CN103465216A - Device for disassembling piston in aircraft engine sheath opening actuator cylinder - Google Patents
Device for disassembling piston in aircraft engine sheath opening actuator cylinder Download PDFInfo
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- CN103465216A CN103465216A CN 201310365374 CN201310365374A CN103465216A CN 103465216 A CN103465216 A CN 103465216A CN 201310365374 CN201310365374 CN 201310365374 CN 201310365374 A CN201310365374 A CN 201310365374A CN 103465216 A CN103465216 A CN 103465216A
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Abstract
The invention discloses a device for disassembling a piston in an aircraft engine sheath opening actuator cylinder. The device comprises tooth rods, an inner rod, a connecting block, an impact block and a pull bar, wherein the tooth rods are a pair of rods with the same structure; each tooth rod comprises a semi-cylindrical flange tooth and a circular arc-shaped rod body, and the external diameter of the flange tooth is larger than that of the rod body; each tooth rod is provided with a through circular arc groove from the flange tooth to the rod body along the length direction; the rod bodies of the pair of tooth rods are connected with one end of the connecting block; openings of the circular arc grooves of the two tooth rods are opposite to each other; a gap is reserved between the opposite end surfaces of the two tooth rods; the pull bar is a T-shaped bar; the head of the T-shaped bar is a stress end; the impact block is sheathed at the rod part of the T-shaped bar and can move along the length direction of the rod part; the other end of the connecting block is connected with the rod part of the pull bar. The device is simple in structure and low in manufacturing cost, and can be used for disassembling the piston in the aircraft engine sheath opening actuator cylinder.
Description
Technical field
The present invention relates to the dismantling device of aircraft components, specifically refer to that a kind of aircraft engine foreskin opens the provision for disengagement of the piston in pressurized strut.
Background technology
At present, the domestic reference tool for aircraft maintenance all external planemaker provides, but the maintenance program given for OEM, and the problem run in actual production does not have foundation that can reference.For example, the piston dismounting Knock-Down Component servicing manual that the aircraft engine foreskin is opened pressurized strut does not just provide the specific purpose tool of appointment.By long-term work, we analyze and sum up and design a set of safe and reliable practicability and effectiveness, and the special purpose device that can not cause damage and injure parts and personnel.
Summary of the invention
The purpose of this invention is to provide a kind of aircraft engine foreskin and open the provision for disengagement of the piston in pressurized strut, this provision for disengagement is simple in structure, cost is low, can complete the dismounting that the aircraft engine foreskin is opened the piston in pressurized strut.
Above-mentioned purpose of the present invention realizes by following technical solution: a kind of aircraft engine foreskin is opened the provision for disengagement of the piston in pressurized strut, it is characterized in that: this provision for disengagement comprises the tooth bar, interior bar, contiguous block, impact block and dead man, the tooth bar is the bar that a pair of structure is identical, each rooted tooth bar forms by the body of rod of semi-cylindrical flange tooth and circular arc, the external diameter of flange tooth is greater than the external diameter of the body of rod, the tooth bar has the arc groove of perforation along its length to the body of rod from the flange tooth, the body of rod of this pair of tooth bar is connected with an end of contiguous block, the arc groove of two rooted tooth bars is the relative shape of opening, leave gap between the relative end face of two rooted tooth bars, described dead man is T shape bar, the head of T shape bar is force side, impact block is sleeved in the bar section of T shape bar, and can move along the length direction of bar section, the other end of contiguous block is connected with the bar section of dead man, described two rooted tooth bars are when inserting the piston hole of piston, there is gap between the external diameter of the formed cylinder of flange tooth of two rooted tooth bars and the aperture of piston hole, described two rooted tooth bars are after the piston hole that inserts piston, interior bar is inserted between described two rooted tooth bars, for clogging the space between two rooted tooth bars, and two rooted tooth bars are strutted, thereby after outwards strutting, bites the flange tooth that makes two rooted tooth bars the inner face of piston, the force side that this provision for disengagement is clashed into dead man by impact block produces the active force of dismantling piston, this active force acts on the inner face of piston after the flange tooth of contiguous block and tooth bar, apply by the inner face to piston the dismounting that active force is realized piston.
In the present invention, described contiguous block has the screwed hole of perforation, and the bar section of described dead man has external screw thread, and described contiguous block is threaded with the bar section of dead man; The body of rod of described a pair of tooth bar also has external screw thread, and this body of rod to the tooth bar is threaded with contiguous block.
