CN108820245B - Solar airplane wing surface covering film tensioning and mounting equipment - Google Patents
Solar airplane wing surface covering film tensioning and mounting equipment Download PDFInfo
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- CN108820245B CN108820245B CN201810673153.0A CN201810673153A CN108820245B CN 108820245 B CN108820245 B CN 108820245B CN 201810673153 A CN201810673153 A CN 201810673153A CN 108820245 B CN108820245 B CN 108820245B
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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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Abstract
A solar airplane wing surface covering film tensioning installation device comprises a base, a tensioning shaft screw mechanism, a mold supporting frame, a mold, a wing box moving lifting table and a moving shaft screw mechanism; the tensioning shaft screw mechanisms are arranged in two groups and are transversely and coaxially arranged on the base; the die is correspondingly connected with the tensioning shaft screw rod mechanism through the die supporting frame and can transversely move oppositely or oppositely under the driving of the tensioning shaft screw rod mechanism; the movable shaft screw mechanism is longitudinally installed and fixed on the base, and the wing box movable lifting platform is connected with the movable shaft screw mechanism and can move back and forth under the driving of the movable shaft screw mechanism. The invention can realize the reliable and fast assembly of the film material on the wing box under the condition of certain pretightening force, thereby realizing the light-weight manufacture of the wing section and ensuring that the surface of the finished product wing meets the established aerodynamic force action requirement.
Description
Technical Field
The invention belongs to the technical field of manufacturing of aviation aircrafts, relates to an aircraft airfoil production device, and particularly relates to solar aircraft airfoil covering film tensioning and mounting equipment.
Background
Lightweight is one of the key indicators for high-altitude solar aircraft design. The wing with the film covering structure has the characteristics of small wing load, light weight and the like, and is very suitable for the design and manufacture of solar aircrafts.
The Chinese invention patent ZL2014104858238 discloses a gridding solar wing structure, and the technical scheme is that rigid solar cells are packaged into a flexible film in a light weight mode and are installed on curved wing surfaces of an airplane as a covering film, so that the structural weight of the solar airplane is effectively reduced, and the load capacity is improved. However, this patent discloses only a method of manufacturing the flexible skin and does not disclose a specific method of mounting the flexible skin on the curved airfoil of an aircraft. Because the wings are continuously deformed under the action of constantly changing external force and internal stress in the flying process, if the flexible covering film is installed by adopting the same process as the traditional metal hard covering film, the flexible covering film is inevitably deformed under the influence of the external force in the flying process, and the given airfoil surface shape cannot be maintained.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides solar airplane wing surface covering film tensioning and mounting equipment which is simple in structure, quick and convenient to operate, high in automation degree, capable of tensioning and mounting a covering film and capable of accurately controlling the tensioning force.
In order to achieve the purpose, the invention adopts the following technical scheme:
a solar airplane wing surface covering film tensioning installation device comprises a base 1, a tensioning shaft screw mechanism 2, a mold supporting frame 3, a mold 4, a wing box moving lifting platform 5 and a moving shaft screw mechanism 6;
the tensioning shaft screw mechanisms 2 are arranged in two groups and transversely and coaxially arranged on the base 1, and a space is reserved between the two groups of tensioning shaft screw mechanisms 2; the two groups of dies 4 are respectively and correspondingly connected with one group of tensioning shaft screw mechanisms 2 through die supporting frames 3 and can transversely move oppositely or oppositely under the driving of the tensioning shaft screw mechanisms 2;
the movable shaft screw mechanism 6 is longitudinally installed and fixed on the base 1, is positioned between the two groups of tensioning shaft screw mechanisms 2 and is perpendicular to a straight line where the two groups of tensioning shaft screw mechanisms 2 are positioned; the wing box moving lifting platform 5 is connected with a moving shaft screw mechanism 6 and can move back and forth under the driving of the moving shaft screw mechanism 6.
Further, the mesa of base 1 is rectangle planar structure, tensioning axle lead screw mechanism 2, removal axle lead screw mechanism 6 are all installed between two parties on the mesa of base 1.
Further, the base 1 is also provided with a guide rail 11 for limiting the horizontal movement of the wing box moving and lifting platform 5 only in the front-back direction.
