CN106363440A - Missile rudder piece clamp - Google Patents

Missile rudder piece clamp Download PDF

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Publication number
CN106363440A
CN106363440A CN201610914136.2A CN201610914136A CN106363440A CN 106363440 A CN106363440 A CN 106363440A CN 201610914136 A CN201610914136 A CN 201610914136A CN 106363440 A CN106363440 A CN 106363440A
Authority
CN
China
Prior art keywords
groove
axle
fixed block
axle sleeve
clamping plate
Prior art date
Application number
CN201610914136.2A
Other languages
Chinese (zh)
Other versions
CN106363440B (en
Inventor
郭健辉
Original Assignee
成都久欣时代科技有限公司
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 成都久欣时代科技有限公司 filed Critical 成都久欣时代科技有限公司
Priority to CN201610914136.2A priority Critical patent/CN106363440B/en
Publication of CN106363440A publication Critical patent/CN106363440A/en
Application granted granted Critical
Publication of CN106363440B publication Critical patent/CN106363440B/en

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23QDETAILS, 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
    • B23Q3/00Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
    • B23Q3/02Devices 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
    • B23Q3/06Work-clamping means
    • B23Q3/08Work-clamping means other than mechanically-actuated

Abstract

The invention discloses an missile rudder piece clamp which comprises a shaft, a shaft sleeve, a hydraulic bearing, a clamping plate A and a clamping plate B; the outer part of the shaft is sleeved by the shaft sleeve; the hydraulic bearing is arranged between the shaft and the shaft sleeve; a plurality of grooves A, which are axially arranged in the axial direction, are formed in the end-head position inside the shaft sleeve, of the shaft; arc-shaped plates are arranged on the positions of the grooves A; the arc-shaped plates penetrate through the shaft sleeve through a connecting rod and are connected with an air cylinder; bumps which are adaptive to the grooves are arranged on surfaces, opposite to the grooves, of the arc-shaped plates; a fixed block A and a fixed block B are arranged on the end surface of the end head, positioned outside the shaft sleeve, of the shaft; handles which are matched through threads are separately arranged on the fixed block A and the fixed block B in the radial direction of the shaft; the clamping plate A and the clamping plate B are fixedly arranged on handle end heads inside the fixed block A and the fixed block B separately; and a groove B which is big in one end and is small in one end is formed in the outer surface of the hydraulic bearing, and the groove B is a trapezoid-shaped groove. The missile rudder piece clamp disclosed by the invention has the beneficial effects of being convenient in clamping, capable of rotating at any angle, long in service life and convenient for missile rudder piece processing.

Description

Guided missile rudder plate clamp

Technical field

The present invention relates to the technical field of missile weapon system centered rudder piece clamping, particularly guided missile rudder plate clamp.

Background technology

In missile parts and components, guided missile rudder piece to the flight of guided missile, steering, implement precision strike and play an important role. The clamping of traditional guided missile rudder piece is to carry out clamping by chuck to rudder piece using lathe, because chuck is difficult precise positioning in itself, Lead to that rudder piece crudy is bad, working (machining) efficiency is low, and by chuck fixing when can only be axially moveable it is impossible to move radially, Exist between processing unit (plant) and lathe during error it is difficult to correct, thus leading to be difficult to rudder piece is processed.

Content of the invention

It is an object of the invention to overcoming the shortcoming of prior art, provide convenient mounting and clamping, the arbitrarily angled rotation of energy, service life The guided missile rudder plate clamp of processing that is long, being easy to guided missile rudder piece.

