CN113044228A - Installation method of airplane equipment - Google Patents
Installation method of airplane equipment Download PDFInfo
- Publication number
- CN113044228A CN113044228A CN201911379826.2A CN201911379826A CN113044228A CN 113044228 A CN113044228 A CN 113044228A CN 201911379826 A CN201911379826 A CN 201911379826A CN 113044228 A CN113044228 A CN 113044228A
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- CN
- China
- Prior art keywords
- shaped material
- equipment
- bracket
- airplane
- material support
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- 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.)
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Links
- 238000009434 installation Methods 0.000 title claims abstract description 26
- 238000000034 method Methods 0.000 title claims abstract description 13
- 230000009286 beneficial effect Effects 0.000 description 1
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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
- B64D47/00—Equipment not otherwise provided for
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- 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
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Toys (AREA)
Abstract
The invention belongs to the mechanical design of airplanes, and mainly relates to equipment installation for a semi-closed area of a compact part of an airplane. The invention relates to an installation method of airplane equipment, wherein the installation position of the equipment is positioned in an airplane landing gear cabin and between two frame webs, the equipment is hung on one side of the frame webs through four Z-shaped material supports, each Z-shaped material support comprises a middle vertical surface, an upper plane and a lower plane, equipment installation holes are formed in the upper plane of each Z-shaped material support, and the lower plane of each Z-shaped material support is fixedly connected with the frame webs. The equipment mounting bracket adopts the Z-shaped material bracket with uniform specification, and has strong universality and simple structure. The two-two parallel and two-two perpendicular fixing connection mode of the support ensures the mounting strength required by equipment mounting, and can provide the convenience for dismounting and maintaining the small-space side mounting equipment of the airplane.
Description
Technical Field
The invention belongs to the mechanical design of airplanes, and mainly relates to equipment installation for a semi-closed area of a compact part of an airplane.
Background
The equipment on the aircraft is installed in various forms, and generally, the equipment support is designed integrally or is combined into the support required by the equipment through various profiles. When the equipment needs to be installed in a small position space and is in a semi-closed state, the bracket is specially designed in order to meet the requirements of installation strength, stability and the like of the equipment. Particularly, when airborne equipment needs to be installed between two frame webs in an aircraft landing gear cabin, the existing installation frame and installation method cannot meet the requirements of quick installation, good maintainability, light weight and the like.
Disclosure of Invention
The application aims to provide an installation method of airplane equipment according to airplane design requirements.
The installation method of the aircraft equipment is characterized in that the equipment is hung on one side of a frame web plate through four Z-shaped material supports, each Z-shaped material support comprises a middle vertical face, an upper plane and a lower plane, equipment installation holes are formed in the upper plane of each Z-shaped material support, and the lower plane of each Z-shaped material support is fixedly connected with the frame web plate.
The number of the Z-shaped material supports is four, wherein a first Z-shaped material support and a fourth Z-shaped material support are located at the right side installation position of the frame web, a second Z-shaped material support and a third Z-shaped material support are located at the left side installation position of the frame web, the middle vertical faces of the first Z-shaped material support and the fourth Z-shaped material support are located on the same longitudinal plane, the middle vertical faces of the second Z-shaped material support and the third Z-shaped material support are parallel to each other, the middle vertical face of the first Z-shaped material support is perpendicular to the middle vertical face of the second Z-shaped material support, and the middle vertical face of the third Z-shaped material support is perpendicular to the middle vertical face of the fourth Z-shaped material support.
The beneficial effect of this application lies in: the equipment mounting support adopts a Z-shaped material support with uniform specification, and has strong universality and simple structure. The two-two parallel and two-two perpendicular fixing connection mode of the support ensures the mounting strength required by equipment mounting, and can provide the convenience for dismounting and maintaining the small-space side mounting equipment of the airplane.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
Fig. 1 is a schematic view of an aircraft equipment installation method as proposed in the present application.
The numbering in the figures illustrates: 1 a first Z-shaped material bracket, 2 a second Z-shaped material bracket, a third Z-shaped material bracket, a fourth Z-shaped material bracket and 5 frame webs.
Detailed Description
Referring to the attached drawings, the installation position of the equipment is located in an aircraft landing gear cabin, the equipment is hung on one side of two frame web plates 5 between the two frame web plates through four Z-shaped material supports, each Z-shaped material support comprises a middle vertical surface, an upper plane and a lower plane, equipment installation holes are formed in the upper plane of each Z-shaped material support, and the lower plane of each Z-shaped material support is fixedly connected with the frame web plates.
