Mold for producing ultra-light aircraft wing

Abstract

The invention discloses an ultra-light aircraft wing production mold which comprises a mounting frame, supporting legs are arranged at the bottom of the mounting frame, the mounting frame comprises four beams arranged in a rectangular shape and supporting columns arranged in the vertical direction, the two beams on the same side are connected through the two supporting columns, and the bottoms of the two beams on the lower side are connected through the supporting legs. A plurality of templates are arranged in the mounting frame in the length direction of the mounting frame and used for controlling production errors of wings, the templates comprise a main template and an auxiliary template, and the main template is provided with a wing mold groove with one side open. According to the grinding tool, the node positions can be marked during design, the sizes of the positioning plate and the clamping plate are designed, and the template can be quickly mounted to the corresponding node positions through the clamping plate, so that production and machining of the wing are assisted, it is ensured that wing production meets design specification requirements, wing errors do not exceed the design range, and the grinding tool is simple in structure and convenient to use.

Description

Technical Field

[0001] The invention relates to the technical field of ultralight aircraft, in particular to a mold for producing an ultralight aircraft wing. Background Art

[0002] Ultralight aircraft are the lightest type of aircraft classified by weight. They have the characteristics of low altitude, low speed, stability and safety. They have simple structure, light weight, low price, easy operation and convenient maintenance. They can be widely used in agriculture, forestry, animal husbandry, exploration, aerial photography, aviation sports and tourism.

[0003] The fixed wing is one of the important parts of an ultralight aircraft, which is installed on the fuselage. Its main function is to generate lift to support the aircraft flying in the air. At present, the precision error of the ultralight aircraft wing needs to be controlled during production and processing to ensure that the wing meets the production design specification requirements. Therefore, the present application provides a mold for the production of ultralight aircraft wings to assist in the production and preparation of ultralight aircraft wings. Summary of the invention

[0004] The technical problem to be solved by the present invention is to overcome the existing defects and provide a mold for the production of ultralight aircraft wings. The node positions can be marked when designing the tooling, and the sizes of the positioning plates and the clamping plates can be designed. The template can be quickly installed to the corresponding node positions through the clamping plates, thereby assisting the production and processing of the wings, ensuring that the wing production meets the design specification requirements, and the wing error does not exceed the design range. The structure is simple and easy to use, which can effectively solve the problems in the background technology.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a mold for producing ultralight aircraft wings, comprising a mounting frame, a support foot is provided at the bottom of the mounting frame, the mounting frame comprises four rectangular beams and vertically arranged pillars, and two beams on the same side are connected by two pillars, and the bottoms of the two beams on the lower side are connected by the support foot, a plurality of templates are arranged inside the mounting frame along its length direction for controlling the production error of the wing, the template comprises a main template and a sub-template, the main template is provided with a wing mold groove with one side open, and the sub-template is installed at the opening of the wing mold groove.

[0006] As a preferred technical solution of the present invention, fences are provided at both upper and lower ends of the template, and both upper and lower ends of the main template are wrapped by the fences.

[0007] As a preferred technical solution of the present invention, eleven nodes for installing templates are marked on the beam, and the eleven templates are installed at the corresponding nodes on the beam through fences.

[0008] As a preferred technical solution of the present invention, the distances between the center points of two adjacent templates from left to right are 360, 290, 420, 310, 375, 350, 380, 200, 540, and 375, respectively, in mm. The height of the template is 1531 mm and the width of the template is 600 mm.

[0009] As a preferred technical solution of the present invention, a clamping plate is provided on one side of the fence corresponding to the crossbeam, and the clamping plate is clamped on the outer side of the crossbeam.

[0010] As a preferred technical solution of the present invention, two symmetrically arranged positioning plates are provided on the side of the beam, and the cross-section of the track composed of the two positioning plates and the beam is an isosceles trapezoid. The track is divided into several node segments for installing the template, and the groove between the clamping plates is adapted to one of the nodes of the track for automatically positioning the template of the node.

[0011] As a preferred technical solution of the present invention, the positioning plate is a magnetic plate, and the clamping plate can be magnetically adsorbed by the magnetic plate.

[0012] As a preferred technical solution of the present invention, a positioning frame is provided on one side of the interior of the mounting frame, and evenly distributed laser rangefinders are provided on the side of the positioning frame. Perforations are provided on the side of the template corresponding to the laser rangefinder, and a positioning plate capable of blocking the perforations is movably inserted on the side of the template corresponding to the perforations.

