Empennage structure of unmanned aerial vehicle

Abstract

The utility model discloses an empennage structure of an unmanned aerial vehicle, which relates to the field of unmanned aerial vehicles, solves the problem that the existing traditional steel material is heavy and easily affects the flight of the unmanned aerial vehicle, and adopts the following scheme: the empennage structure comprises an empennage consisting of a vertical tail and a horizontal tail; a vertical fin skin is assembled on the outer wall of the vertical fin, a vertical fin front beam and a vertical fin rear beam are arranged on the front side and the rear side of the vertical fin, a vertical fin tail end rib is assembled at the bottom end of the vertical fin through a vertical fin rib # 1, and a vertical fin frame is fixedly installed at the top end of the vertical fin. According to the empennage structure of the unmanned aerial vehicle, the horizontal tail and vertical tail structures formed through foam filling and compression molding are lighter than traditional metal structures, the overall weight of the unmanned aerial vehicle can be reduced, meanwhile, the composite carbon fiber fabric skin and the foam filling material can provide good structural strength, various mechanical requirements in the flight process can be met, and the unmanned aerial vehicle can be widely applied to the field of aircrafts. And therefore, the flight effect can be ensured, and the flight energy consumption can be reduced.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane technical field, concretely is a kind of unmanned plane tail wing structure. BACKGROUND

[0002] The tail wing structure of aircraft is the key component for adjusting its attitude and direction. Although the traditional unmanned plane tail wing structure is stable and reliable, its production, assembly and maintenance process is relatively complex. Therefore, a low-cost tail wing structure that can be mass-produced has become a focus of research and development.

[0003] After searching, in the application book with patent application number 202122111924.7, a kind of unmanned plane tail wing structure convenient for steering is disclosed, including connecting plate, direction plate is provided on the one end upper of connecting plate, the both sides of the one end of connecting plate are all fixedly connected with lifting plate, the one end fixedly connected with servo motor in connecting plate away from lifting plate, lifting plate is all provided with No. gear at the one end close to direction plate, compared with prior art, the beneficial effects of the utility model include: through servo motor control fixed block moves, cooperation No. electric telescopic rod controls the steering of fixed block, to control No. gear rotation, control the steering of tail wing and the steering of unmanned plane, to realize the steering adjustment of unmanned plane;Through the steering adjustment mechanism away from tail wing structure, the weight of tail wing is greatly reduced, to avoid that tail wing is too heavy to affect the flight of unmanned plane, affect the steering of tail wing and unmanned plane;When No. gear rotates, control corresponding No. gear to rotate, steering adjustment is carried out to auxiliary plate.

[0004] The setting of each structure in the above application file tail wing can achieve auxiliary adjustment effect, but the structure in the prior art and the above file has the following problems:

[0005] 1. Difficult to maintain: the traditional unmanned plane tail wing structure is usually composed of multiple complex components, which needs to be disassembled and reassembled during maintenance, which is time-consuming and easy to cause damage or incorrect installation;

[0006] 2. High manufacturing cost: the traditional unmanned plane tail wing structure is made of metal material, which needs complex machining and assembly process, resulting in high manufacturing cost;

[0007] 3. Poor durability: the traditional unmanned plane tail wing structure is easily affected by corrosion, fatigue and other factors, resulting in short service life and frequent replacement and maintenance;

[0008] 4. Too heavy: the traditional unmanned plane tail wing structure is made of metal material, which is heavy, increasing the overall weight of the aircraft, affecting fuel efficiency and flight performance.

[0009] Therefore, we propose a kind of unmanned plane tail wing structure. Utility model content

[0010] In view of the deficiencies of the prior art, the unmanned aerial vehicle tail wing structure solves the problem that the existing conventional steel material is heavy and easily affects the flight of the unmanned aerial vehicle.

[0011] To achieve the above object, the utility model discloses the following technical schemes to realize: an unmanned aerial vehicle tail wing structure, comprising a tail wing, the tail wing is composed of a vertical tail and a horizontal tail,

[0012] The outer wall of the vertical tail is equipped with a vertical tail skin, the front and rear sides of the vertical tail are provided with a vertical tail front beam and a vertical tail rear beam, the bottom end of the vertical tail is equipped with a vertical tail end rib through a vertical tail rib 1, and the top end of the vertical tail is fixedly installed with a vertical tail frame.

