CN205150216U - Unmanned aerial vehicle's foam presss from both sides core wing - Google Patents

Abstract

The utility model discloses an unmanned aerial vehicle's foam presss from both sides core wing, including last covering (2), lower covering (1), upper surface glued membrane (3), foam laminboard layer (4), lower surface glued membrane (5) and spar (6), go up covering (2) through upper surface glued membrane (3) and foam laminboard layer (4), spar (6) fixed connection, lower covering (1) through lower surface glued membrane (5) and foam laminboard layer (4), spar (6) fixed connection, all fills foam laminboard layer (4) under, in the cavity between covering (1) and spar (6) at last covering (2), spar (6) are fixed through splicing with foam laminboard layer (4). The utility model discloses a wing structure is simple, the light is high -efficient, can improve the structure efficiency of unmanned aerial vehicle airfoil, improves the the stiffness and the shock resistance of structure, and more easy to carry out's manufacture craft and more controllable manufacturing cost make the structure have better design nature and wholeness simultaneously.

Description

A foam sandwich wing for a small drone

technical field

The utility model relates to a drone wing, in particular to a foam sandwich wing of a small drone.

Background technique

Existing UAV wings usually use traditional beam structure airfoils and honeycomb sandwich structure airfoils. The traditional beam-type airfoil structure mainly relies on the spar to carry and maintain the structural rigidity. The structure is simple and reliable. However, for small and thin airfoil UAV wings, the height of the spar is too small, the utilization rate of structural materials is low, and the strength and stiffness characteristics are poor. Honeycomb sandwich structure airfoil, with thick skin as the main load-bearing dimensional structure, can ensure the strength characteristics and take into account the structural stability. However, for small UAV wings, the manufacturing process requirements are high, and the structural performance is difficult. accomplish.

The airfoils of small UAVs mostly adopt thin airfoils, and have strict requirements on the structural weight. Several typical structures have poor applicability to small thin airfoils, and are difficult to process, making it difficult to achieve lightweight structures.

Utility model content

The technical problem to be solved by the utility model is to provide a foam sandwich wing structure suitable for small unmanned aerial vehicles with simple structure, light weight and high efficiency, which can improve the structural efficiency of the airfoil of small unmanned aerial vehicles and improve the structure The overall rigidity and impact resistance, the manufacturing process that is easier to implement and the manufacturing cost are more controllable, and at the same time, the structure has better design and integrity.

The utility model comprises the following technical solutions:

A foam sandwich wing of a small unmanned aerial vehicle, comprising an upper skin, a lower skin, an upper surface adhesive film, a foam sandwich layer, a lower surface adhesive film and a spar; the upper skin is passed through the upper surface adhesive film and the foam The sandwich layer and the spar are fixedly connected, the lower skin is fixedly connected with the foam sandwich layer and the spar through the lower surface adhesive film, and the cavity between the upper skin, the lower skin and the spar is completely filled with the foam core layer, and the spar and the foam sandwich layer are fixed by bonding.

The upper skin and the lower skin are composite fiber laminated skins, and the foam sandwich layer is closed-cell rigid foam plastic material.

The upper skin and the lower skin are laminated with carbon fiber, aramid fiber or glass fiber material.

The upper skin and the lower skin are mixed layers of carbon fiber, aramid fiber and glass fiber materials.

The upper skin and the lower skin are laminated with aramid fiber, the foam sandwich layer is polyurethane foam, and the material of the spar is aramid fiber.

The thicknesses of the upper and lower skins are both 0.2 mm.

The opening part of the airfoil is directly processed on the foam sandwich layer, and the upper and lower skins are laid according to the shape of the opening.

The mounting holes of the airfoil joint part are directly processed on the foam sandwich layer, and the connecting parts are pre-embedded in the foam sandwich layer.

The foam sandwich layer is polyurethane foam.

The spar is made of carbon fiber, aramid laminated structure or high-strength plastic material.

