CN108528756A - A kind of aircraft engine parks bracket - Google Patents
A kind of aircraft engine parks bracket Download PDFInfo
- Publication number
- CN108528756A CN108528756A CN201711351475.5A CN201711351475A CN108528756A CN 108528756 A CN108528756 A CN 108528756A CN 201711351475 A CN201711351475 A CN 201711351475A CN 108528756 A CN108528756 A CN 108528756A
- Authority
- CN
- China
- Prior art keywords
- bracket
- fuselage
- support bar
- fixing device
- aircraft engine
- 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.)
- Pending
Links
- 210000000452 mid-foot Anatomy 0.000 claims abstract description 9
- 230000003139 buffering effect Effects 0.000 claims description 10
- 230000007246 mechanism Effects 0.000 claims description 9
- 238000013016 damping Methods 0.000 description 4
- 238000012423 maintenance Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25H—WORKSHOP EQUIPMENT, e.g. FOR MARKING-OUT WORK; STORAGE MEANS FOR WORKSHOPS
- B25H5/00—Tool, instrument or work supports or storage means used in association with vehicles; Workers' supports, e.g. mechanics' creepers
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Arrangement Or Mounting Of Propulsion Units For Vehicles (AREA)
Abstract
The present invention relates to a kind of aircraft engines to park bracket, it includes holder, be arranged holder front end output shaft tray, be arranged on output shaft tray output shaft fixing device, fuselage bracket and the fuselage fixing device that is arranged on fuselage bracket in back-end support are set, the fuselage bracket includes side support bar and the midfoot support bar that is arranged in the middle part of two side support bars being arranged in back-end support both sides, is rolled in the side support bar and midfoot support bar and is provided with pulley；The present invention in rack by being provided with output shaft fixing device and fuselage fixing device, it can be connected respectively with corresponding fixing device after aircraft engine removes, allow engine is highly stable to be placed in rack, realize properly place, effectively avoid because park it is improper caused by damage.
Description
Technical field
The present invention relates to a kind of aircraft engines to park bracket.
Background technology
Present aircraft engine when carrying out dismounting maintenance and maintenance process, stop accordingly after aircraft engine removes by nothing
Put guarantee equipment, the engine being removed is easy the reasons such as not paying attention to because parking improper, operating personnel, and generating means weigh wounded,
It the unnecessary damage such as collides with.
Invention content
Technical problem to be solved by the invention is to provide a kind of aircrafts that ground safeguard can be provided for aircraft engine
Engine parks bracket.
The technical solution adopted in the present invention is：A kind of aircraft engine parks bracket comprising holder is arranged in holder
The output shaft fixing device being arranged on output shaft tray, fuselage bracket in back-end support is arranged in the output shaft tray of front end
And the fuselage fixing device being arranged on fuselage bracket.
Fuselage bracket of the present invention includes being arranged in the side support bar of back-end support both sides and setting described in two
Midfoot support bar in the middle part of side support bar rolls in the side support bar and midfoot support bar and is provided with pulley.
The connection frame that fuselage fixing device of the present invention includes circular frame, is arranged in circular frame by connecting plate
Frame and the elastic buffering mechanism being uniformly arranged in connection framework, the circular frame, which rolls, to be arranged in side support bar and middle part
On the pulley of supporting rod.
Elastically damping device of the present invention is set to four or more, and the axis of four elastic buffering mechanisms described above
It intersects at a point.
Elastic buffering mechanism of the present invention includes that the buffer bar being fixed in connection framework and setting are buffering
Rubber pad on bar.
Output shaft fixing device of the present invention includes the fixed block being fixed on output shaft tray, leads to fixed block
It crosses the shaft of bearing rotation connection, be arranged in the terminal pad of shaft side and setting in shaft and positioned at fixed block and company
The positioning disk between disk is connect, is provided on fixed block and the matched fixed pin of positioning disk.
The present invention is provided with more than two location holes on the positioning disk, and multiple rounded settings of location hole are fixed
On the disk of position, the fixed pin is adapted with location hole.
The present invention is provided with traveling wheel on the bracket.
The positive effect of the present invention is：The present invention is fixed by being provided with output shaft fixing device and fuselage in rack
Device can be connected with corresponding fixing device so that engine can be highly stable respectively after aircraft engine removes
Be placed in rack, realize properly place, effectively avoid because park it is improper caused by damage.