[0013] The horizontal tail is sleeved with a horizontal tail skin, the top and bottom sides of the horizontal tail are provided with a horizontal tail rear beam and a horizontal tail front beam, the tail end of the horizontal tail is provided with a horizontal tail connector 1 and a horizontal tail connector 2 opposite in position, and a horizontal tail end rib is arranged between the horizontal tail connector 1 and the horizontal tail connector 2.

[0014] As a preferred scheme of the utility model, the vertical tail skin and the horizontal tail skin in the vertical tail and the horizontal tail are all made of composite material carbon fiber fabric skin material;

[0015] Among them, each component in the horizontal tail and the vertical tail is made by mold pressing, which ensures the manufacturing effect of each component.

[0016] As a preferred scheme of the utility model, the vertical tail front beam and the vertical tail rear beam in the vertical tail and the horizontal tail skin and the horizontal tail front beam are all C-shaped cross-section structures;

[0017] Among them, the setting of the structure shape of the vertical tail front beam and the vertical tail rear beam and the horizontal tail skin and the horizontal tail front beam can ensure the rigidity and structure shape of the horizontal tail and the vertical tail as a whole.

[0018] As a preferred scheme of the utility model, foams are pre-buried in the vertical tail and the horizontal tail, the foams and the vertical tail skin, the vertical tail front beam, the vertical tail rear beam, the vertical tail rib 1, the vertical tail end rib and the vertical tail frame in the vertical tail are glued by J-133C structural glue, and the foams and the horizontal tail skin, the horizontal tail rear beam, the horizontal tail front beam, the horizontal tail rib, the horizontal tail end rib and the horizontal tail connector 2 in the horizontal tail are glued by J-133C structural glue.

[0019] Among them, the J-133C structural glue is composed of modified epoxy resin and modified amine curing agent, and is glued by room temperature curing and heating curing.

[0020] As a preferred scheme of the utility model, each vertical tail skin and horizontal tail skin in the vertical tail and the horizontal tail is glued by J-133C structural glue.

[0021] As a preferred scheme of the utility model, the vertical tail and the flat tail are connected through 7075-T7451 aluminum alloy machine parts, each group of joint of the vertical tail and the flat tail adopts two bolt and nut connections, and the bolt is assembled at the outer surface of the tail wing;

[0022] The vertical tail and the flat tail are arranged to be installed on the tail wing, thereby achieving the effect of efficiently assisting the flight of the unmanned aerial vehicle.

[0023] The utility model provides a kind of unmanned aerial vehicle tail wing structure.It has the following beneficial effects:

[0024] 1、The unmanned aerial vehicle tail wing structure, the structure of flat tail and vertical tail formed by foam filling moulding is lighter than traditional metal structure, can reduce the overall weight of aircraft, while its composite carbon fiber fabric skin plus foam filling material can provide good structural strength, can meet various mechanical requirements in flight process, to be able to reduce energy consumption of flight while guaranteeing flight effect, solve the problem that existing traditional steel material is relatively heavy, easy to affect unmanned aerial vehicle flight;

[0025] 2、The unmanned aerial vehicle tail wing structure, by being installed outside the tail wing, can be maintained without disassembling the cover, save time and cost, while composite material carbon fiber plus fabric foam filling material has good corrosion resistance, can maintain long service life in harsh environment, to realize the goal of convenient maintenance, low manufacturing cost, high durability and light weight. BRIEF DESCRIPTION OF DRAWINGS

[0026] Figure 1 It is the structure diagram of the vertical tail of the utility model;

[0027] Figure 2 It is the structure diagram of the flat tail of the utility model.

[0028] In the drawing: A1, vertical tail skin;A2, vertical tail front beam;A3, vertical tail rear beam;A4, vertical tail rib #1;A5, vertical tail end rib;A6, vertical tail frame;B1, flat tail skin;B2, flat tail rear beam;B3, flat tail front beam;B4, flat tail rib;B5, flat tail end rib;B6, flat tail connecting piece #2;B7, flat tail connecting piece #1. DETAILED DESCRIPTION

[0029] The technical scheme in the embodiments of the utility model will be described clearly and completely in conjunction with the drawings of the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor belong to the scope of protection of the utility model.

