CN208468266U - A kind of screw strength provision for disengagement - Google Patents
A kind of screw strength provision for disengagement Download PDFInfo
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- CN208468266U CN208468266U CN201820766829.6U CN201820766829U CN208468266U CN 208468266 U CN208468266 U CN 208468266U CN 201820766829 U CN201820766829 U CN 201820766829U CN 208468266 U CN208468266 U CN 208468266U
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- screw
- supporter
- disassembly
- support plate
- lever construction
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Abstract
A kind of screw strength provision for disengagement, it includes screw in compression mechanism and disassembly executing agency；The screw in compression mechanism uses lever construction, is equipped with supporter and support plate, and the supporter lower end is groove to be arranged on supporter top, the support plate is inserted into groove, and passes through pin and supporter hinge mounted with externally threaded cylindrical body；The fulcrum of lever construction is made of pin, support plate one end is the master arm of lever construction, and the other end is the slave arm of lever construction；Described master arm one end is equipped with force section, and swivel nut is arranged in force section, loading screw is matched in swivel nut, the screw rod lower end is equipped with pedestal in hinged way, and the pedestal is placed on the horizontal plane of aircraft body；Described slave arm one end is equipped with compressed part, and the compressed part and disassembly executing agency are equipped.Screw disassembling is difficult during the utility model solves the problems, such as aircraft maintenance, has achieved the purpose that reduce aircraft maintenance cost, has avoided causing aircraft body damage.
Description
Technical field
The utility model relates to a kind of screw strength provisions for disengagement, belong to hand-operated tools technical field.
Background technique
There are a large amount of screw connecting elements on aircraft, flown for a long time by aircraft and it is outdoor park the period and influenced,
Screw connecting elements will appear corrosion solidification phenomenon, therefore during aircraft maintenance, the disassembly of screw member is extremely difficult,
The method that can only be removed by destructiveness, scraps processing for screw, thus not only maintenance cost is increased, while there is also right
Aircraft body causes the potential risk of damage.
Utility model content
The utility model provides a kind of screw strength provision for disengagement, it is intended to which screw member is torn open during solving aircraft maintenance
Difficult problem is unloaded, achievees the purpose that reduce aircraft maintenance cost, avoid causing aircraft body damage.
To achieve the above objectives, the present invention adopts the following technical solutions:
A kind of screw strength provision for disengagement, including screw in compression mechanism and disassembly executing agency；The screw in compression mechanism
Using lever construction, it is equipped with supporter and support plate, the supporter lower end is with externally threaded cylindrical body, for that will support
Body screws on aircraft body in original screw hole, and the groove parallel with center axis thereof is arranged on supporter top, described
Support plate is inserted into groove, and passes through pin and supporter hinge mounted；The fulcrum of lever construction, support plate one are made of pin
End is the master arm of lever construction, and the other end is the slave arm of lever construction；Described master arm one end is equipped with force section, is exerting a force
Swivel nut is arranged in portion, matches loading screw in the swivel nut, and swivel nut and screw rod form screw nut driven unit, the screw rod lower end with
Articulated manner is equipped with pedestal, and the pedestal is placed on the horizontal plane of aircraft body；Described slave arm one end is equipped with compressed part, institute
It states compressed part and disassembly executing agency is equipped.
Above-mentioned screw strength provision for disengagement, the compressed part are tube-in-tube structure；The sleeve is welded in support plate slave arm
One end, the limiting groove that end setting is axially positioned for dismantling executing agency under a bushing.
Above-mentioned screw strength provision for disengagement, the disassembly executing agency include operation handle, rotary body, core retainer plate and disassembly knife
Head；The operation handle is mounted on rotary body upper end；The rotary body is sleeved in core retainer plate, in the middle part of rotary body be equipped with wait tear open
The consistent external screw thread of screw screw pitch is unloaded, in rotary body lower end installing and dismounting cutter head；The core retainer plate is inlaid in screw in compression mechanism
Sleeve inner is equipped with positive stop lug boss in core retainer plate lower end, and the positive stop lug boss and the limiting groove of sleeve lower end match, and core retainer plate is set
There is the internal screw thread with rotation extracorporeal thread cooperation.
