CN207482215U - Aircraft engine radome fairing is removed and installation assistor - Google Patents
Aircraft engine radome fairing is removed and installation assistor Download PDFInfo
- Publication number
- CN207482215U CN207482215U CN201721501292.2U CN201721501292U CN207482215U CN 207482215 U CN207482215 U CN 207482215U CN 201721501292 U CN201721501292 U CN 201721501292U CN 207482215 U CN207482215 U CN 207482215U
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- bearing
- slide bar
- radome fairing
- aircraft engine
- screw
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Abstract
A kind of aircraft engine radome fairing is removed and installation assistor, which is characterized in that including：Bearing, slide bar, bulb, slide bar driving mechanism, universal base, upright bar and two force pieces.It is protruding by slide bar driving structure driving slider, it realizes and is in contact at universal base and aircaft configuration, since universal base, so as to match at the aircaft configuration of different angle, can be supported with respect to ball joint-rotating.Later by the fixed torsion pound table of the bearing other end with need remove or install fixing glue connect, rotate entire assistor, so as to facilitate by first order stator blade radome fairing remove or install.Whole process working efficiency is greatly improved, while installation accuracy is also improved, safe and reliable.
Description
Technical field
The utility model is related to aircraft maintenance fields, and in particular to a kind of aircraft engine radome fairing is removed and installation is used and added
Power device.
Background technology
Boeing-737 NG aircraft engines are when removing first order guide vane radome fairing, since the component is chronically at height
The influence of vibrations, high and low temperature alternative and all kinds of etchant gas liquid, the fixing glue of radome fairing are very tight under the action of stress
Gu very big power is needed during dismounting, and since its working region is in engine inlets, first order guide vane radome fairing
The distance between air intake duct very little is unfavorable for having an effect when removing fixing glue, therefore not only very takes when removing fixing glue
Power is also easy to that fixing glue is caused to damage, and great inconvenience is caused to follow-up work.On the other hand in installation first order guide vane
During radome fairing, in order to ensure the aerodynamic characteristic of engine, the fastening grooves of the screw of fixed radome fairing are compared to conventional bolt slightly
More shallow, radome fairing and air intake duct inner wall spacing are small, along with the screw of the position needs certain Tightening moment, are using pound
During table pound screw torque, due to that tool cannot be made closely to interlock with screw well, so as to be easy to cause screw damage, so that
Cannot pound to requirement torque, and remove it is also extremely difficult, if let go unchecked to such case, it is easy to cause engine
Security risk.Also there are many components due to corroding for a long time in other individual events work of aircraft maintenance, damage is either
Lead to not be well on dismounting and installation because of limited space.Such situation not only wastes time, and is also easy to cause surrounding
The damage and pollution of component and working environment, leverage working efficiency and repair quality.
Utility model content
The utility model provides a kind of raising first order stator blade radome fairing and tears open to overcome the shortcomings of more than technology
Except being removed with the aircraft engine radome fairing of installment work efficiency and precision and installation assistor.
Technical solution is used by the utility model overcomes its technical problem：
A kind of aircraft engine radome fairing is removed and installation assistor, which is characterized in that including：
Bearing is equipped with linear bearing on the bearing by screw III；
Slide bar, level are slided and are plugged in linear bearing；
Bulb, tail end are fixed on by the screw rod of setting in the corresponding screw hole in slide bar；
Slide bar driving mechanism, is set on bearing, is slided in the horizontal direction for driving slider；
Universal base is flexibly connected by internal ball groove with bulb；
Upright bar is combined on the tail end of bearing by the end of thread of setting；And
Two force pieces, are respectively arranged in the upper and lower ends of upright bar, and the inner end of the force piece is provided with protrusion, torsion
Pound table folder is exerted a force loaded on two between pieces, and passes through raised clamping and positioning.
Further, above-mentioned slide bar driving mechanism includes the ear mount being set on bearing, flexible handle, is set to slide bar tail
In being provided with hole on the tracking wheel of flexible handle lower end, the flexible handle, screw II is primary for the sliding rail at end and rotational installation
By nut check after across ear mount and hole, the tracking wheel rolling is set in sliding rail, when flexible handle is revolved around screw II
When turning, the radius of gyration of tracking wheel and the bending radius of sliding rail match.
For the ease of operation, the fixation handle being fixed on by screw IV on bearing, the fixed handle and branch are further included
The angle of seat is right angle.
Universal base is fallen in order to prevent, further includes restriction plate, and circular hole is provided in the restriction plate, and the Circularhole diameter is small
In bulb diameter, restriction plate is fixed on the tail end of universal base by screw I, and bulb is clipped between restriction plate and universal base.
In order to play the role of buffer non-skid, the head end of above-mentioned universal base is provided with rubber block.
In order to realize the transformation of length, further include several sections and lengthen loop bar, each lengthening loop bar passes through screw thread between each other
Screw coaxially connected, each lengthening loop bar one end after connection is connect with bearing, the end of thread connection of the other end and upright bar.