[0030] Referring to Figure 1 and 2 The utility model discloses an unmanned aerial vehicle tail wing structure, tail wing, tail wing is composed of fin and tail plane, the outer wall of fin is equipped with fin skin A1, and the front and back sides of fin are provided with fin front beam A2 and fin rear beam A3, and the bottom end of fin is equipped with fin end rib A5 through fin rib 1A4, and the top end of fin is fixedly installed with fin frame A6, and the tail plane is equipped with tail plane skin B1, and the top and bottom sides of tail plane are provided with tail plane rear beam B2 and tail plane front beam B3, and the tail end of tail plane is provided with tail plane connecting piece 1B7 and tail plane connecting piece 2B6 that are opposite in position, and J-133C structural glue is used to glue the tail plane connecting piece 1B7 and tail plane connecting piece 2B6, and the tail plane connecting piece 1B7 and tail plane connecting piece 2B6 are provided with tail plane end rib B5 between them.

[0031] The unmanned aerial vehicle tail wing structure is lighter than the traditional metal structure, can reduce the overall weight of the aircraft, and can provide good structural strength by the composite carbon fiber fabric skin and the foam filling material, can meet various mechanical requirements in the flight process, and can reduce the energy consumption of flight while ensuring the flight effect, and solves the problem that the existing traditional steel material is heavy and affects the flight of the unmanned aerial vehicle.

[0032] Embodiment 2:

[0033] The fin skin A1 and the tail plane skin B1 in the fin and the tail plane are all made of composite material carbon fiber fabric skin material, wherein each component in the tail plane and the tail plane is made by molding to ensure the manufacturing effect of each component.

[0034] The fin front beam A2 and the fin rear beam A3 in the fin and the tail plane and the tail plane skin B1 and the tail plane front beam B3 are all C-shaped cross-section structures, wherein the setting of the structure shape of the fin front beam A2 and the fin rear beam A3 and the tail plane skin B1 and the tail plane front beam B3 can ensure the rigidity and structure shape of the tail plane and the tail plane as a whole.

[0035] Foam is pre-embedded in the fin and the tail plane, and the foam and the fin skin A1, the fin front beam A2, the fin rear beam A3, the fin rib 1A4, the fin end rib A5 and the fin frame A6 in the fin are glued by J-133C structural glue, and the foam and the tail plane skin B1, the tail plane rear beam B2, the tail plane front beam B3, the tail plane rib B4, the tail plane end rib B5 and the tail plane connecting piece 2B6 in the tail plane are glued by J-133C structural glue, wherein the J-133C structural glue is composed of modified epoxy resin and modified amine curing agent, and is glued by room temperature curing and heating curing.

[0036] The vertical tail skin A1 and horizontal tail skin B1 in the vertical tail and horizontal tail are bonded together by J-133C structural adhesive.

[0037] The vertical stabilizer and horizontal stabilizer are connected by a 7075-T7451 aluminum alloy machined part. Each joint of the vertical stabilizer and horizontal stabilizer is connected by two bolts and nuts, and the bolts are mounted on the outer surface of the tail fin. The vertical stabilizer and horizontal stabilizer are designed to facilitate their installation on the tail fin, thereby achieving the effect of efficient flight assistance for the UAV.

[0038] The tail structure of this drone, by mounting it on the outside of the tail fin, eliminates the need to remove the cover during maintenance, saving time and costs. At the same time, the composite material carbon fiber plus fabric foam filling material has good corrosion resistance and can maintain a long service life in harsh environments, thus achieving the goals of convenient maintenance, low manufacturing cost, high durability and light weight.

[0039] The tail fin consists of a horizontal stabilizer and a vertical stabilizer. The horizontal stabilizer skin is made of composite carbon fiber fabric and is formed by integral molding. The tail fin structure is arranged with double beams as the main load-bearing components. At the horizontal stabilizer-vertical stabilizer connection joint, the horizontal stabilizer and vertical stabilizer are connected by a metal part in the form of an "I". The fasteners are on the outer surface of the tail fin. When maintaining the tail fin, only the four fasteners on the outside need to be removed, which can save maintenance time.