Further, the tensioning shaft screw mechanism 2 comprises a tensioning screw 21 and a tensioning screw control box 22, and the die supporting frame 3 is mounted on the tensioning screw 21 of the tensioning shaft screw mechanism 2; the tensioning screw control box 22 drives the tensioning screw 21 to rotate, so that the die supporting frame 3 is driven to move horizontally.
Further, the moving-shaft screw mechanism 6 includes a moving screw 61 and a moving screw control box 62; the wing box moving lifting platform 5 is arranged on a moving screw rod 61; the moving screw control box 62 drives the moving screw 61 to rotate, thereby driving the wing box moving lift 5 to move horizontally back and forth.
Further, the wing box moving lifting platform 5 comprises a platform 51 for installing and fixing the wing box, a stepping jacking cylinder 52 and a support frame 53; the lower end of the support frame 53 is arranged on a movable screw 61 of the movable shaft screw mechanism 6, and the upper end of the support frame is fixedly connected with the platform 51; the support frame 53 can drive the platform 51 to horizontally move back and forth under the driving of the movable shaft screw mechanism 6; step-by-step jacking cylinder 52 upper end and platform 51 fixed connection can drive the vertical rising of platform 51 or descend, step-by-step jacking cylinder 52 lower extreme is connected with the guide rail 11 of base 1, and under the restriction of guide rail 11, advances the synchronous front and back horizontal motion of formula jacking cylinder 52 and platform 51.
Further, still include central control computer 8, central control computer 8 is connected with tensioning lead screw control box 22 of tensioning axle lead screw mechanism 2, the removal lead screw control box 62 that removes axle lead screw mechanism 6 and the marching type jacking cylinder 52 electricity of wing box removal elevating platform 5 respectively through cable 7 to control the course of work that tensioning axle lead screw mechanism 2, remove axle lead screw mechanism 6 and wing box removed elevating platform 5.
Further, the tension shaft screw mechanism 2, the moving shaft screw mechanism 6 and the stepping jacking cylinder 52 of the wing box moving lifting table 5 are all provided with locking devices; the joint of the cable 7 is a pluggable structure.
Further, the mold 4 comprises an upper mold and a lower mold, wherein the upper mold and the lower mold are fixedly connected through bolts, and clamping and fixing of the covering film to be laid are achieved.
Further, the base 1 is a fixed or movable cast iron platform or a cement platform.
The solar airplane wing surface covering film tensioning and mounting equipment comprises a tensioning shaft screw mechanism, a wing box moving lifting platform, a solar airplane wing surface covering film tensioning and mounting equipment, a mould and a mould, wherein the tensioning shaft screw mechanism is used for pre-tensioning a covering film to be laid, which is clamped and fixed on the mould; in the period, the central control computer is used for carrying out automatic and quantitative control on the tensioning shaft screw rod mechanism, the wing box moving lifting platform and the moving shaft screw rod mechanism, so that the installation efficiency and quality can be greatly improved. The invention can realize the reliable and fast assembly of the film material on the wing box under the condition of certain pretightening force, thereby realizing the light-weight manufacture of the wing section and ensuring that the surface of the finished product wing meets the established aerodynamic force action requirement.
Drawings
FIG. 1 is a front view of a solar aircraft airfoil film tensioning installation of embodiment 1;
FIG. 2 is a top view of a solar aircraft airfoil film tensioning installation of embodiment 1.
Detailed Description
The following further describes an embodiment of the solar airplane airfoil covering film tensioning installation device in combination with the attached drawings 1 and 2. The solar aircraft airfoil film tensioning installation apparatus of the present invention is not limited to the description of the embodiments below.
Example 1:
the embodiment shows a specific structure of a solar airplane airfoil covering film tensioning installation device, and as shown in fig. 1 and fig. 2, the solar airplane airfoil covering film tensioning installation device comprises a base 1, a tensioning shaft screw mechanism 2, a mold supporting frame 3, a mold 4, a wing box moving lifting platform 5, a moving shaft screw mechanism 6, a central control computer 8 and a cable 7. The dimensional parameters of the above-mentioned components are matched to the dimensions of the wing box to be machined.