Description of the drawings
Fig. 1 is schematic structural view of the invention；
Fig. 2 is output shaft fixture structure schematic diagram of the present invention；
Fig. 3 is partial enlarged view at Fig. 2 A of the present invention.
Specific implementation mode
As illustrated in the accompanying drawings from 1 to 3, the present invention includes holder 1, is arranged in 1 front end of holder（Left end i.e. shown in FIG. 1）Output
Shaft tray 8, is arranged in 1 rear end of holder the output shaft fixing device being arranged on output shaft tray 8（Right end i.e. shown in FIG. 1）
Fuselage bracket and the fuselage fixing device that is arranged on fuselage bracket, traveling wheel 16 and braking are additionally provided on holder 1
Device 14.Output shaft fixing device and fuselage fixing device are respectively used to the output shaft and fuselage of placement engine, can will send out
Motivation is integrally placed, and realizes properly parking for engine.
Fuselage bracket includes being arranged in the side support bar 2 of 1 rear end both sides of holder and setting in two side support bars 2
The midfoot support bar 3 at middle part rolls in the side support bar 2 and midfoot support bar 3 and is provided with pulley 15, and fuselage fixes dress
Placement location is on pulley 15.
Fuselage fixing device includes circular frame 4, is arranged in circular frame 4 by connecting plate 6 connection framework 5 and
The elastic buffering mechanism 7 being uniformly arranged in connection framework 5, the circular frame 4, which rolls, to be arranged in side support bar 2 and middle part branch
On the pulley 15 of strut 3.Under the action of pulley 15, realize that circular frame 4 can rotate on fuselage bracket.Elastically damping device
7 are set for being fixedly connected with and can effectively carry out damping with engine fuselage, avoid because shake it is excessive due to starting both to make
At damage.
The elastic buffering mechanism 7 includes the buffer bar being fixed in connection framework 5 and is arranged on buffer bar
Rubber pad.Its quantity is four or more, is uniformly arranged in connection framework 5, and four elastically damping devices described above
7 axis is set to intersect at a point.
The output shaft fixing device includes the fixed block 9 being fixed on output shaft tray 8, passes through with fixed block 9
The shaft 10 of bearing rotation connection is arranged in the terminal pad 12 of 10 side of shaft and setting in shaft 10 and positioned at fixation
Positioning disk 11 between block 9 and terminal pad 12, be provided on fixed block 9 with 11 matched fixed pin 13 of positioning disk, in institute
It states and is provided with more than two location holes 14 on positioning disk 11, multiple location holes 14 are rounded to be arranged on positioning disk 11, institute
Fixed pin 13 is stated to be adapted with location hole 14.There is the connection being mounted on by shaft 10 on fixed block 9 on output shaft fixing device
Disk 12, terminal pad 12 is for output axis connection with engine, can be with since shaft 10 is arranged by bearing on fixed block 9
It rotates freely in an axial direction, coordinates fuselage fixing device so that the rotation that engine can be whole, and positioning disk 11 and fixed pin
13, which can limit it, rotates freely, and realization can adjust the angle of engine in order to repair at any time.
Brake apparatus 14 is the braking strut being arranged on holder 1, braking strut lower end is provided with support plate, for whole
The braking of a holder 1.
The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although with reference to the foregoing embodiments
Invention is explained in detail, it will be understood by those of ordinary skill in the art that：It still can be to previous embodiment
Recorded technical solution is modified or equivalent replacement of some of the technical features；And these are changed or replace
It changes, the spirit and scope for technical solution of the embodiment of the present invention that it does not separate the essence of the corresponding technical solution.
Claims (7)
1. a kind of aircraft engine parks bracket, it is characterised in that it includes holder（1）, be arranged in holder（1）The output of front end
Shaft tray（8）, setting output shaft tray（8）On output shaft fixing device, be arranged in holder（1）The fuselage bracket of rear end with
And the fuselage fixing device being arranged on fuselage bracket；
The fuselage bracket includes being arranged in holder（1）The side support bar of rear end both sides（2）And setting is described collateral at two
Strut（2）The midfoot support bar at middle part（3）, in the side support bar（2）With midfoot support bar（3）On roll be provided with pulley
（15）.
2. a kind of aircraft engine according to claim 1 parks bracket, it is characterised in that the fuselage fixing device packet
Include circular frame（4）, pass through connecting plate（6）It is arranged in circular frame（4）Interior connection framework（5）And it is uniformly arranged on connection
Frame（5）On elastic buffering mechanism（7）, the circular frame（4）It rolls and is arranged in side support bar（2）With midfoot support bar
（3）Pulley（15）On.
