CN207807604U - A kind of aviation accessory parts disassembling fixture integrating stretching and dismounting - Google Patents
A kind of aviation accessory parts disassembling fixture integrating stretching and dismounting Download PDFInfo
- Publication number
- CN207807604U CN207807604U CN201820102306.1U CN201820102306U CN207807604U CN 207807604 U CN207807604 U CN 207807604U CN 201820102306 U CN201820102306 U CN 201820102306U CN 207807604 U CN207807604 U CN 207807604U
- Authority
- CN
- China
- Prior art keywords
- ontology
- top gland
- gland
- turbine
- disassembling fixture
- 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
Links
Landscapes
- Sealing Devices (AREA)
Abstract
The utility model discloses a kind of aviation accessory parts disassembling fixtures integrating stretching and dismounting for belonging to maintenance tool range.The parts disassembling fixture is mainly made of ontology, bottom end end cap and top gland, and top gland is connected by standard screws with ontology；Rod head is carried out top gland, turbine, swivel head and bottom end end cap by bottom end bolt coaxially connected；Rod head lower end is connect with pull rod screw, and upper end is stuck in gland housing upper face, and pull rod, which is just pulled upwardly, to be stretched.There is the swivel head that turbine and gear on worm cooperation rotation are connect with nut between ontology and upper end gland loosening the nut on pull rod, thus may be implemented to stretch pull rod and loosening two functions of nut on pull rod.The utility model pull rod is not rotated and is stretched vertically upward, avoids unbalance stress, and caused workpiece deflection and weak part deform, ensure the aviation accessory being disassembled will not secondary injury, this disassembling fixture is simple in structure, easy to operate, and accommodation is extensive.
Description
Technical field
The utility model belongs to maintenance tool range, more particularly to a kind of aviation accessory zero integrating stretching and dismounting
Component disassembling fixture.
Background technology
It is conventional to use mutual disassembly or the electronic dismounting mode of machinery when aviation accessory repairs, and use lever principle
Workpiece is dismantled, unbalance stress is easily caused, causes workpiece deflection, the weak part of workpiece is made to deform, it may be to work
Part causes secondary destruction；Due to the difference of each aircraft components, in addition manufacture cost of parts cost is high；Some aviation accessories simultaneously
On part not specification, therefore need specific matching specific purpose tool and it decomposed or is assembled, therefore, it is necessary to set
A kind of aerospace parts disassembling fixture for integrating and stretching with disassembling function is counted out, to overcome the shortcomings of existing disassembling fixture.
Utility model content
The purpose of this utility model be for above-mentioned existing disassembling fixture deficiency propose it is a kind of collect stretching and dismounting in one
The aviation accessory parts disassembling fixture of body；It is characterized in that, the aviation accessory parts disassembling fixture mainly by ontology 1,
Bottom end end cap 2 and top gland 3 form, and top gland 3 is connected by standard screws 14 with ontology 1；Ontology 1 and top gland
It is supportted by cushion block 7 among 3；Rod head 4 is waited for after passing through washer 13, top gland 3, turbine 5 and swivel head 6 by bottom end
Demounting bolt 17 carries out top gland 3, turbine 5, swivel head 6 and bottom end end cap 2 coaxially connected；First sealing ring 15 and second
Sealing ring 16 forms sealing surface, sealed bottom oil pressure chamber between ontology 1 and bottom end end cap 2；8 one end of oil pump joint is on top
The end face of 3 inner cavity of gland and ontology 1 is simultaneously sealed by copper gasket 12 and is fixed, be parallel to rod head 4 stretch out top gland 3 and
Sealing is fixed；8 other end of oil pump joint provides hydraulic pressure with oil pump piping connection；
The turbine 5 and swivel head 6 connect, and turbine 5 coordinates with worm screw 9, by solid under worm screw upper fixed seat 11 and worm screw
10 state of reservation determines onto ontology 1；
The washer 13 is the pressure buffer part between rod head 4 and top gland 3.
First sealing ring, 15 and second sealing ring 16 is O-ring seal.
