CN217805228U

CN217805228U - Composite material unmanned aerial vehicle structure capable of being integrally formed

Info

Publication number: CN217805228U
Application number: CN202221250164.6U
Authority: CN
Inventors: 胡春雷; 徐田彬; 尹传红
Original assignee: Shandong Feishi Intelligent Technology Co ltd
Current assignee: Shandong Feishi Intelligent Technology Co ltd
Priority date: 2022-05-24
Filing date: 2022-05-24
Publication date: 2022-11-15
Anticipated expiration: 2032-05-24

Abstract

The utility model discloses a but integrated into one piece's combined material unmanned aerial vehicle structure, including fuselage subassembly, wing subassembly and horizontal tail subassembly, the both sides of fuselage subassembly all are provided with the wing subassembly, and the tail end of fuselage subassembly is provided with the horizontal tail subassembly, the fuselage subassembly includes first vertical strengthening rib, annular strengthening rib and fuselage covering. Through letting first vertical strengthening rib, the structural strength of fuselage subassembly not only can be improved to annular strengthening rib and fuselage covering, simultaneously can also let its processing more convenient, through the first vertical stiffening beam that sets up, first horizontal strengthening rib, the synthetic degree that wing subassembly can be improved to the vertical strengthening rib of second and connection intubate, through the first horizontal stiffening beam that sets up, the vertical stiffening beam of second, mutually support between the vertical strengthening rib of third and the horizontal strengthening rib of second, thereby can let the installation of horizontal tail subassembly more convenient, and then can effectually shorten the time of processing.

Description

Composite material unmanned aerial vehicle structure capable of being integrally formed

Technical Field

The utility model relates to an unmanned aerial vehicle makes technical field, specifically is a but integrated into one piece's combined material unmanned aerial vehicle structure.

Background

An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. Drones tend to be more suitable for tasks that are too "fool, dirty, or dangerous" than are manned aircraft. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle is applied in the industry and is really just needed by the unmanned aerial vehicle; the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand the industrial application and develop the unmanned aerial vehicle technology.

The traditional unmanned aerial vehicle body manufacturing process adopts a prepreg or a molding structure which is formed by introducing vacuum into a semi-finished product and then closing a mold; the machine body, the wings and the tail are usually formed by laying prepreg on a mould or introducing resin glue in vacuum, then laying disposable auxiliary materials (an isolating film, demoulding cloth, adhesive suction or an isolating film, a flow guide net, demoulding cloth and adhesive suction) to seal by using a vacuum bag, pushing the auxiliary materials into an oven to be cured and formed, removing the auxiliary materials to cut along the edge of the mould to remove corners, finally taking out a machine shell, then precisely processing a laminated board or a glass fiber board by using a laser engraving machine or a numerical control engraving machine to be used as a meat frame in the machine body, needing to be repeatedly debugged, modified and polished, putting the machine shell back into the mould to be trial assembled, positioning the cut separating frame by a positioning tool, then smearing the resin glue to fix, closing the mould, and finally producing a complete individual after curing, and closing the mould by mostly combining the vertical tail and the machine body, wherein the inner frame in the vertical tail is also repeatedly debugged, modified and polished, and finally positioned and formed by the tool;

the product produced by the molding structure has great defects; (1) the bonding area at the die assembly position is small, and the bonding strength is not high; (2) A plurality of tools are needed in the whole manufacturing process, so that the difficulty and complexity of installation are increased; (3) low efficiency and high labor cost. 80-120 working hours are needed for manufacturing a complete machine shell, and only 32 working hours are needed for production by utilizing a new process; (4) The working environment needs to contact resin adhesive in the mold closing process, and the site is easy to be dirty and messy; (5) The weight of the product produced by this process is heavy; (6) The formed product is easy to deform and has larger deviation from actual theoretical data; the flight performance is influenced, and the workload of test flight, installation and debugging is invisibly increased.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a but integrated into one piece's combined material unmanned aerial vehicle structure aims at improving the problem that traditional unmanned aerial vehicle preparation technology exists.