Compared with the prior art, the utility model has the following advantages:

The utility model adopts a full-cavity filled foam sandwich airfoil structure, and all the cavities between the wing skin and the spar are filled with foam materials, and the foam sandwich layer is glued to the skin and other contact parts. The airfoil structure supported by a full-size foam sandwich has a high yield limit and good impact resistance, and is compatible with the stall landing method commonly used by small UAVs, especially suitable for small UAVs with relatively small airfoil thickness. man-machine. The foam core layer is easier to realize different airfoil configurations, and is convenient for the setting of airfoil openings and interfaces, and has good designability. The upper and lower skins, foam core layers and beams are connected by adhesive bonding, with a large connection area and strong structural integrity. By adopting the above structure, the structure of the utility model is simpler, easy to process, and easy to control the quality and cost.

Description of drawings

Fig. 1 is the schematic diagram of the first structural form of the foam sandwich wing;

Fig. 2 is a schematic diagram of an airfoil opening structure;

Fig. 3 is the schematic diagram of the second structural form of the foam sandwich wing;

Fig. 4 is a schematic diagram of the mold on the lower surface of the wing;

Fig. 5 is a schematic diagram of the upper surface mold of the wing.

detailed description

Below just in conjunction with accompanying drawing, the utility model is further introduced.

As shown in Figure 1, the foam sandwich airfoil of the small unmanned aerial vehicle of the present utility model comprises upper skin 2, lower skin 1, upper surface adhesive film 3, foam sandwich layer 4, lower surface adhesive film 5 and The spar 6; the upper skin 2 is fixedly connected with the foam sandwich layer 4 and the spar 6 through the upper surface adhesive film 3, and the lower skin 1 is fixedly connected with the foam sandwich layer 4 and the spar 6 through the lower surface adhesive film 5, The cavity between the upper skin 2 , the lower skin 1 and the spar 6 is completely filled with the foam sandwich layer 4 , and the spar 6 and the foam sandwich layer 4 are fixed by bonding. The front and rear edges of the wing can be paved with reinforced layers according to the actual working conditions to strengthen the strength of the front and rear edges. The installation opening required for the airfoil installation equipment can be directly processed on the foam sandwich layer, and the skin fiber layup is laid in accordance with the shape of the opening. As shown in Figure 2, the rudder surface 22 is controlled by the steering gear installed in the opening 21. The opening 21 is directly processed and formed when the foam core layer is prepared, and the skin fiber layup is laid on the surface, and the reinforcement layup can be laid on the edge of the opening as required. .

The upper skin 2 and the lower skin 1 are laminated skins made of composite material with high specific strength and specific stiffness, so that the airfoil structure has good mechanical properties. Individual materials such as carbon fiber, glass fiber and aramid fiber or mixed layers can be selected, which can effectively improve the strength of the structure. The filling core layer can be made of polyurethane foam and other closed-cell rigid foam materials, which are glued to the skin, beams, ribs and other structures to improve the overall rigidity and impact resistance of the structure.

The spar 6 adopts carbon fiber, aramid fiber laminated structure or high-strength plastic material. The layout of the spar 6, as well as the specific shape and cross-section parameter design, etc., can be changed according to requirements, or other internal structural forms can be selected. As shown in Figure 3, another structural form of the foam sandwich wing adopts a double-beam structure inside, including the front beam 7 and the rear beam 6, and adopts different cross-sectional shapes, and its connection with other components is the same as that shown in Figure 1. The single beam structure is the same.

The airfoil structure has good mechanical properties, and the structure is light and efficient. The skin and beam structure made of composite materials, and the foam-filled core layer all have good mechanical properties and low density, and the material utilization rate is high. The upper and lower skins are connected by a foam sandwich layer, and the lower skin under tension can support the upper skin under compression through the core layer, so the structure has a higher yield limit. At the same time, the foam sandwich layer can also effectively improve the stiffness and impact resistance of the airfoil structure, and can be well compatible with the stall landing method commonly used by small UAVs.

The airfoil has a simple structure, good processing technology, and controllable processing cost and production cycle. The preparation of the foam sandwich layer and the laying of the fiber skin are easy to implement, and the processing quality is easy to control. It is suitable for the production and application requirements of small UAVs with a weight below 10kg.

The airfoil structure has good designability, the openings and interfaces of the airfoil can be designed directly for the reinforced core layer, and the composite fiber skin can be directly laid according to the shape of the core layer, without complicated opening reinforcement measures. The structural integrity is easy to ensure, and the internal reinforcement structure is reliably connected to the overall structure.

Example

In this embodiment, the upper skin 2 and the lower skin 1 are laminated with aramid fiber, the foam sandwich layer 4 is made of polyurethane foam, and the spar 6 is made of aramid fiber, wherein the lower skin 1, the upper skin 2 and the The foam sandwich layer 4 and the spar 6 are glued and connected by glue films 3 and 5, and the glue films are preferably epoxy resin glue. The spar 6 is an I-shaped beam. The manufacturing process of the wing is as follows:

On the lower skin mold shown in FIG. 4 , starting from the film surface, the first layer of the lower surface is a single-layer aramid fiber cloth lower skin 1 with a thickness of 0.2 mm.

The second layer is the lower surface adhesive film 5, which is used for bonding the airfoil skin with the foam sandwich layer 4 and the spar 6. The foam sandwich layer 4 is connected with parts such as the spar 6 inside the airfoil through adhesive bonding. The foam sandwich layer 4 (including internal components such as the spar 6 ) is laid on the third layer, and glued to the lower skin 1 through the lower surface adhesive film 5 .

The upper surface adhesive film 3 is laid on the fourth layer for bonding the foam sandwich layer 4 and the upper skin 2 .

The upper skin 2 is preferably aramid fiber fabric, laid on the fifth layer, with a thickness of 0.2mm. The adhesive film 3 on the upper surface is glued to the foam sandwich layer 4 .

The mold on the upper surface and the mold on the lower surface as shown in Figure 5 are pressurized and solidified for molding.

The airfoil shape of the lower surface of the wing can be guaranteed by the mold shown in Figure 4, and the shape of the upper surface airfoil can be guaranteed by the foam sandwich structure processed by numerical control.

The wing manufacturing of this structural form can be realized by vacuum bag forming process, and each layer is laid layer by layer from the film surface (the internal structure such as the foam sandwich layer 4 and the spar 6 can be connected by glue first), and the upper and lower molds Close the mold and pressurize, and solidify and form at one time.

The descriptions in the above specific embodiments are the preferred solutions of the present utility model, and are not intended to limit the protection scope of the present utility model.

Parts not described in detail in the utility model belong to the common knowledge of those skilled in the art.

Claims (10)

1. the foam core wing of a SUAV (small unmanned aerial vehicle), it is characterized in that, comprise covering (2), lower covering (1), upper surface glued membrane (3), foam sandwich laminate (4), lower surface glued membrane (5) and spar (6); Upper covering (2) is fixedly connected with foam sandwich laminate (4), spar (6) by upper surface glued membrane (3), lower covering (1) is fixedly connected with foam sandwich laminate (4), spar (6) by lower surface glued membrane (5), whole filled and process laminboard layer (4) in upper covering (2), cavity between lower covering (1) and spar (6), described spar (6) is fixed by glueing joint with foam sandwich laminate (4).

2. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 1, it is characterized in that: described upper covering and lower covering are composite fiber laying covering, foam sandwich laminate (4) is closed pore rigid foamed plastic materials.

3. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 1, is characterized in that: described upper covering and lower covering are carbon fiber, aramid fiber or glass fiber material laying.

4. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 1, is characterized in that: described upper covering and lower covering are the mixing laying of carbon fiber, aramid fiber and glass fiber material.

5. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 1, it is characterized in that: described upper covering and lower covering adopt aramid fiber laying, described foam sandwich laminate (4) is Polyurethane foam, and the material of described spar (6) is aramid fiber.

6. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 4, is characterized in that: the thickness of described upper and lower covering is 0.2mm.

7. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 1, is characterized in that: aerofoil opening portion is directly in the upper processing of foam sandwich laminate (4), and upper and lower covering adapts to opening shape and lays.

8. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 1, is characterized in that: aerofoil blank area mounting hole is directly in the upper processing of foam sandwich laminate (4), and attaching parts is embedded in foam sandwich laminate (4).

9. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 1, is characterized in that: foam sandwich laminate (4) is Polyurethane foam.

10. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 1, is characterized in that: spar (6) adopts carbon fiber, aramid fiber laminate structures or strong plastic material.