The purpose of the present invention is achieved through the following technical solutions: guided missile rudder plate clamp, including axle, axle sleeve, fluid bearing, Clamping plate a and clamping plate b, is cased with axle sleeve outside described axle, one end of axle is stretched out the other end of axle outside axle sleeve and is located in axle sleeve, axle It is provided with fluid bearing and axle sleeve between;

Tip position within axle sleeve for the described axle position has multiple groove a along axle is axially arranged, on the corresponding axle sleeve of groove a Have through hole, in through hole, be placed with connecting rod, the termination within positioned at axle sleeve is fixed with arc, arc is relative with groove a Face is provided with the projection being adapted with groove a, the connecting rod termination outside axle sleeve and cylinders, end outside axle sleeve for the axle position Fixed block a and fixed block b is provided with end surface, fixed block a and fixed block b is respectively arranged with along Axial and radial and is joined by screw thread The handle closing, is respectively fixed with clamping plate a and clamping plate b, clamping plate a and folder on the tiller grip of fixed block a and the inner side of fixed block b The tenon shape groove being adapted with guided missile rudder piece is provided with the corresponding face of plate b;

The little groove b in the big one end in one end is had on described fluid bearing outer surface, groove b is dovetail groove, the two of fluid bearing Individual end is provided with sealing device, is provided with oil inlet pipe in the big sealing device of groove b opening, near groove b opening It is provided with flowline, oil inlet pipe and flowline continuous boss in little sealing device.

Have upper and lower two through holes on the described corresponding axle sleeve of groove a, be provided with connecting rod in each through hole, up and down Connecting rod termination in through hole is provided with arc and cylinder.

It is provided with gap between described sealing device and fluid bearing.

The little one end of groove b on described fluid bearing is arranged near axle sleeve port, and the groove b on fluid bearing is big One end is arranged near groove a.

Described axle is provided with the diameter less than non-recessing a position on axle for the diameter at groove a position.

The invention has the advantages that

(1) by arranging, on clamping plate a and clamping plate b, the tenon shape groove matching with guided missile rudder piece, and clamping plate a and clamping plate b is passed through Handle is realized moving, and is easy to the clamping of guided missile rudder piece;

(2) fluid bearing is set, realizes rudder piece and rotate at any angle, by arranging cylinder, arc and groove a, realize rudder The positioning of piece corner, is easy to the processing of guided missile rudder piece all directions;

(3) pass through the little groove b in the big one end in one end is had on fluid bearing, by arranging oil inlet pipe and flowline, when passing through When arc carrys out fixing axle rotation, it is soft impulse between axle and hydraulic oil, key position not easy damaged, long service life.

Brief description

Fig. 1 is the structural representation of the present invention;

Fig. 2 is the structural representation of fluid bearing;

In figure, 1 axle, 2 axle sleeves, 3 fluid bearings, 4 clamping plate a, 5 clamping plate b, 6 groove a, 7 arcs, 8 gas Cylinder, 9 fixed block a, 10 fixed block b, 11 handles, 12 groove b, 13 sealing devices, 14 oil inlet pipes, 15 is fuel-displaced Pipe.

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 shown in figure 1, guided missile rudder plate clamp, including plate clamp, including axle 1, axle sleeve 2, fluid bearing 3, clamping plate a4 and clamping plate b5, It is cased with axle sleeve 2, one end of axle 1 stretches out that axle sleeve 2 is outer and the other end of axle 1 is located in axle sleeve 2, axle 1 and axle sleeve outside described axle 1 It is provided with fluid bearing 3 between 2;

The tip position that described axle 1 is located within axle sleeve 2 has multiple groove a6 along axle 1 is axially arranged, and axle 1 is provided with groove a6 The diameter at position is less than the diameter at non-recessing a6 position on axle 1, has through hole, in through hole on the corresponding axle sleeve of groove a6 2 Be placed with connecting rod, the termination within positioned at axle sleeve 2 is fixed with arc 7, arc 7 face relative with groove a6 be provided with recessed The projection that groove a6 is adapted, the connecting rod termination outside axle sleeve 2 is connected with cylinder 8, and axle 1 is located at the termination end face outside axle sleeve 2 On be provided with fixed block a9 and fixed block b10, fixed block a9 and fixed block b10 is respectively arranged with by screw thread along axle 1 radial direction The handle 11 of cooperation, is respectively fixed with clamping plate a4 and clamping plate on handle 11 termination of fixed block a9 and the inner side of fixed block b10 B5, clamping plate a4 and clamping plate b5 are provided with, on corresponding face, the tenon shape groove being adapted with guided missile rudder piece;