In provision for disengagement of the present invention, the tooth bar is a set of, and the flange tooth of two semicircle column types is for biting the large end face of piston, and top screw thread is for being connected with contiguous block, the inner chamber that a set of tooth bar forms, for placing interior bar, makes the tooth bar bite securely piston in conjunction with contiguous block.Interior bar is for filling tooth bar inner chamber, to meet the needs of tooth bar function realization.Dead man is connected with contiguous block, and the power of dismounting piston is provided to the tooth bar in conjunction with impact block.Contiguous block is to connect tooth bar and dead man, and the active force that the conduction impact block produces on dead man is to the tooth bar.Impact block is in order to produce the active force of dismounting piston in conjunction with dead man.
Compared with prior art, the present invention has following remarkable result:
1, the dismounting aircraft engine foreskin that the present invention can be safe and reliable is opened the pressurized strut piston, can not damage parts and injury related personnel.
2, the present invention is convenient and swift, can dismantle fast and effectively the aircraft engine foreskin and open the pressurized strut piston.
3, efficiency of the present invention is high, can realize the one man operation, saves manpower and works consuming time.
The accompanying drawing explanation
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail.
The overall structure figure that Fig. 1 is provision for disengagement of the present invention;
The cutaway view of Fig. 2 provision for disengagement of the present invention;
The structure chart that Fig. 3 is dead man in provision for disengagement of the present invention;
The structure chart that Fig. 4 is contiguous block in provision for disengagement of the present invention;
The structure chart that Fig. 5 is two rooted tooth bars in provision for disengagement of the present invention, show the position relationship of two rooted tooth bars;
The structure chart that Fig. 6 is provision for disengagement dens in dente bar of the present invention;
Enlarged drawing is looked on the left side that Fig. 7 is Fig. 6;
The structure chart that Fig. 8 is interior bar in provision for disengagement of the present invention;
The structure chart that Fig. 9 is impact block in provision for disengagement of the present invention.
Description of reference numerals
1, tooth bar; 11, flange tooth; 12, the body of rod; 13, half slot; 2, interior bar;
3, contiguous block; 31, screwed hole; 4, dead man; 41, head; 42, bar section;
5, impact block
The specific embodiment
A kind of aircraft engine foreskin is as shown in Figures 1 to 9 opened the provision for disengagement of the piston in pressurized strut, this provision for disengagement comprises tooth bar 1, interior bar 2, contiguous block 3, impact block 5 and dead man 4, tooth bar 1 is the bar that a pair of structure is identical, each rooted tooth bar 1 forms by the body of rod 12 of semi-cylindrical flange tooth 11 and circular arc, the external diameter of flange tooth 11 is greater than the external diameter of the body of rod 12, the external diameter φ 3 of flange tooth 11 is 19.812mm, the external diameter φ 2 of the body of rod 12 is 19.050mm, tooth bar 1 has the arc groove 13 of perforation along its length to the body of rod 12 from flange tooth 11, the diameter phi 1 of arc groove 13 is 10.160mm, the body of rod 12 of this pair of tooth bar 1 is connected with an end of contiguous block 3, the arc groove 13 of two rooted tooth bars 1 is the relative shape of opening, leave gap delta between the relative end face of two rooted tooth bars 1, this gap delta is 11.176mm, be that the body of rod 12 in the present embodiment and arc groove 13 are the arcuate structure formed after a semi-cylindrical structure excision part, half 5.588mm that the height of cut-out is gap delta numerical value, the body of rod of two rooted tooth bars 1 and arc groove be not half cylindrical structure before excision, after two rooted tooth bar 1 laminatings, the body of rod forms a complete cylinder, arc groove forms a complete cylinder groove, after excision, the body of rod and the arc groove of two rooted tooth bars 1 are arc-shaped structure, leave the gap delta of 11.176mm between the relative end face of two rooted tooth bars 1, but flange tooth 11 is still complete half cylindrical structure, dead man 4 is T shape bar, the head 41 of T shape bar is force side, impact block 5 is sleeved in the bar section 42 of T shape bar, and can move along the length direction of bar section 42, the other end of contiguous block 3 is connected with the bar section 42 of dead man 4, two rooted tooth bars 1 are when inserting the piston hole of piston, there is gap between the external diameter of the flange tooth 11 formed cylinders of two rooted tooth bars 1 and the aperture of piston hole, two rooted tooth bars 1 are after the piston hole that inserts piston, interior bar 2 is inserted between two rooted tooth bars 1, for clogging the space between two rooted tooth bars 1, and two rooted tooth bars 1 are strutted, thereby after outwards strutting, bites the flange tooth 11 that makes two rooted tooth bars 1 inner face of piston, the force side that this provision for disengagement is clashed into dead man 4 by impact block 5 produces the active force of dismantling piston, this active force acts on the inner face of piston after the flange tooth 11 of contiguous block 3 and tooth bar 1, inner face to piston produces an outside pulling force, apply by the inner face to piston the dismounting that active force is realized piston, should interior bar 2 be cylindrical bar, the diameter phi 4 of interior bar 2 is 10.160mm, suitable with the size of arc groove 13, interior bar 2 is inserted into rear both the seamless contacts of arc groove 13, interior bar 2 is also T-shaped bar, the T prefix is installed in the stairstepping draw-in groove of offering tooth bar 1 termination, play the positioning function that clamps of interior bar 2, prevent that interior bar 2 from coming off.