3. a kind of aircraft engine according to claim 2 parks bracket, it is characterised in that the elastic buffering mechanism（7）
It it is four or more, and four elastic buffering mechanisms described above（7）Axis intersect at a point.
4. a kind of aircraft engine according to claim 2 parks bracket, it is characterised in that the elastic buffering mechanism（7）Packet
It includes and is fixed at connection framework（5）On buffer bar and the rubber pad that is arranged on buffer bar.
5. a kind of aircraft engine according to claim 1 parks bracket, it is characterised in that the output shaft fixing device
Including being fixed at output shaft tray（8）On fixed block（9）With fixed block（9）The shaft being rotatablely connected by bearing
（10）, be arranged in shaft（10）The terminal pad of side（12）And it is arranged in shaft（10）Above and it is located at fixed block（9）With company
Connect disk（12）Between positioning disk（11）, in fixed block（9）On be provided with and positioning disk（11）Matched fixed pin（13）.
6. a kind of aircraft engine according to claim 5 parks bracket, it is characterised in that in the positioning disk（11）On
It is provided with more than two location holes（14）, multiple location holes（14）It is rounded to be arranged in positioning disk（11）On, the fixation
Pin（13）With location hole（14）It is adapted.
7. parking bracket according to a kind of aircraft engine of claim 1-6 any one of them, it is characterised in that in the holder
（1）On be provided with traveling wheel（16）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711351475.5A CN108528756A (en) | 2017-12-15 | 2017-12-15 | A kind of aircraft engine parks bracket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711351475.5A CN108528756A (en) | 2017-12-15 | 2017-12-15 | A kind of aircraft engine parks bracket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108528756A true CN108528756A (en) | 2018-09-14 |
Family
ID=63488807
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711351475.5A Pending CN108528756A (en) | 2017-12-15 | 2017-12-15 | A kind of aircraft engine parks bracket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108528756A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112441252A (en) * | 2020-10-14 | 2021-03-05 | 广州飞机维修工程有限公司 | Dismounting method of aircraft engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6170141B1 (en) * | 1998-09-25 | 2001-01-09 | Stanley Aviation Corporation | Shipping system for jet aircraft engine and method of installing and removing jet aircraft engine |
| US20090294625A1 (en) * | 2008-05-29 | 2009-12-03 | Rolls-Royce Plc | Cradle arrangement |
| CN202030493U (en) * | 2010-12-16 | 2011-11-09 | 神华集团有限责任公司 | Overturn support of engine |
| WO2017020881A1 (en) * | 2015-07-31 | 2017-02-09 | MTU Aero Engines AG | Guide carriage for an engine component |
| CN107443348A (en) * | 2017-08-15 | 2017-12-08 | 中国航空工业集团公司沈阳飞机设计研究所 | Lift various dimensions adjust motor mounts car |
| CN207860500U (en) * | 2017-12-15 | 2018-09-14 | 石家庄飞机工业有限责任公司 | A kind of aircraft engine parks bracket |
-
2017
- 2017-12-15 CN CN201711351475.5A patent/CN108528756A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6170141B1 (en) * | 1998-09-25 | 2001-01-09 | Stanley Aviation Corporation | Shipping system for jet aircraft engine and method of installing and removing jet aircraft engine |
| US20090294625A1 (en) * | 2008-05-29 | 2009-12-03 | Rolls-Royce Plc | Cradle arrangement |
| CN202030493U (en) * | 2010-12-16 | 2011-11-09 | 神华集团有限责任公司 | Overturn support of engine |
| WO2017020881A1 (en) * | 2015-07-31 | 2017-02-09 | MTU Aero Engines AG | Guide carriage for an engine component |
| CN107443348A (en) * | 2017-08-15 | 2017-12-08 | 中国航空工业集团公司沈阳飞机设计研究所 | Lift various dimensions adjust motor mounts car |
| CN207860500U (en) * | 2017-12-15 | 2018-09-14 | 石家庄飞机工业有限责任公司 | A kind of aircraft engine parks bracket |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112441252A (en) * | 2020-10-14 | 2021-03-05 | 广州飞机维修工程有限公司 | Dismounting method of aircraft engine |
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| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180914 |