CN208020101U - Aircraft kingbolt dismounts tooling - Google Patents
Aircraft kingbolt dismounts tooling Download PDFInfo
- Publication number
- CN208020101U CN208020101U CN201820345100.1U CN201820345100U CN208020101U CN 208020101 U CN208020101 U CN 208020101U CN 201820345100 U CN201820345100 U CN 201820345100U CN 208020101 U CN208020101 U CN 208020101U
- Authority
- CN
- China
- Prior art keywords
- aircraft
- kingbolt
- guide post
- sleeve
- taper hole
- 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.)
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Abstract
The utility model discloses a kind of aircraft kingbolts to dismount tooling, includes guide post for connect with aircraft kingbolt and is sheathed in guide post and is used for the sleeve to guide post or aircraft kingbolt application impact force.The aircraft kingbolt of the utility model dismounts tooling, can facilitate the dismounting of aircraft kingbolt, improves the disassembly efficiency of aircraft kingbolt, and sleeve will not injure aircraft by a crashing object during the motion, is conducive to protect aircraft, operator that can operate more energetically.
Description
Technical field
The utility model belongs to General Aviation technical field of auxiliary equipment, specifically, the utility model is related to one kind to fly
Owner's bolt disassembly tooling.
Background technology
With the graduallying relax control of China's low altitude airspace, the intensive appearance for related policy favourable of opening the navigation or air flight, China's navigation industry goes out
The development for the formula that bursts out is showed.Aircraft general assembly is the technical work that a technical difficulty is big, it is wide to be related to subject, comprehensive integration degree is high,
It decides the final mass, manufacturing cost and period of aircraft, and restricts the huge obstacle of China's aircraft rapid development, and restrict
One big bottleneck of aircraft final assembly technique development is exactly the development of all kinds of toolings.Equally, the repair of general-purpose aircraft is equally sent out by tooling
Open up the influence of lag.
The kingbolt of aircraft is the part for connecting aircraft wing and fuselage, and since the part load is big, status is important,
So dimensions is larger；Since its installing force is larger, and since it is typically mounted in aircraft main landing gear compartment, installation space
Extremely narrow, so operating process cannot use the tools such as iron hammer, this causes certain trouble to the installation of aircraft kingbolt.
Utility model content
The utility model aims to solve at least one of the technical problems existing in the prior art.For this purpose, the utility model carries
Tooling is dismounted for a kind of aircraft kingbolt, it is therefore an objective to facilitate the dismounting of aircraft kingbolt.
To achieve the goals above, the technical solution that the utility model is taken is：Aircraft kingbolt dismounting tooling, including with
In the guide post being connect with aircraft kingbolt and it is sheathed in guide post and is hit for applying to guide post or aircraft kingbolt
The sleeve of power.
The guide post includes sequentially connected ring flange, interconnecting piece and guide post ontology, and the sleeve, which has, allows guide post sheet
The centre bore that body passes through, ring flange are located at the outside of sleeve.
The interconnecting piece is that the busbar of revolving body and interconnecting piece is arc-shaped, and the maximum gauge of interconnecting piece is less than the sleeve
Centre bore diameter.
The ring flange is discoid, and ring flange and the interconnecting piece and guide post ontology are coaxial arrangement, ring flange it is straight
Diameter is more than the diameter of the centre bore of the sleeve.
The centre bore of the sleeve includes the first taper hole section set gradually in an axial direction, circular hole portion and the second taper hole section, and
The miner diameter end of one taper hole section and miner diameter end and the second taper hole section that the second taper hole section is bellmouth and the first taper hole section is opposite cloth
It sets.
The diameter of the bigger diameter end of first taper hole section and the bigger diameter end of second taper hole section is more than the interconnecting piece
Maximum gauge.
The outer surface of the sleeve is equipped with embossing.
The aircraft kingbolt of the utility model dismounts tooling, can facilitate the dismounting of aircraft kingbolt, improves the main spiral shell of aircraft
The disassembly efficiency of bolt, sleeve will not injure aircraft by a crashing object during the motion, be conducive to protect aircraft, operator that can grasp more energetically
Make.
Description of the drawings
This specification includes the following drawings, and shown content is respectively：
Fig. 1 is the structural schematic diagram of the utility model aircraft kingbolt dismounting tooling；
Fig. 2 is enlarged diagram at A in Fig. 1；
Fig. 3 is the structural schematic diagram of guide post；
Fig. 4 is the sectional view of sleeve；
In figure label for：1, guide post；101, ring flange；102, interconnecting piece；103, guide post ontology；2, sleeve；201,
One taper hole section；202, circular hole portion；203, the second taper hole section.