In the present embodiment, contiguous block 3 all adopts screw connection structure with tooth bar 1 and dead man 4, and concrete structure is as follows: contiguous block 3 has the screwed hole 31 of perforation, and the bar section 42 of dead man 4 has external screw thread, and contiguous block 3 is threaded with the bar section 42 of dead man 4; The body of rod 12 of a pair of tooth bar 1 also has external screw thread, and this body of rod to tooth bar 1 12 is threaded with contiguous block 3.
As the conversion of the present embodiment, contiguous block 3 also can adopt the syndetons such as plug-in mounting, buckle with tooth bar 1 and dead man 4, or is connected with connectors such as bolt, rivets.
In the present embodiment, in placing in tooth bar 1, during bar 2, one is matched in clearance to the formed cylinder external diameter of semicolumn flange tooth 11 and piston hole internal diameter size, is convenient to the inner face that tooth bar 1 passes piston hole arrival piston; When interior bar 2 is positioned over the inner chamber that this forms between to tooth bar 1, interior bar 2 struts two rooted tooth bars 1, thereby after outwards strutting, bites the flange tooth 11 that makes two rooted tooth bars 1 inner face of piston, and now, it between the external diameter of tooth bar 1 body of rod 12 and piston hole internal diameter size, is still matched in clearance, only by the flange tooth 11 of tooth bar 1, bite the power of the inner face generation of piston, realize the dismounting of piston under contiguous block 3, impact block 5 and dead man 4 actings in conjunction.
The provision for disengagement operating process of the present embodiment is as follows: at first a pair of tooth bar 1 is put into to the piston hole that the aircraft engine foreskin is opened the pressurized strut piston, and the semicircle column type flange tooth that guarantees the tooth bar is not subject to the restriction of piston hole, want to arrive by piston hole the inner face of piston, then interior bar 2 is put into to the inner chamber formed between the tooth bar, strut the inner face that flange tooth 11 that tooth bar 1 causes the tooth bar can be bitten piston.Hold tooth bar 1, by screw thread, it is connected with contiguous block 3.Impact block 5 is enclosed within on dead man 4.By screw thread, dead man 4 and contiguous block 3 are coupled together.Now, assembly work finishes.While implementing the decomposition dismounting of piston, one holds contiguous block 3, one holds impact block 5, applying suitable power makes impact block 5 slide to clash into the force side of dead man 4 on the body of rod of dead man 4, produce certain pulling force with this, to tooth bar 1, to decompose dismounting aircraft engine foreskin, open the piston in pressurized strut by contiguous block 3 conduction.
The present invention opens the piston in pressurized strut need of production for decomposing dismounting aircraft engine foreskin has brought facility, meet the aircraft engine foreskin and opened pressurized strut when maintenance, the requirement of to decomposing dismounting aircraft engine foreskin, opening the piston in pressurized strut, can realize the one man operation, opening piston in pressurized strut and decompose dismounting important technical support is provided for solving aircraft engine foreskin of the same type, is the important breakthrough of maintenance frock improvement.After the present invention is put into production, it is method for dismounting fast and effectively, has solved because of the long problem that should not dismantle piston of cylindrical shell, also is reduced to manpower, physics that this piston of dismounting need consume simultaneously, has shortened the maintenance cycle of piston.
The above embodiment of the present invention is not limiting the scope of the present invention; embodiments of the present invention are not limited to this; all this kind is according to foregoing of the present invention; ordinary skill knowledge and customary means according to this area; do not breaking away under the above-mentioned basic fundamental thought of the present invention prerequisite; the modification of other various ways that said structure of the present invention is made, replacement or change, within all should dropping on protection scope of the present invention.
