（3）And cylinder（4）, described
Base plate（1）Including I and II, II right side being arranged on I and I ratio II is high, I upper surface has tenon shape groove
（5）, tenon shape groove（5）Right side completely through I and do not run through the left side of I, tenon shape groove（5）In be provided with block（2）, block
（2）Horizontally disposed and I left side between have spring A（6）, near tenon shape groove in I（5）It is provided with trapezoidal below right-hand member
Chamber（7）, trapezoidal chamber（7）In be placed with trapezoid block（3）, trapezoid block（3）Lower section is fixed with spring B（8）, spring B（8）Along trapezoidal chamber
（7）Bevel direction be connected on I body, trapezoid block（3）Right side be provided with push pedal（9）, push pedal（9）Passed through by push rod
I and cylinder（4）It is connected, cylinder（4）It is arranged on the upper surface of II, I corresponding push rod position has through hole.
2. guided missile rudder piece frock clamp according to claim 1 it is characterised in that：Described block（2）Bottom surface and tenon
Shape groove（5）Be adapted.
3. guided missile rudder piece frock clamp according to claim 1 it is characterised in that：Described trapezoidal chamber（7）And trapezoid block
（3）It is right-angled trapezium, and trapezoidal chamber（7）And trapezoid block（3）Inclined-plane contact.
4. guided missile rudder piece frock clamp according to claim 1 it is characterised in that：Described base plate（1）I left side set
It is equipped with rotating shaft（10）.
5. guided missile rudder piece frock clamp according to claim 4 it is characterised in that：Described rotating shaft（10）Solid by chuck
It is scheduled on lathe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610914132.4A CN106392720B (en) | 2016-10-20 | 2016-10-20 | Guided missile rudder piece frock clamp |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610914132.4A CN106392720B (en) | 2016-10-20 | 2016-10-20 | Guided missile rudder piece frock clamp |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106392720A true CN106392720A (en) | 2017-02-15 |
| CN106392720B CN106392720B (en) | 2018-08-28 |
Family
ID=58012717
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610914132.4A Active CN106392720B (en) | 2016-10-20 | 2016-10-20 | Guided missile rudder piece frock clamp |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106392720B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112377787A (en) * | 2020-11-14 | 2021-02-19 | 徐州长航科技有限公司 | Display installation device of crane |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4114868A (en) * | 1978-01-09 | 1978-09-19 | Smith Daniel Wm | Work aligning vise jaw |
| CN202240967U (en) * | 2011-10-19 | 2012-05-30 | 潘济安 | Soft nip vise |
| CN202479848U (en) * | 2012-03-19 | 2012-10-10 | 中核(天津)科技发展有限公司 | Automatic location clamp device |
| CN102873383A (en) * | 2012-09-26 | 2013-01-16 | 湖北三江航天江北机械工程有限公司 | Processing method of nonmetal special-shaped rudder sheet and clamp for processing |
| CN203726373U (en) * | 2014-01-26 | 2014-07-23 | 梁官寿 | Wedge-caulking parallel mechanical clamp |
| CN103978452A (en) * | 2014-06-11 | 2014-08-13 | 重庆市丰收农机制造有限公司 | Oblique-plane ejector pad clamping device |
| CN104289949A (en) * | 2014-10-27 | 2015-01-21 | 北京海普瑞森科技发展有限公司 | Clamp device |
| CN104476277A (en) * | 2014-12-10 | 2015-04-01 | 成都市翻鑫家科技有限公司 | Self-resetting drilling fixture |
-
2016
- 2016-10-20 CN CN201610914132.4A patent/CN106392720B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4114868A (en) * | 1978-01-09 | 1978-09-19 | Smith Daniel Wm | Work aligning vise jaw |
| CN202240967U (en) * | 2011-10-19 | 2012-05-30 | 潘济安 | Soft nip vise |
| CN202479848U (en) * | 2012-03-19 | 2012-10-10 | 中核(天津)科技发展有限公司 | Automatic location clamp device |
| CN102873383A (en) * | 2012-09-26 | 2013-01-16 | 湖北三江航天江北机械工程有限公司 | Processing method of nonmetal special-shaped rudder sheet and clamp for processing |
| CN203726373U (en) * | 2014-01-26 | 2014-07-23 | 梁官寿 | Wedge-caulking parallel mechanical clamp |
| CN103978452A (en) * | 2014-06-11 | 2014-08-13 | 重庆市丰收农机制造有限公司 | Oblique-plane ejector pad clamping device |
| CN104289949A (en) * | 2014-10-27 | 2015-01-21 | 北京海普瑞森科技发展有限公司 | Clamp device |
| CN104476277A (en) * | 2014-12-10 | 2015-04-01 | 成都市翻鑫家科技有限公司 | Self-resetting drilling fixture |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112377787A (en) * | 2020-11-14 | 2021-02-19 | 徐州长航科技有限公司 | Display installation device of crane |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106392720B (en) | 2018-08-28 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: Missile rudder piece tool fixture Effective date of registration: 20200720 Granted publication date: 20180828 Pledgee: Agricultural Bank of China Limited Chengdu Economic and Technological Development Zone sub branch Pledgor: CHENGDU JIUXIN TIMES TECHNOLOGY Co.,Ltd. Registration number: Y2020510000075 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Granted publication date: 20180828 Pledgee: Agricultural Bank of China Limited Chengdu Economic and Technological Development Zone sub branch Pledgor: CHENGDU JIUXIN TIMES TECHNOLOGY CO.,LTD. Registration number: Y2020510000075 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: Missile rudder blade fixture Granted publication date: 20180828 Pledgee: Agricultural Bank of China Limited Chengdu Economic and Technological Development Zone sub branch Pledgor: CHENGDU JIUXIN TIMES TECHNOLOGY CO.,LTD. Registration number: Y2024510000035 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right |