The little groove b12 in the big one end in one end is had on described fluid bearing 3 outer surface, groove b12 is dovetail groove, fluid bearing The little one end of groove b12 on 3 is arranged near axle sleeve 2 port, and the big one end of the groove b12 on fluid bearing 3 is near groove a6 Setting, two ends of fluid bearing 3 are provided with sealing device 13, are provided with gap between sealing device 13 and fluid bearing 3, It is provided with oil inlet pipe 14 in the big sealing device 13 of groove b12 opening, set in the little sealing device of groove b12 opening It is equipped with flowline 15, oil inlet pipe 14 and flowline 1 continuous boss 2.

During work, guided missile rudder piece is picked up by mechanical hand and is placed between fixed block a9 and fixed block 10b, by rotating Handle 11, by guided missile rudder piece clamping, due to beginning with tenon shape groove corresponding with guided missile rudder piece on fixed block a9 and fixed block b10, fills Folder is quick, convenient;By injecting hydraulic oil in oil inlet pipe 14 phase fluid bearing 3, the hydraulic oil in entrance fluid bearing 3 passes through recessed Groove b12 flows out from flowline 15, the one end being connected with flowline 15 greatly with the one end that is connected of oil inlet pipe 14 due to groove b12 Little, groove b12 is dovetail groove, is therefore rotated by fluxion strap fluid bearing 3 inner ring of hydraulic oil, and fluid bearing 3 inner ring drives Axle 1 rotates, and axle 1 drives the 360 degree of rotations of guided missile rudder piece, drives arc 7 radially to move along axle 1 by cylinder 8, arc Projection in 7 snaps in the groove a6 of axle 1 it is achieved that the braking of axle 1, it is achieved thereby that the braking of guided missile rudder piece.

In the present embodiment, the described corresponding axle sleeve of groove a6 2 has upper and lower two through holes, is respectively provided with each through hole There is connecting rod, the connecting rod termination in upper lower through-hole is provided with arc 7 and cylinder 8.

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 plate clamp it is characterised in that: include axle (1), axle sleeve (2), fluid bearing (3), clamping plate a(4) and clamping plate b (5), be cased with axle sleeve (2) outside described axle (1), one end of axle (1) stretch out axle sleeve (2) outward and the other end of axle (1) is located at axle In set (2), between axle (1) and axle sleeve (2), it is provided with fluid bearing (3);
Described axle (1) is located at the internal tip position of axle sleeve (2) has multiple groove a(6 along axle (1) is axially arranged), in groove a (6) have through hole on corresponding axle sleeve (2), in through hole, be placed with connecting rod, be fixed with arc positioned at the internal termination of axle sleeve (2) (7), arc (7) and groove a(6) relative face is provided with and groove a(6) projection that is adapted, positioned at axle sleeve (2) company outward Extension bar termination is connected with cylinder (8), and axle (1) is located at and is provided with fixed block a(9 on axle sleeve (2) termination end face outward) and fixed block b (10), fixed block a(9) and fixed block b(10) on be radially respectively arranged with, along axle (1), the handle (11) coordinating by screw thread, Fixed block a(9) and fixed block b(10) handle (11) termination of inner side on be respectively fixed with clamping plate a(4) and clamping plate b(5), folder Plate a(4) and clamping plate b(5) it is provided with the tenon shape groove being adapted with guided missile rudder piece on corresponding face;
The little groove b(12 in the big one end in one end is had on described fluid bearing (3) outer surface), groove b(12) it is dovetail groove, liquid Two ends that last item holds (3) are provided with sealing device (13), near groove b(12) set in the big sealing device of opening (13) It is equipped with oil inlet pipe (14), near groove b(12) it is provided with flowline (15) in the little sealing device of opening, oil inlet pipe (14) and going out Oil pipe (1) continuous boss (2).
2. guided missile rudder plate clamp according to claim 1 it is characterised in that: described groove a(6) corresponding axle sleeve (2) On have upper and lower two through holes, be provided with connecting rod in each through hole, the connecting rod termination in upper lower through-hole is provided with arc Shape plate (7) and cylinder (8).
3. guided missile rudder plate clamp according to claim 1 it is characterised in that: described sealing device (13) and fluid bearing (3) it is provided with gap between.
4. the guided missile rudder plate clamp according to claim 1 or 3 it is characterised in that: the groove on described fluid bearing (3) B(12) little one end is arranged near axle sleeve (2) port, the groove b(12 on fluid bearing (3)) big one end is near groove a(6) Setting.
5. guided missile rudder plate clamp according to claim 1 it is characterised in that: described axle (1) is provided with groove a(6) portion Position diameter be less than axle (1) on non-recessing a(6) position diameter.
CN201610914136.2A 2016-10-20 2016-10-20 Guided missile rudder plate clamp CN106363440B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201610914136.2A CN106363440B (en) 2016-10-20 2016-10-20 Guided missile rudder plate clamp

