CN107264814A - A kind of engine mounting component - Google Patents
A kind of engine mounting component Download PDFInfo
- Publication number
- CN107264814A CN107264814A CN201610210417.XA CN201610210417A CN107264814A CN 107264814 A CN107264814 A CN 107264814A CN 201610210417 A CN201610210417 A CN 201610210417A CN 107264814 A CN107264814 A CN 107264814A
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- Prior art keywords
- crash
- engine
- ring
- pin
- shock absorber
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- Pending
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- 230000035939 shock Effects 0.000 claims abstract description 21
- 239000006096 absorbing agent Substances 0.000 claims abstract description 19
- 238000009434 installation Methods 0.000 abstract description 8
- 238000010586 diagram Methods 0.000 description 3
- 238000010521 absorption reaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
本发明属于发动机安装技术领域，涉及一种发动机座架组件。减震器(13)安装在发动机支架(11)和发动机支座(12)之间，抗坠毁装置(14)由抗坠毁环(15)和抗坠毁销(16)组成，抗坠毁环(15)固定在发动机支架(11)的下部，抗坠毁销(16)固定在发动机支座上，抗坠毁环(15)是一个带有两个安装耳片的环状结构，抗坠毁销(16)是一个圆柱结构，抗坠毁销(16)插入在抗坠毁环(15)内，两者具有相同的轴线，发动机支架(11)下部两侧各安装一个减震器(13)，且抗坠毁环(15)在发动机支架(11)上的宽度方向不对称。本技术方案提供的发动机座架组件高度尺寸降低、重量减轻。
The invention belongs to the technical field of engine installation, and relates to an engine mount assembly. Shock absorber (13) is installed between engine support (11) and engine support (12), anti-crash device (14) is made up of anti-crash ring (15) and anti-crash pin (16), anti-crash ring (15) ) is fixed on the bottom of the engine bracket (11), the anti-crash pin (16) is fixed on the engine support, the anti-crash ring (15) is a ring structure with two mounting lugs, and the anti-crash pin (16) It is a cylindrical structure, and the anti-crash pin (16) is inserted in the anti-crash ring (15). (15) The width direction on the engine bracket (11) is asymmetrical. The engine mounting assembly provided by the technical solution has reduced height and reduced weight.
Description
技术领域technical field
本发明属于发动机安装技术领域，涉及一种发动机座架组件。The invention belongs to the technical field of engine installation, and relates to an engine mount assembly.
背景技术Background technique
现有Z9直升机的发动机座架组件如图1所示用于为发动机提供安装和减震。具有发动机支架1和发动机支座2，两者之间安装有减震器3。为了在坠毁条件下保持发动机不脱落，发动机座架组件上设置了抗坠毁装置。同时，为了防止发动机支架1错误安装，发动机座架组件上设置了防差错结构。The engine mounting assembly of the existing Z9 helicopter is used to provide installation and shock absorption for the engine as shown in Figure 1. It has an engine support 1 and an engine support 2, and a shock absorber 3 is installed between the two. In order to keep the engine from falling out under crash conditions, anti-crash devices are provided on the engine mount assembly. Simultaneously, in order to prevent the wrong installation of the engine bracket 1, an anti-mistake structure is provided on the engine mount assembly.
抗坠毁装置由发动机支座2上的抗坠毁销6和发动机支架1上的孔7组成。在坠毁条件下，减震器3可能破坏，抗坠毁销6与孔7接触，能够承受坠毁的载荷，使得发动机支座2和发动机支架1不会分开。The anti-crash device is made up of the anti-crash pin 6 on the engine mount 2 and the hole 7 on the engine mount 1. Under crash conditions, the shock absorber 3 may be damaged, and the anti-crash pin 6 is in contact with the hole 7 to withstand the load of the crash, so that the engine mount 2 and the engine mount 1 will not be separated.
防差错结构有一个防错销4和一个防错角片5组成。防错销4安装在发动机支架1底部，防错角片5安装在发动机支座2上。错误安装时，防错销4顶在防错角片5上，无法继续安装，起到防差错效果。The error-proofing structure has an error-proofing pin 4 and an error-proofing angle piece 5 to form. The anti-error pin 4 is installed on the bottom of the engine bracket 1, and the anti-error angle piece 5 is installed on the engine support 2. During wrong installation, the wrong-proof pin 4 is pushed on the wrong-proof angle piece 5, and the installation cannot be continued, which plays a wrong-proof effect.
由于这种发动机座架组件采用的抗坠毁装置的结构特征，发动机支架1的高度尺寸偏大。Due to the structural features of the anti-crash device adopted by this engine mounting assembly, the height dimension of the engine support 1 is too large.
由于这种发动机座架组件采用的防差错装置的结构特征，发动机支座2的高度尺寸偏大。且防差错装置仅具有防错功能，不具有其他功能。Due to the structural features of the anti-error device adopted by this engine mount assembly, the height dimension of the engine mount 2 is too large. And the anti-error device only has an error-proof function, and does not have other functions.