Above-mentioned screw strength provision for disengagement, the disassembly cutter head are filled by the hexagonal structure and rotary body for being disposed thereon end
Match.
Above-mentioned screw strength provision for disengagement, the support plate are equipped with the horizontal elongated slot of matching pin.
The force section of above-mentioned screw strength provision for disengagement, described screw in compression mechanism master arm one end is additionally provided with gasket, institute
Gasket is stated to be placed between pedestal and aircraft body horizontal plane.
The utility model is a kind of screw strength provision for disengagement, it passes through original screw hole on supporter and aircraft body
Cooperation, and screw in compression mechanism is designed as lever construction, which is branch with supporter and the hinged pin of support plate
Point, lever construction master arm one end and aircraft body upper horizontal plane cooperate, then pass through the screw nut driven unit of force section
Upward thrust is provided, lever construction converts this thrust to the axial pressure for being mounted on the disassembly executing agency of slave arm one end
Power, then rotary body is rotated counterclockwise by operation handle in disassembly executing agency, screw is unscrewed by disassembly cutter head, due to can
Lever construction slave arm one end height is adjusted by screw nut driven unit, so that support plate is in horizontality, ensure that and apply
The pressure being added on screw to be removed is consistent with center axis thereof, while the positive stop lug boss of core retainer plate and outer in disassembly executing agency
The limiting groove cooperation of sleeve realizes the axially position of core retainer plate, and core retainer plate and rotary body thread matching structure and spiral shell to be removed
The thread pitch of nail is consistent, thus avoids screw itself and damage to aircraft body upper bolt aperture in disassembly process；
The utility model also on the supporting plate be provided with matching pin horizontal elongated slot, therefore can be used on aircraft with intrinsic screw hole
The screw disassembling of different distance has stronger universal performance；The utility model is also arranged in the force section of screw in compression mechanism
Gasket, avoids the damage to aircraft body.In conclusion the utility model solves screw during aircraft maintenance
The problem of component removal difficulty has achieved the purpose that reduce aircraft maintenance cost, has avoided causing aircraft body damage.
Detailed description of the invention
Fig. 1 is the utility model composed structure schematic diagram；
Fig. 2 is the utility model section structural schematic diagram；
Fig. 3 is supporting body structure schematic diagram；
Fig. 4 is supporting plate structure schematic diagram；
Fig. 5 is disassembly executing agency's schematic diagram；
Fig. 6 is utility model works status diagram.
Each list of reference numerals in figure are as follows: 1, pedestal, 2, screw rod, 3, support plate, 3-1, swivel nut, 3-2, horizontal elongated slot, 3-3, set
4-1, cylinder, 3-4, limiting groove, 4, supporter have externally threaded cylindrical body, 4-2, groove, 4-3, pin, 5, disassembly execution
Mechanism, 5-1, operation handle, 5-2, rotary body, 5-3, core retainer plate, 5-4, disassembly cutter head, 5-5, positive stop lug boss, 6, gasket, 7, flight
Device body, 8, screw to be removed, 9, original screw hole on aircraft body.
Specific embodiment
With reference to the accompanying drawing and specific embodiment the utility model is described in further detail.
Referring to Fig. 1, Fig. 2, Fig. 3, Fig. 4, Fig. 6, the utility model is a kind of screw strength provision for disengagement, is suitable for aircraft
The disassembly of screw connecting structure when overhaul, due to, wait tear the components such as more ribs and mouth frame around screw open, passing through routine on aircraft
Strut press, can not reliably put forth effort, screw pressure is arranged by screw hole 9 original on aircraft body in the utility model
Tight mechanism and disassembly executing agency 5；The screw in compression mechanism uses lever construction, is equipped with supporter 4 and support plate 3, described
4 lower end of supporter is with externally threaded cylindrical body 4-1, for supporter 4 to be screwed in original screw hole 9 on aircraft body
In, the groove 4-2 parallel with center axis thereof is set on 4 top of supporter, and the support plate 3 is inserted into groove 4-2, and is passed through
Pin 4-3 and 4 hinge mounted of supporter are equipped with the horizontal elongated slot 3-2 of matching pin 4-3 in support plate 3；By pin 4-3 structure
At the fulcrum of lever construction, 3 one end of support plate is the master arm of lever construction, and the other end is the slave arm of lever construction；It is described
Master arm one end is equipped with force section, and swivel nut 3-1 is arranged in force section, loading screw 2, swivel nut 3-1 and spiral shell are matched in the swivel nut 3-1
Bar 2 forms screw nut driven unit, and 2 lower end of screw rod is equipped with pedestal 1 in hinged way, and the pedestal 1 is placed in aircraft
On the horizontal plane of body 7；Described slave arm one end is equipped with compressed part, and the compressed part and disassembly executing agency 5 are equipped.
Referring to Fig. 1, Fig. 2, Fig. 4, screw strength provision for disengagement described in the utility model, the compressed part is sleeve 3-3 knot
Structure；The sleeve 3-3 is welded in 3 slave arm one end of support plate, and in the lower end sleeve 3-3, setting is axially fixed for dismantling executing agency
The limiting groove 3-4 of position.
Referring to Fig. 1, Fig. 2, Fig. 5, screw strength provision for disengagement described in the utility model, the disassembly executing agency 5 includes
Operation handle 5-1, rotary body 5-2, core retainer plate 5-3 and disassembly cutter head 5-4；The operation handle 5-1 is mounted on rotary body 5-2
End；The rotary body 5-2 is sleeved in core retainer plate 5-3, is equipped in the middle part of rotary body 5-2 consistent with 8 thread pitch of screw to be removed
External screw thread, the lower end rotary body 5-2 pass through interior hexagonal structure installing and dismounting cutter head 5-4；The core retainer plate 5-3 is inlaid in screw pressure
Inside the sleeve 3-3 of tight mechanism, in the case where the lower end core retainer plate 5-3 is equipped with positive stop lug boss 5-5, the positive stop lug boss 5-5 and sleeve 3-3
The limiting groove 3-4 at end matches, and core retainer plate 5-3 is additionally provided with the internal screw thread with the cooperation of rotary body 5-2 external screw thread.
Referring to Fig. 1, Fig. 2, Fig. 6, screw strength provision for disengagement described in the utility model, the force of the screw in compression mechanism
Portion is additionally provided with gasket 6, and the gasket 6 is placed between pedestal 1 and the horizontal plane of aircraft body 7.
Referring to Fig. 1 to Fig. 6, the utility model has outer spiral shell when carrying out the disassembly of aircraft screwing, by 4 bottom of supporter
On the cylindrical body 4-1 screw-in aircraft body of line in original screw hole 9, pass through the screw nut driven list of lever construction force section
Member provides upward thrust, and lever construction converts this thrust to the axial direction for being mounted on the disassembly executing agency 5 of slave arm one end
Pressure, then rotary body 5-2 is rotated counterclockwise by operation handle 5-1 in disassembly executing agency 5, by disassembly cutter head 5-4 by spiral shell
Nail unscrews, and adjusts lever construction slave arm one end height due to that can pass through screw nut driven unit, support plate 3 is made to be in level
State ensure that the pressure being applied on screw 8 to be removed is consistent with center axis thereof, while in disassembly 5 core of executing agency
The limiting groove 3-4 cooperation for covering the positive stop lug boss 5-5 and sleeve 3-3 of 5-3 realizes the axially position of core retainer plate 5-3, and core retainer plate
5-3 is consistent with the screw pitch of screw 8 to be removed with rotary body 5-2 thread matching structure, thus avoids screw in disassembly process
Itself and the damage to aircraft body upper bolt aperture.