[0040] The working principle and usage process of this utility model are as follows: When manufacturing this device, foam is pre-embedded before bonding the vertical tail skin A1 and the horizontal tail skin B1. J-133C structural adhesive is used to bond the vertical tail skin A1 and the horizontal tail skin B1, the vertical tail front beam A2 and the horizontal tail front beam B3, the vertical tail rear beam A3 and the horizontal tail front beam B3, the foam-skin connection, the beam-horizontal tail skin connection, and the rib-horizontal tail skin connection. After the upper and lower vertical tail skin A1 and the horizontal tail skin B1 are pre-embedded, the skins can be merged into a whole by bonding. Then, 7075-T7451 aluminum alloy machining parts are used to fix the horizontal tail and the vertical tail. Finally, the horizontal tail and the vertical tail are fixedly installed on the tail fin using fastening bolts to ensure the convenience of subsequent disassembly and maintenance.

[0041] The basic principle and main features of the present application and the advantages of the present application are shown and described above, for those skilled in the art, obviously the present application is not limited to the details of the above exemplary embodiments, and can be realized in other specific forms without departing from the spirit or basic characteristics of the present application. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting, the scope of the present application is defined by the appended claims rather than the above description, therefore all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be included in the present application. Any reference signs in the claims should not be considered as limiting the claims involved.

[0042] In addition, it should be understood that, although the present application is described in the form of embodiments, not every embodiment contains only one independent technical solution, the description of the specification is only for the sake of clarity, those skilled in the art should consider the specification as a whole, the technical solutions in each embodiment can also be combined appropriately to form other embodiments that those skilled in the art can understand.

Claims

1. An unmanned aerial vehicle tail wing structure, characterized by: The tail fin is composed of a vertical fin and a horizontal fin. An outer wall of the vertical fin is equipped with a vertical fin skin (A1), front and back sides of the vertical fin are provided with a vertical fin front beam (A2) and a vertical fin back beam (A3), a bottom end of the vertical fin is equipped with a vertical fin end rib (A5) through a vertical fin rib #1 (A4), and a top end of the vertical fin is fixedly installed with a vertical fin frame (A6). The horizontal fin is equipped with a horizontal fin skin (B1), top and bottom sides of the horizontal fin are provided with a horizontal fin back beam (B2) and a horizontal fin front beam (B3), a tail end of the horizontal fin is provided with a horizontal fin connector #1 (B7) and a horizontal fin connector #2 (B6) in opposite positions, and a horizontal fin end rib (B5) is arranged between the horizontal fin connector #1 (B7) and the horizontal fin connector #2 (B6).

2. The unmanned aerial vehicle tail wing structure of claim 1, wherein: The vertical fin skin (A1) and the horizontal fin skin (B1) in the vertical fin and the horizontal fin are both made of composite carbon fiber fabric skin material.

3. The unmanned aerial vehicle tail wing structure of claim 1, wherein: The vertical fin front beam (A2) and the vertical fin back beam (A3) in the vertical fin and the horizontal fin skin (B1) and the horizontal fin front beam (B3) are both C-shaped cross-section structures.

4. The unmanned aerial vehicle tail wing structure of claim 1, wherein: Foams are pre-embedded in the vertical fin and the horizontal fin, the foams are glued to the vertical fin skin (A1), the vertical fin front beam (A2), the vertical fin back beam (A3), the vertical fin rib #1 (A4), the vertical fin end rib (A5), and the vertical fin frame (A6) in the vertical fin through J-133C structural glue, and the foams are glued to the horizontal fin skin (B1), the horizontal fin back beam (B2), the horizontal fin front beam (B3), the horizontal fin rib (B4), the horizontal fin end rib (B5), and the horizontal fin connector #2 (B6) in the horizontal fin through J-133C structural glue.

5. The unmanned aerial vehicle tail wing structure of claim 1, wherein: Each group of vertical fin skins (A1) and horizontal fin skins (B1) in the vertical fin and the horizontal fin are glued together through J-133C structural glue.

6. The unmanned aerial vehicle tail wing structure of claim 1, wherein: The vertical fin and the horizontal fin are connected through 7075-T7451 aluminum alloy machine parts, two bolts and nuts are used for each group of joints of the vertical fin and the horizontal fin, and the bolts are assembled at the outer surface of the tail fin.

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