[0013] As a preferred technical solution of the present invention, there are no less than four laser rangefinders.

[0014] As a preferred technical solution of the present invention, the side of the positioning plate close to the laser rangefinder is flush with the middle longitudinal interface of the template.

[0015] Compared with the prior art, the present invention has the following beneficial effects:

[0016] The tooling for producing ultralight aircraft wings exemplified in the present invention can mark node positions when designing the tooling, and design the sizes of the positioning plates and the clamping plates. The templates can be quickly installed at the corresponding node positions through the clamping plates, thereby assisting the production and processing of the wings, ensuring that the wing production meets the design specification requirements, and the wing error does not exceed the design range. The structure is simple and easy to use. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the structure of the present invention;

[0018] Figure 2 It is a schematic diagram of the matching structure of the crossbeam and the clamping plate in the present invention;

[0019] Figure 3 for Figure 2Schematic top view of .

[0020] In the figure: 1 support leg, 2 pillars, 3 fence, 31 plywood, 31 perforation, 33 positioning plate, 4 beam, 41 positioning plate, 5 template, 6 positioning frame, 61 laser rangefinder. DETAILED DESCRIPTION

[0021] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0022] Embodiment 1:

[0023] See also Figure 1-3 The present invention provides a technical solution: a mold for producing ultralight aircraft wings, including a mounting frame, a support leg 1 is provided at the bottom of the mounting frame, the mounting frame includes four rectangular beams 4 and pillars 2 arranged in the vertical direction, and two beams 4 on the same side are connected by two pillars 2, and the bottoms of the two beams 4 on the lower side are connected by the support leg 1, and a plurality of templates 5 are arranged inside the mounting frame along its length direction for controlling the production error of the wing. The template 5 includes a main template and a sub-template, and the main template is provided with a wing mold groove with one side open, and the sub-template is installed at the opening of the wing mold groove. The mold is opened according to the shape of the wing, so that the mold grooves of the templates 5 at different parts are gradually changed, and then the wing plate is restricted and fixed by the mold groove, so as to produce a wing that meets the design specifications.

[0024] Furthermore, fences 3 are provided at both upper and lower ends of the template 5, and both upper and lower ends of the main template are wrapped by the fences 3.

[0025] Furthermore, eleven nodes for installing the templates 5 are marked on the beam 4 , and the eleven templates 5 are installed at the corresponding nodes on the beam 4 through the fence 3 .

[0026] Furthermore, the position of template 5 is controlled according to the size of the wing and the shape change of the mold groove of template 5, as follows: the distances between the center points of two adjacent templates 5 from left to right are 360, 290, 420, 310, 375, 350, 380, 200, 540, 375, respectively, in mm. The height of template 5 is 1531 mm, and the width of template 5 is 600 mm.

[0027] Furthermore, a clamping plate 31 is provided on one side of the fence 3 corresponding to the cross beam 4 , and the clamping plate 31 is clamped on the outer side of the cross beam 4 .

[0028] Furthermore, two symmetrically arranged positioning plates 41 are provided on the side of the beam 4, and the cross-section of the track formed by the two positioning plates 41 and the beam 4 is an isosceles trapezoid. The track is divided into several node segments for installing the template 5, and the grooves between the clamps 31 are adapted to one of the nodes of the track for automatically positioning the template 5 at the node.

[0029] Furthermore, the positioning plate 41 is a magnetic plate, and the clamp 31 can be magnetically adsorbed by the magnetic plate. The clamp 31 is clamped on the narrower end of the track, and then the clamp 31 is slid along the track. The clamp 31 drives the template 5 to move. When the clamp 31 cannot move, it means that the template 5 has moved to the corresponding node position.

[0030] Embodiment 2:

[0031] In order to better position the template 5 and detect whether the template 5 is deformed during the wing production process, the present embodiment provides the following technical solutions: a positioning frame 6 is provided on one side of the interior of the mounting frame, and evenly distributed laser rangefinders 61 are provided on the side of the positioning frame 6. A through hole 31 is provided on the side corresponding to the template 5 and the laser rangefinder 61, and a positioning plate 33 capable of blocking the through hole 31 is movably inserted on the side corresponding to the template 5 and the through hole 31. The laser rangefinder 61 detects the position of the corresponding template 5 by detecting the distance between the laser rangefinder 61 and the positioning plate 33, thereby determining whether the template 5 is installed in place; when the template 5 is installed in place, the positioning plate 33 is pulled out, and the laser detects through the through hole 31 whether the next wooden board 5 is installed in place.

[0032] Furthermore, there are no less than four laser rangefinders 61, and the four laser rangefinders 61 work simultaneously. When the template 5 is installed tilted, the distances detected by the four laser rangefinders 61 are different. During the processing, when the template 5 is deformed or tilted, the laser emitted by the laser rangefinder 61 cannot pass through the perforation 31, thereby detecting the distance change, and the template 5 needs to be adjusted.

[0033] Furthermore, the side of the positioning plate 33 close to the laser rangefinder 61 is flush with the middle longitudinal interface of the template 5, which can ensure that the distance detected by the positioning plate 33 is the corresponding node position of the template 5.

[0034] The present invention can mark the node position when designing the tooling, and design the dimensions of the positioning plate 41 and the clamping plate 31, and can quickly install the template 5 to the corresponding node position through the clamping plate 31, thereby assisting the production and processing of the wing, ensuring that the wing production meets the design specification requirements, and the wing error does not exceed the design range. The structure is simple and easy to use.

[0035] The undisclosed parts in the present invention are all prior art, and their specific structures, materials and working principles are not described in detail. Although the embodiments of the present invention have been shown and described, it is understood by those skilled in the art that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the attached claims and their equivalents.

Claims

1. A mold for producing an ultralight aircraft wing, comprising a mounting frame, the bottom of the mounting frame is provided with a support foot (1), characterized in that: The mounting frame comprises four cross beams (4) arranged in a rectangular shape and pillars (2) arranged in a vertical direction, and two cross beams (4) on the same side are connected by two pillars (2), and the bottoms of the two cross beams (4) on the lower side are connected by supporting feet (1). A plurality of templates (5) are arranged inside the mounting frame along its length direction for controlling the production error of the wing, and the templates (5) comprise a main template and a sub-template, and the main template is provided with a wing mold groove with one side open, and the sub-template is installed at the opening of the wing mold groove.

2. The tooling for producing ultralight aircraft wings according to claim 1, characterized in that: The upper and lower ends of the template (5) are both provided with fences (3), and the upper and lower ends of the main template are both wrapped by the fences (3).

3. The tooling for producing ultralight aircraft wings according to claim 2, characterized in that: Eleven nodes for installing templates (5) are marked on the crossbeam (4), and the eleven templates (5) are installed at corresponding nodes on the crossbeam (4) through the fence (3).

4. The tooling for producing ultralight aircraft wings according to claim 3, characterized in that: The distances between the center points of two adjacent templates (5) from left to right are 360, 290, 420, 310, 375, 350, 380, 200, 540, 375, in units of mm, respectively. The height of the template (5) is 1531 mm, and the width of the template (5) is 600 mm.

5. The tooling for producing ultralight aircraft wings according to claim 4, characterized in that: A clamping plate (31) is provided on one side of the fence (3) corresponding to the crossbeam (4), and the clamping plate (31) is clamped on the outside of the crossbeam (4).

6. The tooling for producing ultralight aircraft wings according to claim 5, characterized in that: Two symmetrically arranged positioning plates (41) are provided on the side of the crossbeam (4), and the cross section of the track formed by the two positioning plates (41) and the crossbeam (4) is an isosceles trapezoid. The track is divided into a plurality of node sections for installing the template (5), and the groove between the clamping plates (31) is adapted to one of the nodes of the track for automatically positioning the template (5) at the node.

7. The tooling for producing ultralight aircraft wings according to claim 6, characterized in that: The positioning plate (41) is a magnetic plate, and the clamping plate (31) can be magnetically adsorbed by the magnetic plate.

8. The tooling for producing ultralight aircraft wings according to claim 1, characterized in that: A positioning frame (6) is provided on one side of the interior of the mounting frame, and laser rangefinders (61) are evenly distributed on the side of the positioning frame (6). A through hole (31) is provided on the side of the template (5) corresponding to the laser rangefinder (61), and a positioning plate (33) capable of blocking the through hole (31) is movably inserted on the side of the template (5) corresponding to the through hole (31).

9. The tooling for producing ultralight aircraft wings according to claim 8, characterized in that: There are no less than four laser rangefinders (61).

10. The tooling for producing ultralight aircraft wings according to claim 8, characterized in that: The side of the positioning plate (33) close to the laser rangefinder (61) is flush with the middle longitudinal interface of the template (5).

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