Claims (2)
1. an aircraft engine foreskin is opened the provision for disengagement of the piston in pressurized strut, it is characterized in that: this provision for disengagement comprises tooth bar (1), interior bar (2), contiguous block (3), impact block (5) and dead man (4), tooth bar (1) is the bar that a pair of structure is identical, each rooted tooth bar (1) forms by the body of rod (12) of semi-cylindrical flange tooth (11) and circular arc, the external diameter of flange tooth (11) is greater than the external diameter of the body of rod (12), tooth bar (1) has the arc groove (13) of perforation along its length to the body of rod (12) from flange tooth (11), the body of rod (12) of this pair of tooth bar (1) is connected with an end of contiguous block (3), the arc groove (13) of two rooted tooth bars (1) is the relative shape of opening, leave gap between the relative end face of two rooted tooth bars (1), described dead man (4) is T shape bar, the head (41) of T shape bar is force side, impact block (5) is sleeved in the bar section (42) of T shape bar, and can move along the length direction of bar section (42), the other end of contiguous block (3) is connected with the bar section (42) of dead man (4), described two rooted tooth bars (1) are when inserting the piston hole of piston, there is gap between the external diameter of the formed cylinder of flange tooth (11) of two rooted tooth bars (1) and the aperture of piston hole, described two rooted tooth bars (1) are after the piston hole that inserts piston, interior bar (2) is inserted between described two rooted tooth bars (1), for clogging the space between two rooted tooth bars (1), and two rooted tooth bars (1) are strutted, thereby after outwards strutting, bites the flange tooth (11) that makes two rooted tooth bars (1) inner face of piston, the force side that this provision for disengagement is clashed into dead man (4) by impact block (5) produces the active force of dismantling piston, this active force acts on the inner face of piston after the flange tooth (11) of contiguous block (3) and tooth bar (1), apply by the inner face to piston the dismounting that active force is realized piston.
2. aircraft engine foreskin according to claim 1 is opened the provision for disengagement of the piston in pressurized strut, it is characterized in that: described contiguous block (3) has the screwed hole (31) of perforation, the bar section (42) of described dead man (4) has external screw thread, and described contiguous block (3) is threaded with the bar section (42) of dead man (4); The body of rod (12) of described a pair of tooth bar (1) also has external screw thread, and this body of rod to tooth bar (1) (12) is threaded with contiguous block (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310365374.9A CN103465216B (en) | 2013-08-20 | 2013-08-20 | Device for disassembling piston in aircraft engine sheath opening actuator cylinder |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310365374.9A CN103465216B (en) | 2013-08-20 | 2013-08-20 | Device for disassembling piston in aircraft engine sheath opening actuator cylinder |
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| Publication Number | Publication Date |
|---|---|
| CN103465216A true CN103465216A (en) | 2013-12-25 |
| CN103465216B CN103465216B (en) | 2015-06-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310365374.9A Active CN103465216B (en) | 2013-08-20 | 2013-08-20 | Device for disassembling piston in aircraft engine sheath opening actuator cylinder |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516155A (en) * | 2016-11-01 | 2017-03-22 | 广州飞机维修工程有限公司 | Airbus A320 series type rudder position locking method and rudder actuating cylinder lock |
| CN106625381A (en) * | 2016-11-16 | 2017-05-10 | 黄凤章 | Impact sleeve for tire dismounting and repairing |
| CN110497352A (en) * | 2019-07-25 | 2019-11-26 | 内蒙古北方重型汽车股份有限公司 | Electric transmission mine car brake piston maintenance device and its application method |
| CN113500561A (en) * | 2021-06-22 | 2021-10-15 | 沈阳北方飞机维修有限公司 | Front wheel turning actuating cylinder disassembling tool assembly |
-
2013
- 2013-08-20 CN CN201310365374.9A patent/CN103465216B/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516155A (en) * | 2016-11-01 | 2017-03-22 | 广州飞机维修工程有限公司 | Airbus A320 series type rudder position locking method and rudder actuating cylinder lock |
| CN106625381A (en) * | 2016-11-16 | 2017-05-10 | 黄凤章 | Impact sleeve for tire dismounting and repairing |
| CN110497352A (en) * | 2019-07-25 | 2019-11-26 | 内蒙古北方重型汽车股份有限公司 | Electric transmission mine car brake piston maintenance device and its application method |
| CN113500561A (en) * | 2021-06-22 | 2021-10-15 | 沈阳北方飞机维修有限公司 | Front wheel turning actuating cylinder disassembling tool assembly |
| CN113500561B (en) * | 2021-06-22 | 2022-07-26 | 沈阳北方飞机维修有限公司 | Front wheel turning actuating cylinder disassembling tool assembly |
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| Publication number | Publication date |
|---|---|
| CN103465216B (en) | 2015-06-17 |
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