CN106697304A - High-reliability aircraft engine mounting mechanism - Google Patents
High-reliability aircraft engine mounting mechanism Download PDFInfo
- Publication number
- CN106697304A CN106697304A CN201710110385.0A CN201710110385A CN106697304A CN 106697304 A CN106697304 A CN 106697304A CN 201710110385 A CN201710110385 A CN 201710110385A CN 106697304 A CN106697304 A CN 106697304A
- Authority
- CN
- China
- Prior art keywords
- mounting bracket
- engine
- aircraft
- installing mechanism
- 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
- 230000035939 shock Effects 0.000 claims description 11
- 239000003638 chemical reducing agent Substances 0.000 claims description 3
- 238000004080 punching Methods 0.000 claims 1
- 238000013016 damping Methods 0.000 abstract 3
- 230000000149 penetrating effect Effects 0.000 abstract 1
- 230000003139 buffering effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 208000020442 loss of weight Diseases 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Classifications
-
- B64D27/40—
Abstract
The present invention relates to the technical field of aircraft design, and especially relates to a high-reliability aircraft engine mounting mechanism, which is characterized by comprising two parallel baseboards fixed on an aircraft, buffer boards horizontally provided above the baseboards, support columns penetrating the baseboards and the buffer boards in order, damping columns erected between the baseboards and the buffer boards and sleeved on the support columns, as well as a first mounting bracket and a second mounting bracket vertically provided at the both ends of the buffer boards, and an engine is mounted on the first mounting bracket and the second mounting bracket. According to the present invention, the engine is mounted above the aircraft through the mounting mechanism, the damping columns fulfill the function of damping, the mounting mechanism is unlikely to deformation, mounting and dismantling are convenient, and the aircraft is more stable.
Description
Technical field
A kind of aircraft devices field of the present invention, and in particular to installing mechanism of high reliability aircraft engine.
Background technology
Installed using suspension beam structure more than the installing mechanism of the engine of conventional aircraft, the hanging stress of engine, engine
Installing mechanism be easily deformed and influence the installation accuracy of engine.In addition, install engine support directly with engine and
Aircraft is contacted firmly, and the life-span of aircraft can also be given a shock influence.
The content of the invention
The present invention is easily deformed for overarm mounting bracket set forth above, and influences asking for the service life of aircraft
Topic, and a kind of installing mechanism of research and design is not allowed yielding and can be effectively isolated engine high-frequency vibration, it is to avoid to aircraft
Produce the installing mechanism of the high reliability aircraft engine of influence.
The technical solution adopted for the present invention to solve the technical problems is：
A kind of installing mechanism of high reliability aircraft engine, it is characterised in that including：It is fixed on carry-on two
The base plate be arrangeding in parallel, the buffer board being horizontally set on above the base plate, the support for sequentially passing through the base plate and buffer board
Post, the shock structure for being erected between the base plate and buffer board and being set on the support column and it is vertically set on buffering
First mounting bracket and the second mounting bracket at plate two ends, engine are arranged on the first mounting bracket and the second mounting bracket.
Further, there are four screw holes for being used for stationary engine on first mounting bracket.
Further, there are two to be used for installing the bearing mounting holes of bearing on first mounting bracket, engine it is defeated
Shaft and reducer shaft are erected on first mounting bracket by bearing respectively.
Further, it is characterised in that there are multiple lightening holes on second mounting bracket.
Further, the installing mechanism also includes the steering wheel fixed mount being fixedly connected with steering wheel, the steering wheel fixed mount
It is fixedly connected on the bottom of the first mounting bracket.
Further, the shock structure is six.
A kind of beneficial effect of the installing mechanism of high reliability aircraft engine of the invention is：
The 1st, installing mechanism is arranged on the top of aircraft, engine is horizontally arranged on installing mechanism, be easily installed and
Dismounting, and engine acts perpendicularly to support and aircraft, it is more reliable and more stable.
2nd, realize being flexible coupling by shock structure between engine and aircraft, six shock structures are effectively isolated engine product
Raw dither, reduces the infringement to engine and aircraft, improves service life.
3rd, lightening hole is set on the second mounting bracket, while support engine is ensured, reduces the load of whole aircraft.
Brief description of the drawings
The present invention is further detailed explanation with reference to the accompanying drawings and detailed description.
Fig. 1 is the stereogram that embodiment of the present invention installing mechanism is connected with engine；
Fig. 2 is the preceding visual angle stereogram of embodiment of the present invention installing mechanism；
Fig. 3 is embodiment of the present invention installing mechanism back angle stereogram.
Wherein：1st, base plate, the 2, first mounting bracket, 21, bearing mounting hole, 22, screw hole, the 3, second mounting bracket, 31, loss of weight
Hole, 4, buffer board, 5, support column, 6, shock structure, 7, engine, 8, steering wheel fixed mount.