In order to realize auxiliary reset, the spring being set on slide bar is further included, one end of the spring is connected with slide bar,
The other end is connected with linear bearing, when the outside Slideslip of slide bar, compression deformation of the spring.
The beneficial effects of the utility model are：In use, it is protruding by slide bar driving structure driving slider, realize ten thousand
It is in contact to seat and aircaft configuration, since universal base can be with respect to ball joint-rotating, so as to match the aircraft of different angle
At structure, it is supported.It is connect later by the fixed torsion pound table of the bearing other end with the fixing glue for needing to remove or install,
Rotate entire assistor, so as to facilitate by first order stator blade radome fairing remove or installation.Whole process working efficiency obtains
To greatly improve, while installation accuracy is also improved, safe and reliable.
Description of the drawings
Fig. 1 is the stereochemical structure explosive view of the utility model；
In figure, 1. rubber block, 2. universal base, 3. screw rod, 4. bulb, 5. restriction plate, 6. screw, I 7. slide bar, 8. sliding rail
9. 12. hole of linear bearing 10. spring, 11. flexible handle, 13. screw, II 14. nut, 15. bearing, 16. ear mount, 17. spiral shell
It follows closely III 18. 19. screws IV 20. of fixation handle and lengthens 21. end of thread of loop bar, 22. force of upright bar 23. piece, 24. protrusion
25. tracking wheel.
Specific embodiment
1 pair of the utility model is described further below in conjunction with the accompanying drawings.
A kind of aircraft engine radome fairing is removed and installation assistor, which is characterized in that including：Bearing 15, bearing 15
It is upper that linear bearing 9 is equipped with by screw III 17；Slide bar 7, level are slided and are plugged in linear bearing 9；Bulb 4, tail end leads to
The screw rod 3 for crossing setting is fixed in the corresponding screw hole in slide bar 7；Slide bar driving mechanism is set on bearing 15, for driving
Slide bar 7 slides in the horizontal direction；Universal base 2 is flexibly connected by internal ball groove with bulb 4；Upright bar 22 passes through setting
The end of thread 21 be combined on the tail end of bearing 15；And two force pieces 23, the upper and lower ends of upright bar 22 are respectively arranged in, are exerted a force
The inner end of piece 23 is provided with protrusion 24, and torsion pound table folder is exerted a force loaded on two between pieces 23, and passes through raised 24 clamping and positionings.
In use, it is protruding by slide bar driving structure driving slider 7, it realizes and is in contact at universal base 2 and aircaft configuration, due to ten thousand
It can rotate relative to bulb 4 to seat 2, so as to match at the aircaft configuration of different angle, be supported.Pass through bearing later
The fixed torsion pound table of 15 other ends with need remove or install fixing glue connect, rotate entire assistor, so as to facilitate by
First order stator blade radome fairing remove or installation.Whole process working efficiency is greatly improved, while installation accuracy
It is improved, it is safe and reliable.
Slide bar driving mechanism can be following structure, including be set on bearing 15 ear mount 16, flexible handle 11, set
The sliding rail 8 and rotational installation for being placed in 7 tail end of slide bar are provided on the tracking wheel 25 of 11 lower end of flexible handle, flexible handle 11
Hole 12, screw II 13 are locked after once passing through ear mount 16 and hole 12 by nut 14, and the rolling of tracking wheel 25 is set in sliding rail 8,
When flexible handle 11 is rotated around screw II 13, the bending radius of the radius of gyration and sliding rail 8 of tracking wheel 25 matches.But
When rotating flexible handle 11, tracking wheel 25 does circular motion, is slided simultaneously along arc-shaped sliding rail 8, so as to be generated to slide bar 7
Outside thrust makes slide bar 7 protruding along linear bearing 9.Preferably, the spring 10 being set on slide bar 7, spring are further included
10 one end is connected with slide bar 7, and the other end is connected with linear bearing 9, and when 7 outside Slideslip of slide bar, the compression of spring 10 becomes
Shape.After use, the 7 inside Slideslip of elastic force driving slider of spring 10, so as to fulfill the auxiliary reset of slide bar 7.Further
Improve the convenience of operation.
It can also include the fixation handle 18 being fixed on by screw IV 19 on bearing 15, fixed handle 18 and bearing 15
Angle be right angle.During operation, operating personnel can hold fixed handle 18, it is facilitated to provide fixed branch in afterburner process
Support, improves convenience during operation.
Restriction plate 5 is further included, circular hole is provided in restriction plate 5, Circularhole diameter is less than 4 diameter of bulb, and restriction plate 5 passes through spiral shell
I 6 tail ends for being fixed on universal base 2 are followed closely, bulb 4 is clipped between restriction plate 5 and universal base 2.Since the diameter of bulb 4 is more than
The Circularhole diameter of restriction plate 5, therefore bulb 4 and universal base 2 can be attached by restriction plate 5, prevent bulb 4 from universal base 2
Ball groove in be detached from.Preferably, the head end of universal base 2 is provided with rubber block 1.By being connect at rubber block 1 and aircaft configuration
It touches, the reliability used can be improved with increasing friction force while realizing compensator or trimmer pressure.
