CN206241960U - A kind of front wing taper bolt dismantling device - Google Patents

A kind of front wing taper bolt dismantling device Download PDF

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Publication number
CN206241960U
CN206241960U CN201621341899.4U CN201621341899U CN206241960U CN 206241960 U CN206241960 U CN 206241960U CN 201621341899 U CN201621341899 U CN 201621341899U CN 206241960 U CN206241960 U CN 206241960U
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CN
China
Prior art keywords
rotary shaft
front wing
taper bolt
handle
sleeve
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.)
Active
Application number
CN201621341899.4U
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Chinese (zh)
Inventor
李晨正
李素博
张庆宇
赵晓涛
贾宏
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Original Assignee
Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
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Application filed by Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC filed Critical Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Priority to CN201621341899.4U priority Critical patent/CN206241960U/en
Application granted granted Critical
Publication of CN206241960U publication Critical patent/CN206241960U/en
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Abstract

The utility model provides a kind of front wing taper bolt dismantling device, for dismantling the front wing taper bolt (6) on aircraft components (5), including rotary shaft (1), handle (2), sleeve (3), rotary shaft (1) is circular bar shape component, rotary shaft (1) one end be provided with for front wing taper bolt (6) in screwed hole be connected thread segment, radially the handle (2) for connecting circular bar shape is run through in direction to rotary shaft (1) other end, sleeve (3) is limited on the required position of rotary shaft (1) especially by clip (4).Front wing taper bolt dismantling device provided by the utility model, is operated by way of screw thread rotation, without applying very big external force, will not damage parts, and can be according to the operation principle popularity application of this instrument.

Description

A kind of front wing taper bolt dismantling device
Technical field
The utility model belongs to aircraft equipment field, and in particular to a kind of front wing taper bolt dismantling device.
Background technology
Aircraft front wing taper bolt is the main force transferring structure that the big axle of front wing is connected with rocking arm, and micro shape is easily produced during flight Become, now dismantle front wing taper bolt, by general tool, connecting bolt simultaneously outwards exerts a force, apply very big power and be also difficult to tear open Unload bolt;During installation, it is also difficult to be installed in place by general tool, the maintenance dismounting work of aircraft front wing is have impact on, also easily Parts are caused to damage.
Utility model content
The purpose of this utility model is to provide a kind of front wing taper bolt dismantling device, overcomes or alleviated by prior art At least one drawbacks described above.
The purpose of this utility model is achieved through the following technical solutions:A kind of front wing taper bolt dismantling device, for tearing open Unload the front wing taper bolt on aircraft components, it is characterised in that including rotary shaft, handle, sleeve, the rotary shaft is circular bar shape Component, the rotary shaft one end be provided with for the front wing taper bolt in screwed hole be connected thread segment, this turn The moving axis other end is socketed in the described thread segment one end in the rotary shaft through the connection handle, the sleeve.
Preferably, the sleeve is limited on the required position of the rotary shaft by clip.
Preferably, the handle is circular bar shape component, and the handle is along the rotary shaft radial direction through this turn of connection Moving axis.
A kind of beneficial effect of front wing taper bolt dismantling device provided by the utility model is, by screw thread rotation Mode operate, without applying very big external force, parts will not be damaged, and can generally be pushed away according to the operation principle of this instrument Wide application.
Brief description of the drawings
Fig. 1 is the structural representation of the utility model front wing taper bolt dismantling device;
Fig. 2 is the scheme of installation of the utility model front wing taper bolt dismantling device.
Reference:
1- rotary shafts, 2- handles, 3- sleeves, 4- clips, 5- aircraft components, 6- front wing taper bolts.
Specific embodiment
For the purpose, technical scheme and advantage for implementing the utility model are clearer, below in conjunction with the utility model Accompanying drawing in embodiment, is further described in more detail to the technical scheme in the utility model embodiment.In the accompanying drawings, ad initio Same or similar element or element with same or like function are represented to same or similar label eventually.Described reality It is a part of embodiment of the invention to apply example, rather than whole embodiments.Embodiment below with reference to Description of Drawings is to show Example property, it is intended to for explaining the utility model, and it is not intended that to limitation of the present utility model.Based in the utility model Embodiment, the every other embodiment that those of ordinary skill in the art are obtained under the premise of creative work is not made, Belong to the scope of the utility model protection.
Front wing taper bolt dismantling device of the present utility model is described in further details below in conjunction with the accompanying drawings.
As shown in figure 1, a kind of front wing taper bolt dismantling device, for dismantling the front wing taper bolt on aircraft components 5 6, including rotary shaft 1, handle 2, sleeve 3, rotary shaft 1 is circular bar shape component, and the one end of rotary shaft 1 is provided with for being bored with front wing The thread segment that screwed hole in shape bolt 6 is connected, the other end of rotary shaft 1 runs through connection handle 2, and the handle 2 selection is Circular bar shape component, and the handle 2 is socketed in rotary shaft 1 along the radial direction of rotary shaft 1 through the rotary shaft 1, the sleeve 3 is connected On thread segment one end, the sleeve 3 is limited on the required position of rotary shaft 1 especially by clip 4.
As shown in Fig. 2 during work, being first connected the screw thread of rotary shaft 1 with the screwed hole of front wing taper bolt 6, handle 2 is rotated, Contacted with the aircraft components 5 on aircraft to sleeve 3, now rotary shaft 1 no longer produces displacement by the spacing of sleeve 3, continue to revolve Handle 2 is changed hands, drives rotary shaft 1 to rotate, rotary shaft 1 makes the front wing taper bolt 6 on aircraft produce displacement by helicitic texture again, So as to remove front wing taper bolt 6;During installation, rotary handle 2 round about.Operated by way of screw thread rotation, Without applying very big external force, parts will not be damaged.
The above, specific embodiment only of the present utility model, but protection domain of the present utility model do not limit to In this, any one skilled in the art in the technical scope that the utility model is disclosed, the change that can be readily occurred in Change or replace, should all cover within protection domain of the present utility model.Therefore, protection domain of the present utility model should be with described Scope of the claims is defined.

