CN204297131U - A kind of composite material structural member quick position installation car - Google Patents
A kind of composite material structural member quick position installation car Download PDFInfo
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- CN204297131U CN204297131U CN201420684496.4U CN201420684496U CN204297131U CN 204297131 U CN204297131 U CN 204297131U CN 201420684496 U CN201420684496 U CN 201420684496U CN 204297131 U CN204297131 U CN 204297131U
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- 239000002131 composite material Substances 0.000 title claims abstract description 39
- 238000009434 installation Methods 0.000 title claims abstract description 18
- 238000000034 method Methods 0.000 abstract description 6
- 238000012423 maintenance Methods 0.000 abstract description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 150000001875 compounds Chemical group 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
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Abstract
本实用新型提供一种复合材料结构件快速定位安装车,包括车架(1)和夹持部(2),在机体上预先安装若干个机体定位器(3),在所述夹持部(2)的上端安装有若干个与所述机体定位器(3)对应的复合功能定位器(4);本安装车解决了飞机部件装配过程中大型、异型复合材料结构件的快速定位、可靠稳定安装和拆卸问题,缩短飞机生产研制周期,提高地面和外场维护反应速度。
The utility model provides a fast positioning and installation vehicle for composite material structural parts, which includes a vehicle frame (1) and a clamping part (2), and several body locators (3) are pre-installed on the body, and the 2) The upper end is equipped with a plurality of composite function locators (4) corresponding to the body locator (3); this installation vehicle solves the problem of rapid positioning, reliable and stable positioning of large and special-shaped composite material structures in the assembly process of aircraft components Installation and disassembly problems, shorten the aircraft production and development cycle, and improve the response speed of ground and field maintenance.
Description
技术领域 technical field
本实用新型属于飞机装配技术领域,特别涉及一种复合材料结构件快速定位安装车。 The utility model belongs to the technical field of aircraft assembly, in particular to a vehicle for fast positioning and installation of composite material structural parts.
背景技术 Background technique
传统飞机多为半硬壳式结构,其结构件由铝合金材料的蒙皮、框缘、长桁铆接装配而成,其装配、定位的工艺装备型架设计已趋于成熟。但随着复合材料成型工艺方法的日趋进步,在飞机结构尤其是大型甚至异型结构件中的应用日益广泛。由于复合材料结构件与铝合金结构件的结构以及材料特性差异,需在飞机总装配后采用专用工艺装备进行安装。 Traditional aircraft are mostly semi-monocoque structures, and their structural parts are assembled by riveting aluminum alloy skins, frame edges, and long trusses. The assembly and positioning process and equipment frame design has become mature. However, with the advancement of composite material forming technology, it is widely used in aircraft structures, especially large and even special-shaped structural parts. Due to the differences in structure and material properties between composite material structural parts and aluminum alloy structural parts, it is necessary to use special process equipment for installation after the general assembly of the aircraft.
由于复合材料结构件体积较大、外形复杂、重量远较金属结构件重,现有复合材料结构件的安装是采用划线定位结,通过专用安装车保型支撑结构件进行安装。该专用安装车通过卡板内型对结构件外形贴合支撑,无稳定可靠的机械连接,导致其在安装车内不易稳定、安装调整难度较高,在安装过程中由于安装需要通过安装车对结构件姿态进行调整,致使结构件易变形、定位不准确、装配质量不稳定的问题。 Due to the large volume, complex shape and much heavier weight than metal structural parts of composite material structural parts, the installation of existing composite material structural parts is to use marking and positioning knots, and install them through special installation car-shaped supporting structural parts. The special installation vehicle fits and supports the shape of the structural parts through the inner type of the pallet, and there is no stable and reliable mechanical connection, which makes it difficult to be stable in the installation vehicle and difficult to install and adjust. Adjusting the posture of structural parts leads to problems such as easy deformation of structural parts, inaccurate positioning, and unstable assembly quality.