The table top of the base 1 is preferably a rectangular structure and can be a cast iron platform or a cement platform. The base 1 mainly has the functions of installing and fixing the tension shaft screw mechanism 2, the wing box moving lifting platform 5 and the moving shaft screw mechanism 6 and ensuring that the reference positions of all components are kept unchanged. Meanwhile, the base 1 is further provided with a guide rail for limiting the movement of the wing box moving and lifting platform 5 in a predetermined direction (i.e., the front-back horizontal direction).
Tensioning shaft screw mechanisms 2 are provided with two groups, transversely and coaxially mounted on the base 1, and an interval is reserved between the two groups of tensioning shaft screw mechanisms 2. The tension shaft screw mechanism 2 includes a tension screw 21 and a tension screw control box 22. The tensioning screw 21 is used for adjusting the relative position of the die supporting frame 3 so as to adjust the die 4 to a specified position, and a preset film covering pretightening force is formed; the tensioning screw control box 22 is mainly used for controlling the rotation angle of the screw 21 so as to drive and adjust the die supporting frame 3 to a specified position, and the tensioning screw control box 22 is controlled by the central control computer 8. The die supporting frame 3 is arranged on a tensioning screw 21 of the tensioning shaft screw mechanism 2; the tensioning screw control box 22 drives the tensioning screw 21 to rotate, so that the die supporting frame 3 is driven to move horizontally.
The die 4 is provided with two sets of dies, is correspondingly connected with a set of tensioning shaft screw mechanism 2 through the die supporting frame 3 respectively, and can transversely move relatively or move oppositely under the driving of the tensioning shaft screw mechanism 2. The mold 4 comprises an upper mold and a lower mold, wherein the upper mold and the lower mold are fixedly connected through bolts, and clamping and fixing of a covering film to be laid are achieved.
The movable shaft screw mechanism 6 is longitudinally installed and fixed on the base 1, is positioned between the two groups of tensioning shaft screw mechanisms 2 and is perpendicular to a straight line where the two groups of tensioning shaft screw mechanisms 2 are positioned; the wing box moving lifting platform 5 is connected with a moving shaft screw mechanism 6 and can move back and forth under the driving of the moving shaft screw mechanism 6.
The wing box moving lifting platform 5 comprises a platform 51 for installing and fixing the wing box, a stepping jacking cylinder 52 and a support frame 53. Wherein the platform 51 is mainly used for mounting a fixed wing box; the stepping jacking cylinder 52 is mainly used for driving the platform 51 to ascend or descend and is controlled by the central control computer 8; the support frame is mainly used for being connected with a movable lead screw 61 of the movable shaft lead screw mechanism 6, and the platform is driven to move in a given direction by the movable lead screw 61. Specifically, the lower end of the support frame 53 is mounted on a movable lead screw 61 of the movable shaft lead screw mechanism 6, and the upper end is fixedly connected with the platform 51; the support frame 53 can drive the platform 51 to horizontally move back and forth under the driving of the movable shaft screw mechanism 6; step-by-step jacking cylinder 52 upper end and platform 51 fixed connection can drive the vertical rising of platform 51 or descend, step-by-step jacking cylinder 52 lower extreme is connected with the guide rail 11 of base 1, and under the restriction of guide rail 11, advances the synchronous front and back horizontal motion of formula jacking cylinder 52 and platform 51.
The moving-shaft screw mechanism 6 includes a moving screw 61 and a moving-screw control box 62. The movable lead screw 61 is mainly used for driving the support frame 53 connected with the movable lead screw to move in a given direction, the movable lead screw control box 62 is mainly used for controlling the rotating angle of the movable lead screw 61 so as to drive the support frame 53 to a specified position, and the movable lead screw control box 62 is controlled by the central control computer 8. Specifically, the wing box moving lifting platform 5 is mounted on a moving screw 61; the moving screw control box 62 drives the moving screw 61 to rotate, thereby driving the wing box moving lift 5 to move horizontally back and forth.
The central control computer 8 is respectively electrically connected with the tensioning screw control box 22 of the tensioning screw mechanism 2, the moving screw control box 62 of the moving screw mechanism 6 and the stepping jacking cylinder 52 of the wing box moving lifting table 5 through cables 7, and controls the working processes of the tensioning screw mechanism 2, the moving screw mechanism 6 and the wing box moving lifting table 5.