The utility model discloses a realize like this:

the utility model provides a but integrated into one piece's combined material unmanned aerial vehicle structure, includes fuselage subassembly, wing subassembly and horizontal tail subassembly, the both sides of fuselage subassembly all are provided with the wing subassembly, and the tail end of fuselage subassembly is provided with horizontal tail subassembly, the fuselage subassembly includes first longitudinal reinforcement, annular reinforcement and fuselage skin, first longitudinal reinforcement and annular reinforcement all set up in the inside of fuselage skin, the outside of first longitudinal reinforcement is provided with the annular reinforcement, fixed connection between first longitudinal reinforcement and the annular reinforcement, the wing subassembly includes first longitudinal reinforcement beam, the first horizontal strengthening rib of outside fixedly connected with of first longitudinal reinforcement beam, equidistant distribution of first horizontal strengthening rib, the outside fixedly connected with second longitudinal reinforcement of first horizontal strengthening rib, the outside of second longitudinal reinforcement is provided with the wing skin, horizontal tail subassembly includes first horizontal reinforcement beam, fixedly connected with second longitudinal reinforcement beam on the first horizontal reinforcement beam, the outside fixedly connected with second horizontal strengthening rib of second longitudinal reinforcement beam, the outside fixedly connected with third longitudinal reinforcement of second horizontal strengthening rib.

Furthermore, the one end of wing covering is provided with the connection intubate, set up to integrated into one piece structure between connection intubate and the wing covering, through the design be for improving the overall structure intensity of wing subassembly to let connection intubate and wing covering set up to integrated into one piece, be for improving its synthetic degree, be for the convenience of being connected the wing subassembly in the both sides of fuselage subassembly through the wing covering that sets up.

Further, the one end of fuselage subassembly is provided with the vertical fin, the vertical fin and the fuselage subassembly between set up to integrated into one piece structure, through setting up like this in order to improve the overall structure intensity of fuselage subassembly.

Furthermore, the bottom of the vertical tail is provided with an attaching groove, the attaching groove and the first transverse reinforcing beam are attached to each other, and the horizontal tail assembly is more convenient and firm to mount through the arrangement.

Further, the first longitudinal reinforcing beam and the connecting insertion pipe are both provided as hollow structures, and the hollow structures are arranged to strengthen the weight of the wing assembly.

Further, the shape of the second transverse reinforcing rib is set to be an oval structure, and the second transverse reinforcing rib is set to be more tightly attached to the third longitudinal reinforcing rib.

Further, the number of the first longitudinal reinforcing beams is two, and the arrangement is to improve the overall structural strength of the wing assembly.

Compared with the prior art, the beneficial effects of the utility model are that: the utility model has the characteristics of rational in infrastructure, the equipment is convenient, through letting first vertical strengthening rib, annular strengthening rib and fuselage covering not only can improve the structural strength of fuselage subassembly, can also let its processing more convenient simultaneously, through the first vertical stiffening beam that sets up, first horizontal strengthening rib, the vertical strengthening rib of second and the synthetic degree that the connection intubate can improve the wing subassembly, through the first horizontal stiffening beam that sets up, the vertical stiffening beam of second, mutually support between the vertical strengthening rib of third and the horizontal strengthening rib of second, thereby can let the installation of horizontal tail subassembly more convenient, and then can effectually shorten the time of processing.

Drawings

In order to more clearly illustrate the technical solution of the embodiments of the present invention, the drawings which are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and that for those skilled in the art, other related drawings can be obtained according to these drawings without inventive efforts.

Fig. 1 is a schematic structural view of a fuselage assembly of an integrally formable composite material unmanned aerial vehicle structure of the present invention;

fig. 2 is a schematic structural view of a wing assembly of the integrally formable composite material unmanned aerial vehicle structure of the present invention;

fig. 3 is the utility model discloses a but the structural schematic of horizontal tail subassembly of integrated into one piece's combined material unmanned aerial vehicle structure.

In the figure: 1. a fuselage assembly; 11. a first longitudinal reinforcing rib; 12. an annular reinforcing rib; 13. a fuselage skin; 2. a wing assembly; 21. a first longitudinal stiffening beam; 22. a first transverse reinforcing rib; 23. a second longitudinal reinforcing rib; 24. connecting the cannula; 25. a wing skin; 3. a horizontal tail assembly; 31. a first transverse reinforcement beam; 32. a second longitudinal reinforcing beam; 33. a third longitudinal reinforcing rib; 34. a second transverse reinforcing rib; 4. hanging a tail; 41. and fitting the groove.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are exemplary only for the purpose of explaining the present invention, and should not be construed as limiting the present invention.

To make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the drawings of the embodiments of the present invention are combined to clearly and completely describe the technical solutions of the embodiments of the present invention, and obviously, the described embodiments are some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work all belong to the protection scope of the present invention. Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work all belong to the protection scope of the present invention.