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201610914136.2A CN106363440B (en) 2016-10-20 2016-10-20 Guided missile rudder plate clamp

Publications (2)

Publication Number Publication Date
CN106363440A true CN106363440A (en) 2017-02-01
CN106363440B CN106363440B (en) 2018-08-10

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN201610914136.2A CN106363440B (en) 2016-10-20 2016-10-20 Guided missile rudder plate clamp

Country Status (1)

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CN (1) CN106363440B (en)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB233170A (en) * 1924-06-11 1925-05-07 Paul Fischer Clamping contrivance for use in connection with machines for cutting-off pipes
DE1477212A1 (en) * 1963-02-28 1969-03-13 Cincinnati Milling Machine Co Automatic device for changing tools
US6315799B1 (en) * 1998-11-09 2001-11-13 Romeo Toniolo Automatic device for replacing grinding wheels in machines for profiling and polishing works obtained from slabs of marble, granite stone, glass, stoneware, cement and the like
CN2578037Y (en) * 2002-09-12 2003-10-08 慈溪市三酉实业有限公司 Automatic clamp device for machine tool
CN201511137U (en) * 2009-09-25 2010-06-23 浙江陀曼精密机械有限公司 Main shaft mechanism capable of realizing automatic clamping
CN202985183U (en) * 2012-12-14 2013-06-12 铜陵市金利电子有限公司 Three-jaw disc-type fixture for drilling machine
CN204621882U (en) * 2015-03-24 2015-09-09 嘉善睿逸电子科技有限公司 A kind of adjustable fixture

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB233170A (en) * 1924-06-11 1925-05-07 Paul Fischer Clamping contrivance for use in connection with machines for cutting-off pipes
DE1477212A1 (en) * 1963-02-28 1969-03-13 Cincinnati Milling Machine Co Automatic device for changing tools
US6315799B1 (en) * 1998-11-09 2001-11-13 Romeo Toniolo Automatic device for replacing grinding wheels in machines for profiling and polishing works obtained from slabs of marble, granite stone, glass, stoneware, cement and the like
CN2578037Y (en) * 2002-09-12 2003-10-08 慈溪市三酉实业有限公司 Automatic clamp device for machine tool
CN201511137U (en) * 2009-09-25 2010-06-23 浙江陀曼精密机械有限公司 Main shaft mechanism capable of realizing automatic clamping
CN202985183U (en) * 2012-12-14 2013-06-12 铜陵市金利电子有限公司 Three-jaw disc-type fixture for drilling machine
CN204621882U (en) * 2015-03-24 2015-09-09 嘉善睿逸电子科技有限公司 A kind of adjustable fixture

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SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
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GR01 Patent grant
PE01 Entry into force of the registration of the contract for pledge of patent right

Denomination of invention: Missile rudder piece clamp

Effective date of registration: 20200720

Granted publication date: 20180810

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