As a preferred embodiment, the step-by-step jacking cylinders 52 of the tensioning shaft screw mechanism 2, the moving shaft screw mechanism 6 and the wing box moving lifting table 5 are all provided with locking devices, the joints of the cables 7 are of a pluggable structure, and the purpose is to separate mechanical parts in the device from the central control computer 8, so that the mechanical parts can be integrally placed in an oven for baking and the like, and the central control computer 8 and multiple sets of mechanical parts are matched for use, thereby saving the cost.
The solar airplane wing surface film covering tensioning installation equipment provided by the embodiment can greatly reduce the difficulty of manual operation and improve the production efficiency; secondly, the quality and the precision of the manufactured wing sections are effectively ensured, and thirdly, the serialized design and the application can be realized aiming at the same type of products.
Example 2:
this embodiment provides a specific use method of the solar aircraft airfoil covering film tensioning and mounting device described in embodiment 1, including the following steps:
1. the to-be-laid film covering material is clamped on the mold 4, a central control computer 8 sends an instruction to a tensioning screw control box 22 through a cable 7, and a tensioning shaft screw mechanism is controlled to drive the mold support frame 3 to move towards two sides to implement tensioning.
2. The wing box to be covered with the film is fixedly installed on the platform 51 of the wing box moving lifting platform 5, and if the covering film and the wing box are connected in a gluing mode, gluing treatment can be performed on the wing box.
3. The central control computer 8 sends an instruction to the movable lead screw control box 62 through the cable 7, and drives the support frame 53 connected with the movable lead screw to move back and forth on the horizontal plane.
4. After the wing box reaches the preset horizontal position, the central control computer 8 sends an instruction to the stepping jacking cylinder 52 through the cable 7 to drive the stepping jacking cylinder 52 to vertically jack the platform 51 to the preset position.
5. If the connection is carried out in a cementing mode, in order to ensure the connection reliability, the tensioning shaft screw mechanism 2, the moving shaft screw mechanism 6 and the stepping jacking cylinder 52 of the wing box moving lifting platform 5 can be locked, then the plug of the cable 7 is pulled down to remove the central control computer 8 and the cable 7, finally the cable 7 is pushed into an oven, the temperature is raised and cured according to the process requirements of the established adhesive, and the installation and fixation of the covering film and the wing box are realized. If the connection and the fixation are realized by adopting a bolt or rivet connection mode, the installation and the fixation processes such as bolt connection or rivet connection can be carried out at the moment.
6. After the procedure of installing and fixing the covering film and the wing box is completed, the central control computer 8 is controlled to enable the tensioning shaft screw rod mechanism 2 to move in the opposite direction so as to unload the covering film. If the connection is made by gluing, it is necessary to first cool and connect the cable 7 and the central control computer 8 again.
7. And cutting the redundant covering film outside the wing box, performing necessary trimming and shape modification, and then taking down the assembled wing box.
8. The central control computer 8 controls the tension shaft screw mechanism 2, the moving shaft screw mechanism 6, and the step-by-step jack cylinder 52 to return to the initial positions.
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.
Claims (5)
1. The utility model provides a solar energy aircraft airfoil covers membrane tensioning erection equipment which characterized in that: the device comprises a base, a tensioning shaft screw rod mechanism, a mould supporting frame, a mould, a wing box moving lifting platform and a moving shaft screw rod mechanism;
the tensioning shaft screw mechanisms are arranged in two groups and transversely and coaxially arranged on the base, and a space is reserved between the two groups of tensioning shaft screw mechanisms; the two groups of dies are respectively and correspondingly connected with one group of tensioning shaft screw mechanisms through die supporting frames and can transversely move oppositely or oppositely under the driving of the tensioning shaft screw mechanisms;
the movable shaft screw mechanisms are longitudinally arranged and fixed on the base, are positioned between the two groups of tensioning shaft screw mechanisms and are perpendicular to the straight line where the two groups of tensioning shaft screw mechanisms are positioned; the wing box moving lifting platform is connected with the moving shaft screw mechanism and can move back and forth under the driving of the moving shaft screw mechanism;
the table-board of the base is of a rectangular plane structure, and the tensioning shaft screw mechanism and the moving shaft screw mechanism are both arranged on the table-board of the base in the middle;
the base is also provided with a guide rail for limiting the horizontal movement of the wing box moving lifting platform only in the front-back direction;
the die supporting frame is arranged on the tensioning screw rod of the tensioning shaft screw mechanism; the tensioning screw control box drives the tensioning screw to rotate, so that the die supporting frame is driven to transversely and horizontally move;
the movable shaft screw mechanism comprises a movable screw and a movable screw control box; the wing box moving lifting platform is arranged on the moving lead screw; the movable lead screw control box drives the movable lead screw to rotate, so that the wing box movable lifting platform is driven to horizontally move back and forth;
the wing box moving lifting platform comprises a platform for installing and fixing the wing box, a stepping jacking cylinder and a support frame; the lower end of the support frame is arranged on a movable screw rod of the movable shaft screw rod mechanism, and the upper end of the support frame is fixedly connected with the platform; the support frame can drive the platform to horizontally move back and forth under the driving of the movable shaft screw mechanism; the upper end of the stepping jacking cylinder is fixedly connected with the platform and can drive the platform to vertically ascend or descend, the lower end of the stepping jacking cylinder is connected with the guide rail of the base, and the stepping jacking cylinder and the platform synchronously move horizontally back and forth under the limitation of the guide rail.