The utility model advantageous effect is that pull rod is not rotated and stretched vertically upward, avoids unbalance stress, caused workpiece
Deflection makes the weak part of workpiece deform, ensure the aviation accessory being disassembled will not secondary injury, and at the same time realize two
Kind function saves manpower.This disassembling fixture is simple in structure, easy to operate, and accommodation is extensive.
Description of the drawings
Fig. 1 is disassembling fixture structural upright schematic diagram.
Fig. 2 is the A-A sectional views of Fig. 1.
Fig. 3 is the B-B sectional views of Fig. 1.
Specific implementation mode
The utility model proposes it is a kind of integrate stretching and dismounting aviation accessory parts disassembling fixture, with reference to
Attached drawing is explained.
Fig. 1 is disassembling fixture structural upright schematic diagram.Aviation accessory parts disassembling fixture as shown in the figure is mainly by ontology
1, bottom end end cap 2 and top gland 3 form, and top gland 3 is connected by standard screws 14 with ontology 1；Ontology 1 and top pressure
It is supportted by cushion block 7 among lid 3；Rod head 4 passes through bottom end after passing through washer 13, top gland 3, turbine 5 and swivel head 6
Bolt 17 to be removed carries out top gland 3, turbine 5, swivel head 6 and bottom end end cap 2 coaxially connected；O-shaped first sealing ring 15
And second sealing ring 16 sealing surface, sealed bottom oil pressure chamber are formed between ontology 1 and bottom end end cap 2；8 one end of oil pump joint
On top, the end face of 3 inner cavity of gland and ontology 1 and being sealed by copper gasket 12 is fixed, and washer 13 is on rod head 4 and top
Become pressure buffer part between gland 3；Oil pump joint 8 is parallel to rod head 4 and stretches out top gland 3, and seals fixed (as schemed
Shown in 2)；8 other end of oil pump joint provides hydraulic pressure with oil pump piping connection；Turbine 5 and swivel head 6 connect, turbine 5 with
Worm screw 9 coordinates, and worm screw 9 is fixed to (as shown in Figure 3) on ontology 1 by worm screw upper fixed seat 11 and 10 state of worm screw lower fixed seat.It draws
Knock-off joint 4 is used for being threadedly coupled with the bolt to be removed 17 of bottom end；Tensile part is stretched, coordinates with bottom end end cap 2
6 Center of swivel head is can be with the screw thread that needs tensile part (bolt 17 to be removed) to coordinate, and turbine 5 and worm screw 9 coordinate
And coordinates with swivel head 6, rotate bolt 17 to be unloaded, so that bolt 17 to be removed is exited bottom end end cap 2 and be removed；It is this dismounting
Tooling is to be connected to oil pump joint 8 by fluid pressure line to provide hydraulic pressure, hydraulic chamber's supercharging, and ontology 1 drives top gland
3, rod head 4 and washer 13 move upwardly together.Since rod head 4 is threadedly coupled with tensile part, therefore tensile part quilt
It stretches.After component to be tensioned is stretched to regulation drawing force, turbine 5 and swivel head 6 is driven to reach to dismounting by rotary worm 9
The disassembling function of the dismounting component of component.Wherein tooling shape keeps pull rod whole using cylinder to reduce compressive load per unit area
Stress is slowly uniform.Pull rod is not rotated and is stretched vertically upward, and unbalance stress, caused dismounting component deflection is avoided to make dismounting
The weak part of component deforms, ensure the aviation accessory being disassembled will not secondary injury, this disassembling fixture is simple in structure, hold
Easy to operate, accommodation is extensive.
Claims (3)
1. a kind of aviation accessory parts disassembling fixture integrating stretching and dismounting；It is characterized in that, the aviation accessory
Parts disassembling fixture is mainly made of ontology (1), bottom end end cap (2) and top gland (3), and top gland (3) passes through standard
Screw (14) is connected with ontology (1)；It is supportted by cushion block (7) among ontology (1) and top gland (3)；Rod head (4) is worn
It crosses top gland (3), turbine after washer (13), top gland (3), turbine (5) and swivel head (6) through bottom end bolt (17)
(5), swivel head (6) and bottom end end cap (2) carry out coaxially connected；First sealing ring (15) and the second sealing ring (16) are in ontology
(1) sealing surface, sealed bottom oil pressure chamber are formed between bottom end end cap (2)；Oil pump joint (8) one end is in top gland (3)
Inner cavity and the end face of ontology (1) simultaneously seal fixation by copper gasket (12), are parallel to rod head (4) and stretch out top gland
(3) and sealing is fixed；Oil pump joint (8) other end provides hydraulic pressure with oil pump piping connection；
The turbine (5) and swivel head (6) connection, turbine (5) coordinate with worm screw (9), and worm screw (9) passes through worm screw upper fixed seat
(11) determine onto ontology (1) with worm screw lower fixed seat (10) state.