Specific implementation mode
Below against attached drawing, by the description of the embodiment, making to specific embodiment of the present utility model further detailed
Thin explanation, it is therefore an objective to help those skilled in the art to the design of the utility model, technical solution have it is more complete, accurate and
Deep understanding, and contribute to its implementation.
As shown in Figures 1 to 4, the utility model provides a kind of aircraft kingbolt dismounting tooling, including is used for and aircraft
The guide post 1 of kingbolt connection and the set for being sheathed in guide post 1 and be used to apply guide post 1 or aircraft kingbolt impact force
Cylinder 2.
Specifically, as shown in Figure 1, sleeve 2 is both ends open and the cylindrical member of inner hollow, sleeve 2 are sheathed on
In guide post 1, sleeve 2 can be movable along the axial direction relative to guide post 1, and aircraft kingbolt is equipped with threaded hole, guide post 1
One end is equipped with the end of external screw thread and guide post 1 for being inserted into the threaded hole on aircraft kingbolt, to realize and the main spiral shell of aircraft
The threaded connection of bolt, easy disassembly.When dismantling aircraft kingbolt, guide post 1 is inserted into the threaded hole on aircraft kingbolt, so
After grasp sleeve 2 and be allowed to slidably reciprocate in guide post 1, and sleeve 2 is made to hit guide post 1, sleeve 2 applies guide post 1
The impact force added can push guide post 1 and aircraft kingbolt movable along the axial direction, to realize the dismounting of aircraft kingbolt；
When installing aircraft kingbolt, guide post 1 is inserted into the threaded hole on aircraft kingbolt, is then grasped sleeve 2 and is allowed to
It slidably reciprocates in guide post 1, and sleeve 2 is made to hit aircraft kingbolt, the impact force that sleeve 2 applies aircraft kingbolt can push away
Dynamic aircraft kingbolt is movable along the axial direction, to realize the installation of aircraft kingbolt, finally by guide post 1 from aircraft kingbolt
On disassemble.
As shown in figures 1 and 3, guide post 1 includes sequentially connected ring flange 101, interconnecting piece 102 and guide post ontology 103,
Sleeve 2, which has, allows the centre bore that guide post ontology 103 passes through, and ring flange 101 is located at the outside of sleeve 2, the centre bore of sleeve 2 for
Axially through the through-hole of setting at the center of sleeve 2, ring flange 101 with sleeve 2 for hitting, to receive the production of sleeve 2
Raw impact force.Ring flange 101 is discoid, and guide post ontology 103 is cylinder, ring flange 101 and interconnecting piece 102 and guide post sheet
Body 103 is coaxial arrangement, and the diameter of ring flange 101 is more than the diameter of the centre bore of sleeve 2.The length of guide post ontology 103 is more than
One end of the length of sleeve 2, guide post ontology 103 is fixedly connected with interconnecting piece 102, and the other end of guide post ontology 103 is equipped with outer spiral shell
Line in the threaded hole for insertion into aircraft kingbolt, realizes the threaded connection of guide post 1 and aircraft kingbolt.
Preferably, as shown in Figure 1 to Figure 3, interconnecting piece 102 is between ring flange 101 and guide post ontology 103, even
Socket part 102 is that the busbar of revolving body and interconnecting piece 102 is arc-shaped, and the maximum gauge of interconnecting piece 102 is less than the centre bore of sleeve 2
Diameter.There are one bigger diameter end and a miner diameter end, the diameters of the bigger diameter end of interconnecting piece 102 to be more than miner diameter end for the tool of interconnecting piece 102
Diameter, the bigger diameter end of interconnecting piece 102 is the maximum one end of diameter, and the bigger diameter end of interconnecting piece 102 is fixed with ring flange 101 to be connected
It connects, the miner diameter end of interconnecting piece 102 is fixedly connected with guide post ontology 103, diameter and the guide post ontology of the miner diameter end of interconnecting piece 102
103 diameter is identical.The interconnecting piece 102 of this structure not will produce contact and shock with sleeve 2, and can be to avoid
Stress concentration so that guide post 1 is not in fracture, the problem of preventing from failing when using, improves reliability and operation
Safety.