因此这种发动机座架组件的总体高度尺寸偏大，重量偏大。Therefore the overall height dimension of this engine mount assembly is too big, and the weight is too big.
发明内容Contents of the invention
本发明要解决的技术问题：提供一种高度尺寸降低和重量减轻的发动机座架组件。The technical problem to be solved by the present invention is to provide an engine mount assembly with reduced height and reduced weight.
本发明的技术方案：一种发动机座架组件，其特征为：所述的组件由发动机支架11和发动机支座12，减震器13和抗坠毁装置14组成，减震器13安装在发动机支架11和发动机支座12之间，抗坠毁装置14由抗坠毁环15和抗坠毁销16组成，抗坠毁环15固定在发动机支架11的下部，抗坠毁销16固定在发动机支座上，抗坠毁环15是一个带有两个安装耳片的环状结构，抗坠毁销16是一个圆柱结构，抗坠毁销16插入在抗坠毁环15内，两者具有相同的轴线，发动机支架11下部两侧各安装一个减震器13，且抗坠毁环15在发动机支架11上的宽度方向不对称。The technical solution of the present invention: an engine mount assembly, characterized in that: the assembly is composed of an engine bracket 11 and an engine mount 12, a shock absorber 13 and an anti-crash device 14, and the shock absorber 13 is installed on the engine bracket 11 and the engine support 12, anti-crash device 14 is made up of anti-crash ring 15 and anti-crash pin 16, and anti-crash ring 15 is fixed on the bottom of engine support 11, and anti-crash pin 16 is fixed on the engine support, and anti-crash The ring 15 is a ring structure with two mounting lugs. The anti-crash pin 16 is a cylindrical structure. The anti-crash pin 16 is inserted in the anti-crash ring 15. Both have the same axis. The two sides of the lower part of the engine bracket 11 Each shock absorber 13 is installed, and the width direction of the anti-crash ring 15 on the engine support 11 is asymmetrical.
本发明的有益效果：本技术方案提供的发动机座架组件高度尺寸降低、重量减轻，可以为发动机提供安装和减震，并保证发动机座架组件具有抗坠毁和防差错功能，且抗坠毁和防差错功能通过相同的一套装置实现。Beneficial effects of the present invention: the height and size of the engine mount assembly provided by the technical solution are reduced, and the weight is lightened, which can provide installation and shock absorption for the engine, and ensure that the engine mount assembly has anti-crash and error-proof functions, and is anti-crash and anti-error. The error function is realized by the same set of devices.
附图说明Description of drawings
图1为Z9直升机的发动机座架组件示意图。Figure 1 is a schematic diagram of the engine mount assembly of the Z9 helicopter.
图2为本发明所述的发动机座架组件示意图。Fig. 2 is a schematic diagram of the engine mount assembly according to the present invention.
图3为本发明抗坠毁装置安装示意图。Figure 3 is a schematic diagram of the installation of the anti-crash device of the present invention.
图中，1为发动机支架、2为发动机支座、3为减震器、4为防错销、5为防错角片、6为抗坠毁销、7为发动机支架上的孔，11为发动机支架、12为发动机支座、13为减震器、14为抗坠毁装置、15为抗坠毁环、16为抗坠毁销、17为左减震器中心线、18为右减震器中心线、a为左减震器中心线17到抗坠毁环中心线的距离，b为右减震器中心线18到抗坠毁环中心线的距离。In the figure, 1 is the engine bracket, 2 is the engine support, 3 is the shock absorber, 4 is the anti-error pin, 5 is the anti-error angle piece, 6 is the anti-crash pin, 7 is the hole on the engine bracket, and 11 is the engine Bracket, 12 is the engine support, 13 is the shock absorber, 14 is the anti-crash device, 15 is the anti-crash ring, 16 is the anti-crash pin, 17 is the center line of the left shock absorber, 18 is the center line of the right shock absorber, a is the distance from the centerline 17 of the left shock absorber to the centerline of the anti-crash ring, and b is the distance from the centerline 18 of the right shock absorber to the centerline of the anti-crash ring.
具体实施方式detailed description
如图2和3所示，本发明所述的发动机座架组件由发动机支架11和发动机支座12，减震器13和抗坠毁装置14组成。As shown in FIGS. 2 and 3 , the engine mount assembly of the present invention consists of an engine bracket 11 and an engine mount 12 , a shock absorber 13 and an anti-crash device 14 .