2. a kind of aviation accessory parts disassembling fixture integrating stretching and dismounting according to claim 1；Its feature
It is, the washer (13) is the pressure buffer part between rod head (4) and top gland (3).
3. a kind of aviation accessory parts disassembling fixture integrating stretching and dismounting according to claim 1；Its feature
It is, first sealing ring (15) and the second sealing ring (16) are O-ring seal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820102306.1U CN207807604U (en) | 2018-01-22 | 2018-01-22 | A kind of aviation accessory parts disassembling fixture integrating stretching and dismounting |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820102306.1U CN207807604U (en) | 2018-01-22 | 2018-01-22 | A kind of aviation accessory parts disassembling fixture integrating stretching and dismounting |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207807604U true CN207807604U (en) | 2018-09-04 |
Family
ID=63324285
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820102306.1U Active CN207807604U (en) | 2018-01-22 | 2018-01-22 | A kind of aviation accessory parts disassembling fixture integrating stretching and dismounting |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207807604U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112621661A (en) * | 2020-12-08 | 2021-04-09 | 中国人民解放军第五七一九工厂 | Decomposition method for lower end bearing of main oil regulating pump of aircraft engine |
-
2018
- 2018-01-22 CN CN201820102306.1U patent/CN207807604U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112621661A (en) * | 2020-12-08 | 2021-04-09 | 中国人民解放军第五七一九工厂 | Decomposition method for lower end bearing of main oil regulating pump of aircraft engine |
| CN112621661B (en) * | 2020-12-08 | 2022-08-26 | 中国人民解放军第五七一九工厂 | Decomposition method for lower end bearing of main oil regulating pump of aircraft engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN207807604U (en) | A kind of aviation accessory parts disassembling fixture integrating stretching and dismounting | |
| CN203348282U (en) | Locking device for large-specification bolt connecting piece | |
| CN203484876U (en) | Impeller main shaft hydraulic removal device and impeller main shaft | |
| CN205840068U (en) | big corner joint | |
| CN108705486B (en) | Intelligent stretcher | |
| CN203401462U (en) | Nut hydraulic dismounting and mounting assembly and nut hydraulic dismounting and mounting device | |
| CN209148432U (en) | A kind of cold spraying metal coating bond strength test device | |
| CN211162789U (en) | Ultrahigh-pressure two-stage stretcher | |
| CN215928082U (en) | High-strength locking double nut capable of being rapidly disassembled | |
| CN115479130A (en) | Stop buffer valve for fracturing gas production wellhead equipment | |
| CN205423358U (en) | Fluid system booster superhigh pressure piston draw bail | |
| CN111745591A (en) | Dismounting device for low-pressure oil filter shell of aircraft engine | |
| CN102434667A (en) | High-pressure test sealing device for fuel pump body local pressure test | |
| CN203756510U (en) | Self-pressurizing piston of water stop rib | |
| CN104551634A (en) | Two-stage high-type bolt stretcher | |
| CN211890665U (en) | Pipeline joint locking or dismounting tool | |
| CN201007689Y (en) | Vibration sealing general arrangement for engine cylinder end leak detection | |
| CN205254857U (en) | Hexagonal spanner | |
| CN2916118Y (en) | High-pressure valve | |
| CN220296988U (en) | Hydraulic bolt stretcher | |
| CN213779479U (en) | Efficient anti-loosening performance testing device applied to threaded fastener | |
| CN217327995U (en) | Bolt fastening device | |
| CN208854124U (en) | A kind of bolt tensioning jack | |
| CN203509531U (en) | Double-stage bolt stretching device | |
| CN208262378U (en) | A kind of air pressure device for loosing knife |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |