CN214875531U - Aerocar wing beam and aerocar wing - Google Patents

Abstract

The application discloses a flying automobile wing beam and a wing, wherein the flying automobile wing beam is connected with a flying automobile body through a wing root; the wing root comprises an outer layer structure and an inlay structure, and the inlay structure is arranged inside the outer layer structure; the inlay structure comprises a first insert, a second insert, a third insert and a fourth insert which are sequentially bonded end to end; the material density interval of the first embedded block and the third embedded block is 30 kg/cubic meter to 60 kg/cubic meter; the material density interval of the second embedded block and the fourth embedded block is 1400-1600 kg/m; the distance between the fourth embedded block and the wingtip is greater than that between the first embedded block and the wingtip; mounting holes are formed in the wing root corresponding to the second embedded block and the fourth embedded block; the mounting hole is used for connecting the flying automobile wing beam with the flying automobile body. The aerocar wing beam and the aerocar wing provided by the utility model have light weight and low assembly difficulty; after the wing root is locally enhanced, the torsion resistance is enhanced.

Description

Aerocar wing beam and aerocar wing

Technical Field

The application relates to the technical field of automobile parts, in particular to a wing beam and a wing of an aerocar.

Background

The aerocar is a general aircraft developed in recent years, the takeoff weight of the aerocar varies from hundreds of kilograms to several tons, the configuration of the aerocar is various, and the layout of a power system is also five-door and eight-door, such as a multi-rotor type, a ducted fan type, a tilting rotor type, a multi-lift propeller type and a single-push propeller type mixed layout. Taking TF-2A as an example, the flight control system is developed based on a multi-propeller and single-propeller layout (a wing with a fixed wing and a lift propeller mechanism), pure clean energy is used, the function of vertical take-off and landing can be realized under the condition that a special runway is not needed, and after a certain height is reached, fixed wing mode flight is realized under the pushing of propellers. Limited by the current battery energy storage level, the flight in the fixed wing mode can reduce the consumption of a power supply and increase the flight mileage. Based on the configuration, the TF-2A needs to be additionally provided with a support rod mechanism on the wing structure, is used for installing a propeller lifting motor and provides power for the vertical take-off and landing stage of the whole machine. In addition, a horizontal tail and a vertical tail are arranged at the rear ends of the inner side stay bars of the left wing and the right wing, so that pitching, yawing and other actions of the airplane can be controlled in a cruising stage. The wing structure of the traditional navigation aircraft has no additional similar stay bar structure, the main load of the wing is the bending moment borne by the wing in the flying stage, and the load is gradually increased from the wing tip to the wing root. However, the TF-2A wing structure is different from a traditional fixed wing aircraft in load form due to the fact that an additional mechanism is added, and besides the unexpected effect of bearing bending moment, the TF-2A wing structure can also bear the torque caused by the imbalance of the lift force generated by the lifting oar in the vertical and pitching stages.

The traditional navigation aircraft structural part mainly comprises metal materials in the early stage, and along with the development of material technology, the proportion of composite materials in the navigation aircraft structural part is larger and can reach more than 90%. Early wing spar parts were made of metal materials, and as the main load-bearing structure of an aircraft, they generally had several forms: i-shaped, C-shaped, Z-shaped, etc. When in manufacturing, the parts (corner pieces, independent upper and lower flanges, webs) and the like are connected together by using bolts or rivets, and then the flanges and the upper and lower skins are connected together by using rivet beams to serve as a main bearing structure of the airplane. The beam structure has the advantages of multiple required parts, multiple fasteners, high weight and long assembly period. With the development of the technology, composite material beams appear in the field of navigation airplanes, and similar to metal beams, the composite material beams can also be divided into I shapes, C shapes, Z shapes and the like. The whole beam is made of composite materials, is formed by adopting the process methods of vacuum bag pressing, autoclave pressing and the like, and is connected with the upper skin and the lower skin through the gluing process. After the composite material beam is processed, the wing beam is connected with the machine body through the metal joint, or a mounting hole is processed at the root part of the wing beam and is fixedly connected with a mounting hole of the machine body bearing beam through a bolt, so that the effect of transferring load is achieved.

After load evaluation, TF-2A finds that the traditional composite beam structure of the navigation aircraft can not meet the strength requirement of the aircraft under all load working conditions, and the structure of the beam needs to be optimally designed.

SUMMERY OF THE UTILITY MODEL

Aiming at the technical problems in the background technology, the application provides a wing beam and a wing of an aerocar, which have light weight and low assembly difficulty; after the wing root is locally enhanced, the torsion resistance is enhanced. The application is realized by the following technical scheme:

a flying car wing beam comprises a wing root and a wing tip, wherein the wing root and the wing tip are respectively positioned at two ends of the flying car wing beam; the flying automobile wing beam is connected with the flying automobile body through the wing root; the wing root includes an outer layer structure and an inlay structure disposed inside the outer layer structure; the inlay structure comprises a first insert, a second insert, a third insert and a fourth insert which are sequentially bonded end to end; the material density interval of the first insert and the third insert is 30-60 kg/m; the material density interval of the second insert and the fourth insert is 1400-1600 kg/m; the distance between the fourth embedded block and the wingtip is larger than that between the first embedded block and the wingtip; mounting holes are formed in the wing root at positions corresponding to the second embedded block and the fourth embedded block; the mounting hole is used for connecting the flying automobile wing beam with the flying automobile body.

Further, the inner wall of the mounting hole is provided with a lining.

Further, the first insert and the third insert are foam plate members; the second and fourth inserts are carbon fiber laminate sheets.

Further, the inlay structure further comprises a first cover layer and a second cover layer; the first covering layer covers one side surfaces of the first embedded block, the second embedded block, the third embedded block and the fourth embedded block; the second covering layer covers the other side surfaces of the first insert, the second insert, the third insert and the fourth insert.

Further, the inlay structure is glued to the inner wall of the outer structure.

Further, the outer layer structure comprises a first flange and a second flange which are oppositely arranged, and a web structure which is perpendicular to the first flange; the relative positions of the first bead and the second bead have equal width and thickness; the space formed by the first bead, the second bead and the web structure is used for accommodating the inlay structure.

Further, the thickness of the wing root is 53 mm to 57 mm.

Further, the web has a thickness of 5 to 7 millimeters; the inlay structure has a thickness of 41 to 45 millimeters; one side of the inlay structure clings to the web plate; the part of the other side of the inlay structure, which is lower than the first bead, is a carbon fiber layer; one side of the carbon fiber layer away from the inlay structure is flush with the first bead.

Further, the width and thickness of the first cap decrease in a direction from the root to the tip.

The utility model also discloses a hovercar wing, the hovercar wing include above-mentioned arbitrary scheme hovercar wing beam.

By adopting the technical scheme, the flying automobile wing beam and the wing provided by the utility model are filled with the first embedded block, the second embedded block, the third embedded block and the fourth embedded block at the root part of the wing; the material density interval of the first insert and the third insert is 30-60 kg/cubic meter, the material density interval of the second insert and the fourth insert is 1400-1600 kg/cubic meter, the torsional rigidity is increased, and the purpose of reducing weight is achieved due to the fact that light materials are adopted for filling. And mounting holes for connecting the aerocar wing beam with the aerocar body are formed in the wing root at positions corresponding to the second embedded block and the fourth embedded block. Through the optimization, the aerocar wing beam and the aerocar wing provided by the utility model have light weight and low assembly difficulty; after the wing root is locally enhanced, the torsion resistance is enhanced.

Drawings

In order to more clearly illustrate the technical solutions of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without inventive effort.

FIG. 1 is a schematic structural diagram of a wing spar of an aerocar provided in an embodiment of the present application;

FIG. 2 is a cross-sectional view of the location of the bolt mounting holes in the root region of FIG. 1;

FIG. 3 is an enlarged view of a portion of area A of FIG. 1;

in the figure: 1-wing root, 11-outer layer structure, 111-first flange, 112-second flange, 113-web structure, 12-inlay structure, 121-first insert, 122-first insert, 123-third insert, 124-fourth insert, 13-mounting hole, 2-wing tip, 3-lining.

Detailed Description

The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

Reference herein to "one embodiment" or "an embodiment" means that a particular feature, structure, or characteristic may be included in at least one implementation of the present application. In the description of the present application, it is to be understood that the terms "upper", "lower", "top", "bottom", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are only for convenience in describing the present application and simplifying the description, and do not indicate or imply that the referred devices or elements must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.

As shown in fig. 1 and fig. 2, an embodiment of the present invention discloses a flying car wing beam, which includes a wing root 1 and a wing tip 2, where the wing root 1 and the wing tip 2 are respectively located at two ends of the flying car wing beam; the flight vehicle wing beam is connected with the flight vehicle body through the wing root 1; the wing root 1 comprises an outer layer structure 11 and an inlay structure 12, the inlay structure 12 being arranged inside the outer layer structure 11; the inlay structure 12 comprises a first insert 121, a first insert 122, a third insert 123 and a fourth insert 124 which are sequentially bonded end to end; the material density interval of the first insert 121 and the third insert 123 is 30 kg/m to 60 kg/m; the material density of the first and fourth inserts 122, 124 may range from 1400 kg/m to 1600 kg/m; the fourth slug 124 is at a greater distance from the wing tip 2 than the first slug 121 is at the wing tip 2; mounting holes 13 are formed in the wing root 1 at positions corresponding to the first insert 122 and the fourth insert 124; the mounting hole 13 is used for connecting the flying automobile wing beam with the flying automobile body.

The embodiment of the utility model provides a aerocar wing beam, through filling first abaculus 121, first abaculus 122, third abaculus 123 and fourth abaculus 124 in wing root 1 portion; the material density interval of the first insert 121 and the third insert 123 is 30 kg/m to 60 kg/m; the material density range of the first insert 122 and the fourth insert 124 is 1400-1600 kg/m, which not only increases the torsional rigidity, but also achieves the purpose of reducing the weight due to the adoption of light material filling. The wing root 1 is provided with a mounting hole 13 corresponding to the first insert 122 and the fourth insert 124 for connecting the wing beam of the hovercar with the hovercar body. Through the optimization, the aerocar wing beam and the aerocar wing provided by the utility model have light weight and low assembly difficulty; after the wing root 1 is locally enhanced, the torsion resistance is enhanced.

In another embodiment of the present invention, the inner wall of the mounting hole 13 is provided with a bushing 3, the bushing 3 is embedded, and then the automobile wing beam is connected with the body by using the matching of the bolt and the mounting hole 13; the first insert 121 and the third insert 123 are foam plate members; the first insert 122 and the fourth insert 124 are carbon fiber laminated plates, so that the insertion of the bushing 3 enhances the extrusion strength of the mounting hole 13, and overcomes the disadvantage that the composite material plate (formed by filling the first insert 121, the first insert 122, the third insert 123 and the fourth insert 124 in the wing root 1) cannot bear a large extrusion load.

In another embodiment of the present invention, the inlay structure 12 further comprises a first cover layer and a second cover layer; the first covering layer covers one side surfaces of the first insert 121, the first insert 122, the third insert 123 and the fourth insert 124; the second cover layer covers the other side surfaces of the first insert 121, the first insert 122, the third insert 123, and the fourth insert 124.

In another embodiment of the present invention, to improve the stability of the inlay structure 12, the inlay structure 12 is glued to the inner wall of the outer structure 11.

In another embodiment of the present invention, the outer layer structure 11 comprises a first rim 111 and a second rim 112 disposed opposite to each other, and a web structure 113 perpendicular to the first rim 111, and the relative positions of the first rim 111 and the second rim 112 have the same width and thickness; the space formed by the first bead 111, the second bead 112, and the web structure 113 is used to accommodate the inlay structure 12.

In another embodiment of the present invention, the thickness of the wing root 1 may be 53 mm to 57 mm; the web 113 may have a thickness of 5 mm to 7 mm; the inlay structure 12 may have a thickness of 41 to 45 millimeters; one side of the inlay structure 12 rests against the web 113; the other side of the inlay structure 12 below the first bead 111 is a carbon fiber layer; the side of the carbon fiber layer remote from the inlay structure 12 is flush with the first bead 111.

In another embodiment of the present invention, the width and thickness of the first cap 111 decrease progressively along the direction from the wing root 1 to the wing tip 2.

The embodiment of the utility model provides a still provide a hovercar wing, hovercar wing includes any one of the above-mentioned embodiments hovercar wing beam.

The foregoing is a preferred embodiment of the present application, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the principle of the present application, and these modifications and decorations are also regarded as the protection scope of the present application.

Claims (10)

1. The flying automobile wing beam is characterized by comprising a wing root and a wing tip, wherein the wing root and the wing tip are respectively positioned at two ends of the flying automobile wing beam;

the flying automobile wing beam is connected with the flying automobile body through the wing root;

the wing root includes an outer layer structure and an inlay structure disposed inside the outer layer structure;

the inlay structure comprises a first insert, a second insert, a third insert and a fourth insert which are sequentially bonded end to end;

the material density interval of the first insert and the third insert is 30-60 kg/m;

the material density interval of the second insert and the fourth insert is 1400-1600 kg/m;

the distance between the fourth embedded block and the wingtip is larger than that between the first embedded block and the wingtip;

mounting holes are formed in the wing root at positions corresponding to the second embedded block and the fourth embedded block;

the mounting hole is used for connecting the flying automobile wing beam with the flying automobile body.

2. An auto wing spar according to claim 1,

and a lining is arranged on the inner wall of the mounting hole.

3. An auto wing spar according to claim 1,

the first insert and the third insert are foam plate pieces;

the second and fourth inserts are carbon fiber laminate sheets.

4. An auto wing spar according to claim 3,

the inlay structure further comprises a first cover layer and a second cover layer;

the first covering layer covers one side surfaces of the first embedded block, the second embedded block, the third embedded block and the fourth embedded block;

the second covering layer covers the other side surfaces of the first insert, the second insert, the third insert and the fourth insert.

5. An auto wing spar according to claim 1,

the inlay structure is glued to the inner wall of the outer structure.

6. An auto wing spar according to claim 5,

the wing root layer structure comprises a first edge strip and a second edge strip which are oppositely arranged, and a web structure which is perpendicular to the first edge strip;

the relative positions of the first bead and the second bead have equal width and thickness;

the space formed by the first bead, the second bead and the web structure is used for accommodating the inlay structure.

7. An auto wing spar according to claim 6,

the thickness of the wing root is 53 mm to 57 mm.

8. An aerocar spar according to claim 7, wherein the web has a thickness of from 5 to 7 mm

The inlay structure has a thickness of 41 to 45 millimeters;

one side of the inlay structure clings to the web plate;

the part of the other side of the inlay structure, which is lower than the first bead, is a carbon fiber layer;

one side of the carbon fiber layer away from the inlay structure is flush with the first bead.

9. An auto wing spar according to claim 8,

the width and thickness of the first cap decrease in a direction from the root to the tip.

10. A hovercar wing comprising a hovercar spar as claimed in any one of claims 1 to 9.

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