Claims (3)

1. a kind of front wing taper bolt dismantling device, for dismantling the front wing taper bolt (6) on aircraft components (5), its feature It is, including rotary shaft (1), handle (2), sleeve (3), the rotary shaft (1) is circular bar shape component, rotary shaft (1) one end Be provided with for the front wing taper bolt (6) in the thread segment that is connected of screwed hole, rotary shaft (1) other end passes through The connection handle (2) is worn, the described thread segment one end in the rotary shaft (1) is socketed in for the spacing sleeve (3), The rotary shaft (1) thread segment is screwed in the screwed hole on the front wing taper bolt (6), the handle (2) to institute is rotated State sleeve (3) to be contacted with the aircraft components (5), the rotary shaft (1) no longer produces position by the spacing of the sleeve (3) Move, continue to rotate the handle (2), drive the rotary shaft (1) to rotate, the rotary shaft (1) makes the front wing by screw thread Taper bolt (6) produces displacement, easy to disassemble.
2. front wing taper bolt dismantling device according to claim 1, it is characterised in that the sleeve (3) is by clip (4) it is limited on the required position of the rotary shaft (1).
3. front wing taper bolt dismantling device according to claim 1, it is characterised in that the handle (2) is circular bar shape Component, the handle (2) is along the rotary shaft (1) radial direction through the connection rotary shaft (1).
CN201621341899.4U 2016-12-08 2016-12-08 A kind of front wing taper bolt dismantling device Active CN206241960U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201621341899.4U CN206241960U (en) 2016-12-08 2016-12-08 A kind of front wing taper bolt dismantling device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201621341899.4U CN206241960U (en) 2016-12-08 2016-12-08 A kind of front wing taper bolt dismantling device

Publications (1)

Publication Number Publication Date
CN206241960U true CN206241960U (en) 2017-06-13

Family

ID=59005423

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201621341899.4U Active CN206241960U (en) 2016-12-08 2016-12-08 A kind of front wing taper bolt dismantling device

Country Status (1)

Country Link
CN (1) CN206241960U (en)

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