减震器13安装在发动机支架11和发动机支座12之间。抗坠毁装置14由抗坠毁环15和抗坠毁销16组成。抗坠毁环15固定在发动机支架11的下部，抗坠毁销16固定在发动机支座上。抗坠毁环15是一个带有两个安装耳片的环状结构，抗坠毁销16是一个圆柱结构。抗坠毁销16插入在抗坠毁环15内，两者具有相同的轴线。The shock absorber 13 is installed between the engine mount 11 and the engine mount 12 . Anti-crash device 14 is made up of anti-crash ring 15 and anti-crash pin 16. Anti-crash ring 15 is fixed on the bottom of engine support 11, and anti-crash pin 16 is fixed on the engine support. The anti-crash ring 15 is an annular structure with two mounting lugs, and the anti-crash pin 16 is a cylindrical structure. The anti-crash pin 16 is inserted in the anti-crash ring 15, both having the same axis.
正常飞行载荷下，抗坠毁环15和抗坠毁销16之间留有足够的间隙。在坠毁条件下，减震器13可能破坏，抗坠毁环15和抗坠毁销16接触，能够承受坠毁的载荷，使得发动机支座12和发动机支架11不会脱离。Under normal flight load, there is enough clearance between the anti-crash ring 15 and the anti-crash pin 16. Under the crash condition, the shock absorber 13 may be damaged, the anti-crash ring 15 and the anti-crash pin 16 are in contact, and can bear the load of the crash, so that the engine mount 12 and the engine mount 11 will not disengage.
发动机支架11下部两侧各安装一个减震器13。且抗坠毁环15在发动机支架11上的宽度方向是不对称的(图3中，a≠b)。发动机支架11错误安装调转180度时，抗坠毁环和抗坠毁销互相干涉，无法继续安装，起到防差错效果。A shock absorber 13 is respectively installed on both sides of the engine support 11 bottom. And the width direction of the anti-crash ring 15 on the engine bracket 11 is asymmetrical (in FIG. 3, a≠b). When the engine support 11 is incorrectly installed and rotated 180 degrees, the anti-crash ring and the anti-crash pin interfere with each other, and cannot continue to be installed, which plays an error-proof effect.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610210417.XA CN107264814A (en) | 2016-04-06 | 2016-04-06 | A kind of engine mounting component |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610210417.XA CN107264814A (en) | 2016-04-06 | 2016-04-06 | A kind of engine mounting component |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107264814A true CN107264814A (en) | 2017-10-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610210417.XA Pending CN107264814A (en) | 2016-04-06 | 2016-04-06 | A kind of engine mounting component |
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| CN (1) | CN107264814A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4634081A (en) * | 1983-12-30 | 1987-01-06 | The Boeing Company | Aft engine mount with vibration isolators |
| US4717094A (en) * | 1986-05-19 | 1988-01-05 | The Boeing Company | Aircraft engine mount system with vibration isolators |
| US5092538A (en) * | 1991-04-02 | 1992-03-03 | Denney Larry D | Mounting system for two cycle in-line engine |
| US5303896A (en) * | 1992-11-12 | 1994-04-19 | Sterka William E | Model airplane engine mounting system |
| CN1174798A (en) * | 1996-08-22 | 1998-03-04 | 波音公司 | Fail-safe engine mount system |
| CN101163624A (en) * | 2005-06-29 | 2008-04-16 | 法国空中客车公司 | Engine accessory pylon for an aircraft |
| US7874515B2 (en) * | 2007-01-25 | 2011-01-25 | Lockheed-Martin Corporation | Air vehicle propulsion system on gimbaled truss |
| US20120012732A1 (en) * | 2010-06-14 | 2012-01-19 | Daniel Zameroski | Helicopter engine mounting system and methods |
-
2016
- 2016-04-06 CN CN201610210417.XA patent/CN107264814A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4634081A (en) * | 1983-12-30 | 1987-01-06 | The Boeing Company | Aft engine mount with vibration isolators |
| US4717094A (en) * | 1986-05-19 | 1988-01-05 | The Boeing Company | Aircraft engine mount system with vibration isolators |
| US5092538A (en) * | 1991-04-02 | 1992-03-03 | Denney Larry D | Mounting system for two cycle in-line engine |
| US5303896A (en) * | 1992-11-12 | 1994-04-19 | Sterka William E | Model airplane engine mounting system |
| CN1174798A (en) * | 1996-08-22 | 1998-03-04 | 波音公司 | Fail-safe engine mount system |
| CN101163624A (en) * | 2005-06-29 | 2008-04-16 | 法国空中客车公司 | Engine accessory pylon for an aircraft |
| US7874515B2 (en) * | 2007-01-25 | 2011-01-25 | Lockheed-Martin Corporation | Air vehicle propulsion system on gimbaled truss |
| US20120012732A1 (en) * | 2010-06-14 | 2012-01-19 | Daniel Zameroski | Helicopter engine mounting system and methods |
Non-Patent Citations (1)
| Title |
|---|
| 端木京顺等: "《航空装备安全学（第2版）》", 31 January 2016, 国防工业出版社 * |
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Application publication date: 20171020 |