2. The solar aircraft airfoil film tensioning installation according to claim 1 wherein: the central control computer is respectively electrically connected with a tensioning screw control box of the tensioning screw mechanism, a movable screw control box of the movable screw mechanism and a stepping jacking cylinder of the wing box movable lifting platform through cables, and controls the working process of the tensioning screw mechanism, the movable screw mechanism and the wing box movable lifting platform.
3. The solar aircraft airfoil film tensioning installation according to claim 2 wherein: the tensioning shaft screw mechanism, the movable shaft screw mechanism and the stepping jacking air cylinder of the wing box movable lifting table are all provided with locking devices; the joint of the cable is a pluggable structure.
4. The solar aircraft airfoil film tensioning installation according to claim 3 wherein: the mould comprises an upper mould and a lower mould, wherein the upper mould and the lower mould are fixedly connected through bolts, and clamping and fixing of a covering film to be laid are achieved.
5. The solar aircraft airfoil film tensioning installation according to claim 4 wherein: the base is a fixed or movable cast iron platform or a cement platform.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810673153.0A CN108820245B (en) | 2018-06-26 | 2018-06-26 | Solar airplane wing surface covering film tensioning and mounting equipment |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810673153.0A CN108820245B (en) | 2018-06-26 | 2018-06-26 | Solar airplane wing surface covering film tensioning and mounting equipment |
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| Publication Number | Publication Date |
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| CN108820245A CN108820245A (en) | 2018-11-16 |
| CN108820245B true CN108820245B (en) | 2022-04-15 |
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| CN201810673153.0A Active CN108820245B (en) | 2018-06-26 | 2018-06-26 | Solar airplane wing surface covering film tensioning and mounting equipment |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110549620B (en) * | 2019-09-16 | 2022-12-09 | 杭州聚纳电子科技有限公司 | Drawing of patterns paper tightening fixing device that cooperation 3D printer bottom plate used |
| CN111177964B (en) * | 2019-12-25 | 2023-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Balance adjusting method and equipment for jacking state of airplane |
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| CN104210647A (en) * | 2014-09-22 | 2014-12-17 | 北京航空航天大学 | Wing structure-meshed solar wing design and development scheme |
| CN103043227B (en) * | 2013-01-17 | 2014-12-31 | 中国人民解放军国防科学技术大学 | Film covering device and method of wing structure surface |
| CN106379516A (en) * | 2016-09-14 | 2017-02-08 | 中国电子科技集团公司第四十八研究所 | Solar-powered airplane wing and manufacturing method thereof |
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2018
- 2018-06-26 CN CN201810673153.0A patent/CN108820245B/en active Active
Patent Citations (6)
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| CN202388489U (en) * | 2011-12-06 | 2012-08-22 | 华侨大学 | Novel displacement working table |
| CN202728614U (en) * | 2012-08-24 | 2013-02-13 | 福州华映视讯有限公司 | Semi-automatic mouth-shaped glue adhering equipment |
| CN103043227B (en) * | 2013-01-17 | 2014-12-31 | 中国人民解放军国防科学技术大学 | Film covering device and method of wing structure surface |
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