Referring to fig. 1-3, an unmanned aerial vehicle structure made of composite materials and capable of being integrally formed comprises a fuselage assembly 1, a wing assembly 2 and a horizontal tail assembly 3, wherein the wing assembly 2 is arranged on each of two sides of the fuselage assembly 1, the horizontal tail assembly 3 is arranged at the tail end of the fuselage assembly 1, the fuselage assembly 1 comprises a first longitudinal reinforcing rib 11, an annular reinforcing rib 12 and a fuselage skin 13, the first longitudinal reinforcing rib 11 and the annular reinforcing rib 12 are arranged inside the fuselage skin 13, the annular reinforcing rib 12 is arranged on the outer side of the first longitudinal reinforcing rib 11, the first longitudinal reinforcing rib 11 and the annular reinforcing rib 12 are fixedly connected, the wing assembly 2 comprises a first longitudinal reinforcing beam 21, the first transverse reinforcing beam 21 is fixedly connected with a first transverse reinforcing rib 22 on the outer side, the first transverse reinforcing rib 22 is distributed at equal intervals, the second longitudinal reinforcing rib 23 is fixedly connected to the outer side of the first transverse reinforcing rib 22, the second longitudinal reinforcing rib 23 is arranged on the outer side of the second longitudinal reinforcing rib 23, the horizontal tail assembly 3 comprises a first transverse reinforcing beam 31, the second transverse reinforcing rib 32 is fixedly connected with a second transverse reinforcing rib 34, and the second transverse reinforcing rib 34 is arranged on the outer side of the fuselage skin to improve the strength of the fuselage assembly 33;

preferably, one end of the wing skin 25 is provided with the connecting insertion tube 24, an integrally formed structure is arranged between the connecting insertion tube 24 and the wing skin 25, the design is to improve the overall structural strength of the wing assembly 2, and the connecting insertion tube 24 and the wing skin 25 are integrally formed to improve the synthesis degree of the wing assembly 2, and the wing skin 25 is arranged to facilitate the connection of the wing assembly 2 to two sides of the fuselage assembly 1.

Preferably, the one end of fuselage subassembly 1 is provided with vertical fin 4, vertical fin 4 and fuselage subassembly 1 between set up to the integrated into one piece structure, and its inside sets up to penetrating structure, through so set up in order to improve fuselage subassembly 1's overall structure intensity.

Preferably, the bottom of the vertical fin 4 is provided with an attaching groove 41, the attaching groove 41 and the first transverse reinforcing beam 31 are attached to each other, and the attaching groove 41 and the first transverse reinforcing beam are arranged so as to enable the installation of the horizontal fin assembly 3 to be more convenient and firm.

Preferably, the first longitudinal stiffening beam 21 and the connecting insertion tube 24 are both provided as hollow structures, by which means the weight of the wing assembly 2 is strengthened.

Preferably, the second transverse beads 34 are shaped in an oval configuration, by which they are arranged to fit more closely to the third longitudinal beads 33.

Preferably, the number of first longitudinal stiffening beams 21 is two, by which is meant to increase the overall structural strength of the wing assembly 2.

The utility model discloses a processing method:

(1) Forming a machine body:

(a) The carbon fiber prepreg cloth which is cut in advance is laid in the mold on one side, the longitudinal reinforcing material is laid on the machine body at the marked position in the longitudinal direction, the semicircular reinforcing cloth is also laid on the machine body at the marked position in the annular direction, and the carbon fiber prepreg cloth on the periphery of the mold is cut along the edge of the mold.

(b) Laying carbon fiber prepreg cloth which is cut in advance in the mold on the other side, laying longitudinal reinforcing materials on the machine body at the marked position in the longitudinal direction, laying semicircular reinforcing cloth at the marked position in the annular direction, and cutting the carbon fiber prepreg cloth on the periphery of the mold at the position 40-50mm away from the edge of the mold.

(c) And (3) placing an air bag in the mold cavity, combining the two molds together after finishing, fixing the peripheries of the two molds by using bolts, sealing and vacuumizing by using a vacuum belt, and placing the two molds into a pressure tank container for curing and molding.

(2) Forming wings:

(a) And laying pre-cut carbon fiber prepreg cloth in the mold on one side, laying longitudinal reinforcing materials on the marked positions of the wings in the longitudinal direction, laying semicircular reinforcing cloth on the marked positions in the annular direction, and cutting the carbon fiber prepreg cloth on the periphery of the mold along the edge of the mold.

(b) Laying carbon fiber prepreg cloth which is cut in advance in the die on the other side, laying longitudinal reinforcing materials on the wing at the marked position in the longitudinal direction, laying semicircular reinforcing cloth at the marked position in the annular direction, laying the carbon fiber prepreg cloth on the periphery of the die which is informed of cutting at the marked position of the wing reinforcing beam, and cutting the carbon fiber prepreg cloth at the position 40-50mm away from the edge of the die.