In implementation, the number of the Z-shaped material brackets is four, wherein a first Z-shaped material bracket 1 and a fourth Z-shaped material bracket 4 are positioned at the right side installation position of the frame web 5, a second Z-shaped material bracket 2 and a third Z-shaped material bracket 3 are positioned at the left side installation position of the frame web 5, the middle vertical surfaces of the first Z-shaped material bracket 1 and the fourth Z-shaped material bracket 4 are positioned on the same longitudinal plane, the middle vertical surfaces of the second Z-shaped material bracket 2 and the third Z-shaped material bracket 3 are parallel to each other, the middle vertical surface of the first Z-shaped material bracket 1 is perpendicular to the middle vertical surface of the second Z-shaped material bracket 2, and the middle vertical surface of the third Z-shaped material bracket 3 is perpendicular to the middle vertical surface of the fourth Z-shaped material bracket 4. The required installation intensity of equipment fixing has been guaranteed through two liang of parallels of Z style of calligraphy material support and two liang of vertically linking firmly the mode again to this application, can provide the convenience of dismantling and maintaining at aircraft little space side direction erection equipment.
Claims (6)
1. The installation method of the aircraft equipment is characterized in that the equipment is hung on one side of a frame web plate through four Z-shaped material supports, each Z-shaped material support comprises a middle vertical face, an upper plane and a lower plane, equipment installation holes are formed in the upper plane of each Z-shaped material support, and the lower plane of each Z-shaped material support is fixedly connected with the frame web plate.
2. The method of installing aircraft equipment according to claim 1, wherein there are four zigzag material brackets, wherein a first zigzag material bracket and a fourth zigzag material bracket are located at a right side installation position of the frame web, and wherein a second zigzag material bracket and a third zigzag material bracket are located at a left side installation position of the frame web.
3. A method of installing aircraft equipment according to claim 2 wherein the intermediate elevations of the first and fourth zigzag brackets lie in the same longitudinal plane.
4. A method of installing aircraft equipment according to claim 3 wherein the intermediate elevations of the second and third zigzag brackets are parallel to one another.
5. A method of installing aircraft equipment according to claim 4 wherein the intermediate upright surface of the first Z-profile bracket is perpendicular to the intermediate upright surface of the second Z-profile bracket.
6. A method of installing aircraft equipment according to claim 5 wherein the intermediate upright surface of the third Z-profile bracket is perpendicular to the intermediate upright surface of the fourth Z-profile bracket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911379826.2A CN113044228A (en) | 2019-12-27 | 2019-12-27 | Installation method of airplane equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911379826.2A CN113044228A (en) | 2019-12-27 | 2019-12-27 | Installation method of airplane equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113044228A true CN113044228A (en) | 2021-06-29 |
Family
ID=76506691
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911379826.2A Pending CN113044228A (en) | 2019-12-27 | 2019-12-27 | Installation method of airplane equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113044228A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1981002718A1 (en) * | 1980-03-21 | 1981-10-01 | Boeing Co | Method and apparatus for vibration damping structural elements |
| US5893534A (en) * | 1995-12-22 | 1999-04-13 | The Boeing Company | Structural apparatus and design to prevent oil can movement of webs in aircraft pressure bulkheads |
| US20140151500A1 (en) * | 2012-11-30 | 2014-06-05 | Airbus Operations S.A.S. | Device for intermediate fastening between an aircraft fuselage and an aircraft landing gear |
| CN110140007A (en) * | 2017-12-07 | 2019-08-16 | 深圳市一窗科技有限责任公司 | Lamp installation component |
| CN209410346U (en) * | 2018-11-26 | 2019-09-20 | 北京金朋达航空科技有限公司 | Bleed radiator |
-
2019
- 2019-12-27 CN CN201911379826.2A patent/CN113044228A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1981002718A1 (en) * | 1980-03-21 | 1981-10-01 | Boeing Co | Method and apparatus for vibration damping structural elements |
| US5893534A (en) * | 1995-12-22 | 1999-04-13 | The Boeing Company | Structural apparatus and design to prevent oil can movement of webs in aircraft pressure bulkheads |
| US20140151500A1 (en) * | 2012-11-30 | 2014-06-05 | Airbus Operations S.A.S. | Device for intermediate fastening between an aircraft fuselage and an aircraft landing gear |
| CN110140007A (en) * | 2017-12-07 | 2019-08-16 | 深圳市一窗科技有限责任公司 | Lamp installation component |
| CN209410346U (en) * | 2018-11-26 | 2019-09-20 | 北京金朋达航空科技有限公司 | Bleed radiator |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20210629 |
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| WD01 | Invention patent application deemed withdrawn after publication |