As shown in Figure 1, Figure 2 and Figure 4, the centre bore of sleeve 2 includes the first taper hole section 201 set gradually in an axial direction, circle
Hole section 202 and the second taper hole section 203, the first taper hole section 201 and the second taper hole section 203 are bellmouth and the first taper hole section 201
Miner diameter end and the miner diameter end of the second taper hole section 203 are positioned opposite.Circular hole portion 202 is the consistent round straight hole of diameter, circle
The length of hole section 202 is more than the length of the first taper hole section 201 and the second taper hole section 203, and the diameter of circular hole portion 202 is not less than guide post
The diameter of ontology 103.First taper hole section 201 has there are one bigger diameter end and a miner diameter end, the bigger diameter end of the first taper hole section 201
Diameter be more than miner diameter end diameter, the second taper hole section 203 also have there are one bigger diameter end and a miner diameter end, the second taper hole section 203
The diameter of bigger diameter end be more than the diameter of miner diameter end, the diameter of the bigger diameter end of the first taper hole section 201 is big with the second taper hole section 203
The diameter at diameter end is identical, and the edge of the miner diameter end of the first taper hole section 201 is connect with an end margin of circular hole portion 202, and second
The edge of the miner diameter end of taper hole section 203 is connect with another end margin of circular hole portion 202, the bigger diameter end of the first taper hole section 201 and
The diameter of the bigger diameter end of two taper hole sections 203 is more than the maximum gauge of interconnecting piece 102, and the diameter of ring flange 101 is more than the first taper hole
The bigger diameter end of the diameter of the bigger diameter end of section 201 and the second taper hole section 203, the first taper hole section 201 and the second taper hole section 203 exists respectively
Opening is formed on one end end face of sleeve 2.The bellmouth being relatively large in diameter is arranged in the both ends of sleeve 2, convenient for guide post 1 insertion with
And the separation of guide post 1 and sleeve 2.
Preferably, as shown in Figure 1 and Figure 4, the outer surface of sleeve 2 is equipped with embossing, to increase between operator's hand
Friction coefficient, prevent caused by skidding operator injured, and the increase of friction coefficient is conducive to operator and operates energetically.
The utility model is exemplarily described above in association with attached drawing.Obviously, the utility model implements not
It is limited by aforesaid way.As long as using the various unsubstantialities of the methodology and technical solution progress of the utility model
Improvement；Or it is not improved, above-mentioned design and technical solution by the utility model directly apply to other occasions, at this
Within the protection domain of utility model.
Claims (5)
1. aircraft kingbolt dismounts tooling, it is characterised in that：Include guide post for being connect with aircraft kingbolt and is sheathed on
Sleeve in guide post and for applying impact force to guide post or aircraft kingbolt；
The guide post includes sequentially connected ring flange, interconnecting piece and guide post ontology, and the sleeve, which has, allows guide post ontology to wear
The centre bore crossed, ring flange are located at the outside of sleeve, and the centre bore of the sleeve includes the first taper hole set gradually in an axial direction
Section, circular hole portion and the second taper hole section, the first taper hole section and the second taper hole section are bellmouth and the miner diameter end of the first taper hole section and the
The miner diameter end of two taper hole sections is positioned opposite.
2. aircraft kingbolt according to claim 1 dismounts tooling, it is characterised in that：The interconnecting piece is revolving body and company
The busbar of socket part is arc-shaped, and the maximum gauge of interconnecting piece is less than the diameter of the centre bore of the sleeve.
3. aircraft kingbolt according to claim 2 dismounts tooling, it is characterised in that：The ring flange is discoid, method
Blue disk is coaxial arrangement with the interconnecting piece and guide post ontology, and the diameter of ring flange is more than the diameter of the centre bore of the sleeve.
4. aircraft kingbolt according to any one of claims 1 to 3 dismounts tooling, it is characterised in that：First taper hole section
Bigger diameter end and second taper hole section bigger diameter end diameter be more than the interconnecting piece maximum gauge.
5. aircraft kingbolt according to claim 4 dismounts tooling, it is characterised in that：The outer surface of the sleeve is equipped with pressure
Flower.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820345100.1U CN208020101U (en) | 2018-03-14 | 2018-03-14 | Aircraft kingbolt dismounts tooling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820345100.1U CN208020101U (en) | 2018-03-14 | 2018-03-14 | Aircraft kingbolt dismounts tooling |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208020101U true CN208020101U (en) | 2018-10-30 |
Family
ID=63907881
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820345100.1U Active CN208020101U (en) | 2018-03-14 | 2018-03-14 | Aircraft kingbolt dismounts tooling |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208020101U (en) |
-
2018
- 2018-03-14 CN CN201820345100.1U patent/CN208020101U/en active Active
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| GR01 | Patent grant | ||
| GR01 | Patent grant |