Specific embodiment
In conjunction with the accompanying drawings, the present invention is further explained in detail.These accompanying drawings are simplified schematic diagram, only with
Illustration illustrates basic structure of the invention, therefore it only shows the composition relevant with the present invention.
The installing mechanism of high reliability aircraft engine as shown in Figure 1-Figure 3, including：Base plate 1, the first mounting bracket 2,
Second mounting bracket 3, buffer board 4, support column 5, shock structure 6 and steering wheel fixed mount 8.Referring to Fig. 2 and Fig. 3, the horizontal parallel of two base plate 1
Set, base plate 1 is fixed on board the aircraft, and buffer board 4 is horizontally set on the top of base plate 1, and support column 5 sequentially passes through the He of base plate 1
Buffer board 4, shock structure 6 is folded between base plate 1 and buffer board 4 and is set on support column 5, and the first mounting bracket 2 and second is pacified
3 two ends for being vertically arranged buffer board 4 are shelved, two mounting brackets are used for fixedly mounting engine 7, have two on the first mounting bracket 2
Bearing mounting hole 21 and four screw holes 22, four screw holes 22 are used for for the shell of engine 7 being fixed on the first mounting bracket 2
On, two bearing mounting holes 21 are respectively intended to place for installing the bearing of engine output shaft and reducer shaft.
From figure 3, it can be seen that the load in order to reduce whole aircraft, has multiple lightening holes on the second mounting bracket 3
31。
Steering wheel fixed mount 8 is fixed on the lower section of the first mounting bracket 2, for being fixedly connected with steering wheel.Shock structure 6 is six,
It is symmetricly set between two base plates 1 and buffer board 4, effectively the pressure between buffering engine 7 and base plate 1 (aircraft).
It should be appreciated that specific embodiment described above is only used for explaining the present invention, it is not intended to limit the present invention.By
Obvious change that spirit of the invention is extended out or among changing still in protection scope of the present invention.
Claims (6)
1. a kind of installing mechanism of high reliability aircraft engine, it is characterised in that including：It is fixed on carry-on two flat
Row set base plate (1), be horizontally set on above the base plate (1) buffer board (4), sequentially pass through the base plate (1) ease up
The support column (5) of punching (4), it is erected between the base plate (1) and buffer board (4) and is set on the support column (5)
Shock structure (6) and first mounting bracket (2) and the second mounting bracket (3) at buffer board (4) two ends are vertically set on, engine (7)
On the first mounting bracket (2) and the second mounting bracket (3).
2. the installing mechanism of high reliability aircraft engine according to claim 1, it is characterised in that first peace
Shelving on (2) has four screw holes (22) for being used for stationary engine (7).
3. the installing mechanism of high reliability aircraft engine according to claim 1 and 2, it is characterised in that described
There are two bearing mounting holes (21) for being used for installing bearing, the output shaft and reducer shaft of engine (7) on one mounting bracket (2)
It is erected on first mounting bracket (2) by bearing respectively.
4. the installing mechanism of high reliability aircraft engine according to claim 3, it is characterised in that second peace
Shelving on (3) has multiple lightening holes (31).
5. the installing mechanism of high reliability aircraft engine according to claim 1, it is characterised in that the fitting machine
Structure also includes the steering wheel fixed mount (8) being fixedly connected with steering wheel, and the steering wheel fixed mount (8) is fixedly connected the first mounting bracket (2)
Bottom.