Claims (6)
1. a kind of screw strength provision for disengagement, characterized in that it includes screw in compression mechanism and disassembly executing agency (5)；It is described
Screw in compression mechanism uses lever construction, is equipped with supporter (4) and support plate (3), and supporter (4) lower end is with outer spiral shell
The cylindrical body (4-1) of line, for screwing in supporter (4) on aircraft body in original screw hole (9), in supporter (4)
The groove (4-2) parallel with center axis thereof is arranged in top, and the support plate (3) is inserted into groove (4-2), and passes through pin
(4-3) and supporter (4) hinge mounted；The fulcrum of lever construction is made of pin (4-3), support plate (3) one end is lever knot
The master arm of structure, the other end are the slave arm of lever construction；Described master arm one end is equipped with force section, and swivel nut is arranged in force section
(3-1) matches loading screw (2) in the swivel nut (3-1), and swivel nut (3-1) and screw rod (2) form screw nut driven unit, institute
It states screw rod (2) lower end and is equipped with pedestal (1) in hinged way, the pedestal (1) is placed on the horizontal plane of aircraft body (7)；Institute
Slave arm one end is stated equipped with compressed part, the compressed part and disassembly executing agency (5) are equipped.
2. screw strength provision for disengagement according to claim 1, characterized in that the compressed part is sleeve (3-3) structure；
The sleeve (3-3) is welded in support plate (3) slave arm one end, is arranged in the sleeve lower end (3-3) for dismantling actuator shaft
To the limiting groove (3-4) of positioning.
3. screw strength provision for disengagement according to claim 2, characterized in that the disassembly executing agency (5) includes behaviour
Make handle (5-1), rotary body (5-2), core retainer plate (5-3) and disassembly cutter head (5-4)；The operation handle (5-1) is mounted on rotation
The upper end body (5-2)；The rotary body (5-2) is sleeved in core retainer plate (5-3), is equipped with and spiral shell to be removed in the middle part of rotary body (5-2)
The consistent external screw thread of (8) screw pitch is followed closely, in rotary body (5-2) lower end installing and dismounting cutter head (5-4)；The core retainer plate (5-3) is inlaid in
The sleeve (3-3) of screw in compression mechanism is internal, is equipped with positive stop lug boss (5-5) in the core retainer plate lower end (5-3), the positive stop lug boss (5-
5) limiting groove (3-4) with the lower end sleeve (3-3) matches, and core retainer plate (5-3) is additionally provided with to be cooperated with rotary body (5-2) external screw thread
Internal screw thread.
4. screw strength provision for disengagement according to claim 3, characterized in that the disassembly cutter head (5-4) passes through setting
The hexagonal structure and rotary body (5-2) held on it assemble.
5. screw strength provision for disengagement according to any one of claim 1 to 4, characterized in that the support plate (3) is also
Horizontal elongated slot (3-2) equipped with matching pin (4-3).
6. screw strength provision for disengagement according to claim 5, characterized in that the force section of the screw in compression mechanism is also
Equipped with gasket (6), the gasket (6) is placed between pedestal (1) and aircraft body horizontal plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820766829.6U CN208468266U (en) | 2018-05-22 | 2018-05-22 | A kind of screw strength provision for disengagement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820766829.6U CN208468266U (en) | 2018-05-22 | 2018-05-22 | A kind of screw strength provision for disengagement |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208468266U true CN208468266U (en) | 2019-02-05 |
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ID=65218398
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820766829.6U Active CN208468266U (en) | 2018-05-22 | 2018-05-22 | A kind of screw strength provision for disengagement |
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| CN (1) | CN208468266U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111730532A (en) * | 2020-06-12 | 2020-10-02 | 陕西飞机工业（集团）有限公司 | Lever type screw disassembling tool |
-
2018
- 2018-05-22 CN CN201820766829.6U patent/CN208468266U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111730532A (en) * | 2020-06-12 | 2020-10-02 | 陕西飞机工业（集团）有限公司 | Lever type screw disassembling tool |
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