(c) And placing an air bag and a fixed longitudinal stiffening beam in a mold cavity, combining the two molds together after finishing, fixing the peripheries of the two molds by using bolts, sealing and vacuumizing by using a vacuum belt, and placing the two molds into a pressure tank container for curing and forming.

(3) Forming a horizontal tail:

(a) Laying carbon fiber prepreg cloth which is cut in advance in a die on one side, longitudinally laying longitudinal reinforcing materials on the flat tail at the position where the mark is made, laying semicircular reinforcing cloth on the ring at the position where the mark is made, and cutting the carbon fiber prepreg cloth on the periphery of the die along the edge of the die.

(b) Laying carbon fiber prepreg cloth which is cut in advance in the mold on the other side, laying longitudinal reinforcing materials on the flat tail at the marked position in the longitudinal direction, laying semicircular reinforcing cloth at the marked position in the annular shape, laying the carbon fiber prepreg cloth on the periphery of the mold which is informed of cutting in advance at the marked position of the wing reinforcing beam, and cutting the carbon fiber prepreg cloth at the position 40-50mm away from the edge of the mold.

To summarize: taking advantage of the advantages of such a shaped structure.

(1) Short production period, high efficiency, and only 24-36 working hours for manufacturing one set of machine body

(2) The whole manufacturing process is simple and easy to learn, and a large amount of auxiliary production of tools is not needed. And (3) the bonding area at the die assembly position is large, and the bonding strength is high.

(4) The product produced by the molding structure has light weight and high structural strength, and the weight is 5.8Kg.

(5) The formed product has high structural consistency, has extremely small deviation with an actual theoretical model, does not influence the flight performance, and greatly reduces the workload of test flight, installation and debugging.

(6) The field working environment is clean.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The utility model provides a but integrated into one piece's combined material unmanned aerial vehicle structure, includes fuselage subassembly (1), wing subassembly (2) and horizontal tail subassembly (3), the both sides of fuselage subassembly (1) all are provided with wing subassembly (2), and the tail end of fuselage subassembly (1) is provided with horizontal tail subassembly (3), its characterized in that: the aircraft fuselage assembly (1) comprises a first longitudinal reinforcing rib (11), an annular reinforcing rib (12) and an aircraft fuselage skin (13), the first longitudinal reinforcing rib (11) and the annular reinforcing rib (12) are arranged inside the aircraft fuselage skin (13), the outer side of the first longitudinal reinforcing rib (11) is provided with the annular reinforcing rib (12), the first longitudinal reinforcing rib (11) and the annular reinforcing rib (12) are fixedly connected, the aircraft wing assembly (2) comprises a first longitudinal reinforcing beam (21), the outer side of the first longitudinal reinforcing beam (21) is fixedly connected with a first transverse reinforcing rib (22), the first transverse reinforcing rib (22) is distributed at equal intervals, the outer side of the first transverse reinforcing rib (22) is fixedly connected with a second longitudinal reinforcing rib (23), the outer side of the second longitudinal reinforcing rib (23) is provided with an aircraft wing skin (25), the horizontal tail assembly (3) comprises a first transverse reinforcing beam (31), the first transverse reinforcing beam (31) is fixedly connected with a second longitudinal reinforcing beam (32), the outer side of the second longitudinal reinforcing beam (32) is fixedly connected with a second transverse reinforcing rib (34), and the outer side of the second transverse reinforcing rib (33) is fixedly connected with a third transverse reinforcing rib (33).

2. An integrally formable composite material unmanned aerial vehicle structure according to claim 1, wherein the wing skin (25) is provided with a connection insertion tube (24) at one end, and an integrally formed structure is provided between the connection insertion tube (24) and the wing skin (25).

3. An integrally formable composite material unmanned aerial vehicle structure according to claim 1, wherein one end of the fuselage assembly (1) is provided with a vertical fin (4), and an integrally formed structure is arranged between the vertical fin (4) and the fuselage assembly (1).

4. The integrally formed composite unmanned aerial vehicle structure of claim 3, wherein the bottom of the vertical fin (4) is provided with an attaching groove (41), and the attaching groove (41) and the first transverse reinforcing beam (31) are attached to each other.

5. An integrally formable composite material drone structure according to claim 1, characterised in that the first longitudinal stiffening beam (21) and the connection cannula (24) are both provided as hollow structures.

6. An integrally formable composite material drone structure according to claim 1, wherein the second transverse stiffener (34) is shaped as an oval structure.

7. An integrally formable composite material drone structure according to claim 1, characterized in that the number of the first longitudinal stiffening beams (21) is provided in two.