实用新型内容 Utility model content
本实用新型的目的是:解决原复合材料结构件安装车无法准确定位、稳定可靠安装和拆卸结构件的问题。 The purpose of the utility model is to solve the problem that the original composite material structural member installation vehicle cannot be accurately positioned, and the structural member can be stably and reliably installed and disassembled.
为解决上述技术问题,本实用新型技术方案提供一种复合材料结构件快速定位安装车,包括车架1和夹持部2,在机体上预先安装若干个机体定位器3,在所述夹持部2的上端安装有若干个与所述机体定位器3对应的复合功能定位器4,所述机体定位器3包括一个带孔的单耳,所述复合功能定位器4包括定位单耳401、夹持单耳402、吊装单耳403、底座404,所述定位单耳401有一个与所述机体定位器3的单耳的孔相配合的孔,所述夹持单耳402通过孔配合与所述夹持部2的上端螺栓连接,所述吊装单耳403位于复合功能定位器4的上部有一个吊装孔,所述底座404有与所述复合材料结构件上的预埋螺纹孔相对应的孔。 In order to solve the above-mentioned technical problems, the technical solution of the utility model provides a fast positioning and installation vehicle for composite material structural parts, which includes a vehicle frame 1 and a clamping part 2, and several body positioners 3 are pre-installed on the body, and in the clamping The upper end of the part 2 is equipped with several composite function locators 4 corresponding to the body locator 3, the body locator 3 includes a single ear with a hole, and the composite function locator 4 includes a positioning single ear 401, Clamping single ear 402, hoisting single ear 403, base 404, the positioning single ear 401 has a hole matching with the hole of the single ear of the body positioner 3, and the clamping single ear 402 is matched with the hole through the hole The upper end of the clamping part 2 is connected by bolts, the hoisting lug 403 is located on the upper part of the composite function locator 4 and has a hoisting hole, and the base 404 has a threaded hole corresponding to the embedded thread hole on the composite material structure hole.
与现有安装车相比,本实用新型的优点是:本安装车解决了飞机部件装配过程中大型、异型复合材料结构件的快速定位、可靠稳定安装和拆卸问题,缩短飞机生产研制周期,提高地面和外场维护反应速度。 Compared with the existing installation vehicle, the utility model has the advantages that: the installation vehicle solves the problems of rapid positioning, reliable and stable installation and disassembly of large and special-shaped composite material structural parts in the assembly process of aircraft components, shortens the production and development cycle of aircraft, and improves Ground and outfield maintenance response speed.
附图说明 Description of drawings
下面对本实用新型附图进行说明: The accompanying drawings of the utility model are described below:
图1复合材料结构件快速定位安装车示意图; Fig. 1 Schematic diagram of rapid positioning and installation vehicle for composite structural parts;
图2复合功能定位器示意图。 Figure 2. Schematic diagram of the composite function locator.
具体实施方式 Detailed ways
下面结合附图与具体实施方式对本实用新型作进一步详细描述: Below in conjunction with accompanying drawing and specific embodiment the utility model is described in further detail:
A,依据工装图样进行加工机体定位器3和复合功能定位器4,保证机体定位器3的基准孔和基准面与复合功能定位器4的定位单耳401的定位孔与定位面相对空间位置协调; A. Process the body locator 3 and composite function locator 4 according to the tooling pattern to ensure that the reference hole and reference surface of the body locator 3 are coordinated with the positioning hole and the positioning surface of the positioning single ear 401 of the composite function locator 4 ;
B,通过飞机结构装配工装在机体上准确安装机体定位器3; B. Accurately install the body positioner 3 on the body through the aircraft structure assembly tool;
C,通过复合材料结构件成型工装在复合材料结构件上准确制出与复合功能定位器连接孔相对应的预埋螺纹孔,采用螺栓将复合功能定位器4与复合材料结构件连接; C. Accurately make pre-embedded threaded holes corresponding to the connecting holes of the composite function locator on the composite material structure through the molding tooling of the composite material structure, and use bolts to connect the composite function locator 4 to the composite structure;