6. the installing mechanism of high reliability aircraft engine according to claim 1, it is characterised in that the shock structure
(6) it is six.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710110385.0A CN106697304A (en) | 2017-02-28 | 2017-02-28 | High-reliability aircraft engine mounting mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710110385.0A CN106697304A (en) | 2017-02-28 | 2017-02-28 | High-reliability aircraft engine mounting mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106697304A true CN106697304A (en) | 2017-05-24 |
Family
ID=58917831
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710110385.0A Pending CN106697304A (en) | 2017-02-28 | 2017-02-28 | High-reliability aircraft engine mounting mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106697304A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111043453A (en) * | 2020-01-02 | 2020-04-21 | 上海蓝享机械制造有限公司 | Rocket engine support |
| CN114435602A (en) * | 2022-03-19 | 2022-05-06 | 北京航空航天大学 | Unmanned aerial vehicle engine mounting bracket |
Citations (14)
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| FR445839A (en) * | 1912-07-06 | 1912-11-20 | App D Aviat Hanriot Des | Device for making removable the propulsion units of airplanes |
| US5509837A (en) * | 1994-10-05 | 1996-04-23 | Allbright, Jr.; Walter E. | Truss system engine mount for light watercraft |
| KR20020017542A (en) * | 2000-08-30 | 2002-03-07 | 임두남 | Vertical takeoff and landing small plane |
| US20060108477A1 (en) * | 2004-11-23 | 2006-05-25 | Helou Elie Jr | Cargo aircraft |
| KR20070047002A (en) * | 2005-11-01 | 2007-05-04 | 아틱스엔지니어링(주) | Stand for a test of an engine |
| CN202414168U (en) * | 2011-11-29 | 2012-09-05 | 成都精石模型开发有限公司 | Multipurpose unmanned helicopter capable of effectively removing resonance |
| KR20130113420A (en) * | 2010-06-14 | 2013-10-15 | 로오드 코포레이션 | A helicopter engine mounting system and methods |
| CN203666364U (en) * | 2013-11-30 | 2014-06-25 | 淮北市天路航空科技股份有限公司 | Engine fixing base |
| CN204096080U (en) * | 2014-08-18 | 2015-01-14 | 国网湖北电力中超建设管理公司 | A kind of multi-rotor aerocraft load shock absorption device |
| CN204310030U (en) * | 2014-10-27 | 2015-05-06 | 湖南农业大学 | A kind of fuselage ring structure of pilotless helicopter |
| CN205044510U (en) * | 2015-10-21 | 2016-02-24 | 浙江华铝铝业股份有限公司 | Novel portable automobile engine base support |
| US20160304186A1 (en) * | 2015-04-20 | 2016-10-20 | Airbus Operations (Sas) | Aircraft having a simplified general section |
| CN205768602U (en) * | 2016-05-23 | 2016-12-07 | 重庆凯特动力科技有限公司 | Back suspension device of engine assembly |
| CN206502033U (en) * | 2017-02-28 | 2017-09-19 | 天峋（常州）智能科技有限公司 | A kind of installing mechanism of high reliability aircraft engine |
-
2017
- 2017-02-28 CN CN201710110385.0A patent/CN106697304A/en active Pending
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR445839A (en) * | 1912-07-06 | 1912-11-20 | App D Aviat Hanriot Des | Device for making removable the propulsion units of airplanes |
| US5509837A (en) * | 1994-10-05 | 1996-04-23 | Allbright, Jr.; Walter E. | Truss system engine mount for light watercraft |
| KR20020017542A (en) * | 2000-08-30 | 2002-03-07 | 임두남 | Vertical takeoff and landing small plane |
| US20060108477A1 (en) * | 2004-11-23 | 2006-05-25 | Helou Elie Jr | Cargo aircraft |
| KR20070047002A (en) * | 2005-11-01 | 2007-05-04 | 아틱스엔지니어링(주) | Stand for a test of an engine |
| KR20130113420A (en) * | 2010-06-14 | 2013-10-15 | 로오드 코포레이션 | A helicopter engine mounting system and methods |
| CN202414168U (en) * | 2011-11-29 | 2012-09-05 | 成都精石模型开发有限公司 | Multipurpose unmanned helicopter capable of effectively removing resonance |
| CN203666364U (en) * | 2013-11-30 | 2014-06-25 | 淮北市天路航空科技股份有限公司 | Engine fixing base |
| CN204096080U (en) * | 2014-08-18 | 2015-01-14 | 国网湖北电力中超建设管理公司 | A kind of multi-rotor aerocraft load shock absorption device |
| CN204310030U (en) * | 2014-10-27 | 2015-05-06 | 湖南农业大学 | A kind of fuselage ring structure of pilotless helicopter |
| US20160304186A1 (en) * | 2015-04-20 | 2016-10-20 | Airbus Operations (Sas) | Aircraft having a simplified general section |
| CN205044510U (en) * | 2015-10-21 | 2016-02-24 | 浙江华铝铝业股份有限公司 | Novel portable automobile engine base support |
| CN205768602U (en) * | 2016-05-23 | 2016-12-07 | 重庆凯特动力科技有限公司 | Back suspension device of engine assembly |
| CN206502033U (en) * | 2017-02-28 | 2017-09-19 | 天峋（常州）智能科技有限公司 | A kind of installing mechanism of high reliability aircraft engine |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111043453A (en) * | 2020-01-02 | 2020-04-21 | 上海蓝享机械制造有限公司 | Rocket engine support |
| CN114435602A (en) * | 2022-03-19 | 2022-05-06 | 北京航空航天大学 | Unmanned aerial vehicle engine mounting bracket |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20221227 Address after: Room 2211, 22nd Floor, Block D, Zhizhen Building, No. 7 Zhichun Road, Haidian District, Beijing 100088 Applicant after: TIANXUN INNOVATION (BEIJING) TECHNOLOGY CO.,LTD. Address before: Building A1, Zhongke entrepreneurship center, Changzhou science and Education City, No.18, middle Changwu Road, Changzhou City, Jiangsu Province, 213000 Applicant before: VOLITATION (CHANGZHOU) INTELLIGENT TECHNOLOGY CO.,LTD. |