It further includes several sections and lengthens loop bar 20, each lengthening loop bar 20 is coaxially connected by threaded engagement between each other, even
Each 20 one end of lengthening loop bar after connecing is connect with bearing 15, and the other end is connect with the end of thread 21 of upright bar 22.Pass through setting
Length variation and the conversion of linkage function can be provided for entire assistor tooling by lengthening loop bar 20, so as to improve not same district
Suitability when domain uses.
Claims (7)
1. a kind of aircraft engine radome fairing is removed and installation assistor, which is characterized in that including：
Bearing（15）, the bearing（15）It is upper to pass through screw III（17）Linear bearing is installed（9）；
Slide bar（7）, level slide be plugged in linear bearing（9）In；
Bulb（4）, screw rod that tail end passes through setting（3）It is fixed on slide bar（7）In interior corresponding screw hole；
Slide bar driving mechanism, is set to bearing（15）On, for driving slider（7）It slides in the horizontal direction；
Universal base（2）, pass through internal ball groove and bulb（4）Flexible connection；
Upright bar（22）, pass through the end of thread of setting（21）It is combined on bearing（15）Tail end；And
Two force pieces（23）, it is respectively arranged in upright bar（22）Upper and lower ends, the force piece（23）Inner end be provided with
Protrusion（24）, torsion pound table folder is loaded on two force pieces（23）Between, and pass through protrusion（24）Clamping and positioning.
2. aircraft engine radome fairing according to claim 1 is removed and installation assistor, it is characterised in that：The cunning
Bar driving mechanism includes being set to bearing（15）On ear mount（16）, flexible handle（11）, be set to slide bar（7）The sliding rail of tail end
（8）And rotational installation is in flexible handle（11）The tracking wheel of lower end（25）, the flexible handle（11）On be provided with hole（12）,
Screw II（13）Once pass through ear mount（16）And hole（12）After pass through nut（14）Locking, the tracking wheel（25）Rolling is set to
Sliding rail（8）In, work as flexible handle（11）Around screw II（13）During rotation, tracking wheel（25）The radius of gyration and sliding rail（8）'s
Bending radius matches.
3. aircraft engine radome fairing according to claim 1 is removed and installation assistor, it is characterised in that：It further includes
Pass through screw IV（19）It is fixed on bearing（15）On fixation handle（18）, the fixed handle（18）With bearing（15）Angle
For right angle.
4. aircraft engine radome fairing according to claim 1 is removed and installation assistor, it is characterised in that：It further includes
Restriction plate（5）, the restriction plate（5）On be provided with circular hole, the Circularhole diameter is less than bulb（4）Diameter, restriction plate（5）Pass through
Screw I（6）It is fixed on universal base（2）Tail end, bulb（4）It is clipped on restriction plate（5）With universal base（2）Between.
5. aircraft engine radome fairing according to claim 1 is removed and installation assistor, it is characterised in that：Described ten thousand
To seat（2）Head end be provided with rubber block（1）.
6. aircraft engine radome fairing as claimed in any of claims 1 to 5 is removed and installation assistor, special
Sign is：It further includes several sections and lengthens loop bar（20）, each lengthening loop bar（20）It is coaxially connected by threaded engagement between each other,
Each lengthening loop bar after connection（20）One end and bearing（15）Connection, the other end and upright bar（22）The end of thread（21）Even
It connects.
7. aircraft engine radome fairing according to claim 2 is removed and installation assistor, it is characterised in that：It further includes
It is set in slide bar（7）On spring（10）, the spring（10）One end and slide bar（7）It is connected, the other end and linear bearing
（9）It is connected, works as slide bar（7）During outside Slideslip, spring（10）Compressive deformation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721501292.2U CN207482215U (en) | 2017-11-13 | 2017-11-13 | Aircraft engine radome fairing is removed and installation assistor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721501292.2U CN207482215U (en) | 2017-11-13 | 2017-11-13 | Aircraft engine radome fairing is removed and installation assistor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207482215U true CN207482215U (en) | 2018-06-12 |
Family
ID=62476677
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721501292.2U Active CN207482215U (en) | 2017-11-13 | 2017-11-13 | Aircraft engine radome fairing is removed and installation assistor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207482215U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107738759A (en) * | 2017-11-13 | 2018-02-27 | 山东太古飞机工程有限公司 | Aircraft engine radome fairing is removed and installation assistor |
-
2017
- 2017-11-13 CN CN201721501292.2U patent/CN207482215U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107738759A (en) * | 2017-11-13 | 2018-02-27 | 山东太古飞机工程有限公司 | Aircraft engine radome fairing is removed and installation assistor |
| CN107738759B (en) * | 2017-11-13 | 2023-12-01 | 山东太古飞机工程有限公司 | Booster for dismounting and mounting aircraft engine fairing |
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| GR01 | Patent grant |