D,使用吊挂通过复合功能定位器4上吊装单耳403的吊钩孔,将复合材料结构件吊装在安装车架1上的夹持部2上,采用螺栓连接将夹持单耳402与夹持部2相连; D, use the hanging hook hole to hoist the single ear 403 on the composite function locator 4, hoist the composite material structure on the clamping part 2 on the installation frame 1, and use bolt connection to clamp the single ear 402 and The clamping parts 2 are connected;
E,调整安装车架1,将复合功能定位器4上定位单耳401的定位面与机体定位器3的基准面相贴合,将定位单耳401的定位孔与机体定位器3的基准孔同心,并采用螺栓连接; E, adjust and install the frame 1, fit the positioning surface of the positioning ear 401 on the composite function positioner 4 with the reference plane of the body positioner 3, and make the positioning hole of the positioning ear 401 concentric with the reference hole of the body positioner 3 , and bolted connection;
F,完成复合材料结构件与机体的紧固件的制孔、连接等工作; F, complete the hole making and connection of the composite material structural parts and the fasteners of the body;
G,拆除复合功能定位器4上定位单耳401与机体定位器3的连接螺栓,将复合功能定位器4上定位单耳401与机体定位器3相脱离; G, remove the connecting bolts connecting the positioning lug 401 on the composite function locator 4 and the body locator 3, and separate the positioning lug 401 on the composite function locator 4 from the body locator 3;
H,拆除复合功能定位器4上夹持单耳402与夹持部2的相连螺栓,将夹持部2与复合功能定位器4上夹持单耳402相脱离; H, remove the connecting bolts that clamp the single ear 402 and the clamping part 2 on the compound function locator 4, and separate the clamping part 2 from the clamping single ear 402 on the compound function locator 4;
I,撤离安装车架1及夹持部2; I, evacuate and install the frame 1 and the clamping part 2;
J,拆除复合功能定位器4上底座404与复合材料结构件相连的螺栓,拆除机体定位器3与机体相连的连接件; J, remove the bolts connecting the upper base 404 of the composite function locator 4 and the composite material structural member, and remove the connecting piece connecting the body locator 3 and the body;
K,拆除复合功能定位器4和机体定位器3,并完成连接件的连接。 K, remove the composite function locator 4 and the body locator 3, and complete the connection of the connectors.
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CN201420684496.4U CN204297131U (en) | 2014-11-14 | 2014-11-14 | A kind of composite material structural member quick position installation car |
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Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109080850A (en) * | 2018-07-25 | 2018-12-25 | 陕西飞机工业(集团)有限公司 | A kind of installation adjusting method of Large aircraft landing gear nacelle |
CN110239421A (en) * | 2019-05-17 | 2019-09-17 | 陕西飞机工业(集团)有限公司 | A kind of the transport overturning tooling and transportation resources of the part turnover posture adjustment of aircraft ultra-wide |
CN116902217A (en) * | 2023-09-13 | 2023-10-20 | 辽宁华天航空科技股份有限公司 | Symmetrical positioning assembly and method based on aircraft composite structural member |
-
2014
- 2014-11-14 CN CN201420684496.4U patent/CN204297131U/en not_active Expired - Lifetime
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109080850A (en) * | 2018-07-25 | 2018-12-25 | 陕西飞机工业(集团)有限公司 | A kind of installation adjusting method of Large aircraft landing gear nacelle |
CN109080850B (en) * | 2018-07-25 | 2022-02-11 | 陕西飞机工业(集团)有限公司 | Installation and adjustment method for large aircraft landing gear nacelle |
CN110239421A (en) * | 2019-05-17 | 2019-09-17 | 陕西飞机工业(集团)有限公司 | A kind of the transport overturning tooling and transportation resources of the part turnover posture adjustment of aircraft ultra-wide |
CN116902217A (en) * | 2023-09-13 | 2023-10-20 | 辽宁华天航空科技股份有限公司 | Symmetrical positioning assembly and method based on aircraft composite structural member |
CN116902217B (en) * | 2023-09-13 | 2023-12-12 | 辽宁华天航空科技股份有限公司 | Symmetrical positioning assembly and method based on aircraft composite structural member |
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Granted publication date: 20150429 |