CN221049945U - Bionic butterfly flapping-wing aircraft - Google Patents

Abstract

The embodiment discloses a bionic butterfly ornithopter, which comprises a fuselage, wings and a driving mechanism, wherein the wings comprise a first flying wing and a second flying wing which are symmetrically arranged on two sides of the fuselage by the central axis of the fuselage; the first flying wing and the second flying wing both comprise flying wing connectors, a front framework and a rear framework, wherein the flying wing connectors are arranged on the outer side of the fuselage in a swinging way, the front framework and the rear framework are connected with the flying wing connectors, the front framework is positioned in front of the rear framework, the front framework and the rear framework are respectively adhered with a front film and a rear film, and a superposition area is formed by superposition of the front film and the rear film; the driving mechanism is mounted on the machine body. According to the technical scheme, the overlapping area is formed between the front film and the rear film in an overlapping manner, so that in the process that the flying wing connector is driven to swing by the driving mechanism, the parts of the front film and the rear film located in the overlapping area are pressed to be matched with each other to close or open the overlapping area, and the lifting force of the bionic butterfly ornithopter can be improved.

Description

Bionic butterfly flapping-wing aircraft

Technical Field

The utility model relates to the technical field of aircrafts, in particular to a bionic butterfly ornithopter.

Background

In nature birds, insects evolve body structures that fly freely in the air by virtue of a constant evolution process. In the field of flapping-wing aircraft, humans have developed flapping-wing aircraft of different shapes (e.g., butterfly-like flapping-wing aircraft) by constantly referencing the body structure of animals in nature. Because the ornithopter has high maneuverability, concealment and flexibility, the ornithopter has wide application prospect in the national defense field and civil aspect.

The chinese patent number 202011391417.7 discloses a bionical butterfly flapping wing aircraft, it comprises right pterygoid lamina, drive mechanism subassembly, left pterygoid lamina and bionical fin, right pterygoid lamina and left pterygoid lamina are symmetrical about the fuselage axis, wherein, right pterygoid lamina comprises right film, right skeleton and right rocker, right film bonds in right skeleton upper surface, and the appearance of right film is butterfly wing shape, it is that right film follows right skeleton and swings to drive the rocker when drive mechanism drives, but the right film in above-mentioned patent adopts the monoblock to bond on right skeleton, the resistance that receives when flapping on flapping wing aircraft is relatively poor, the lift of production is unfavorable for the stable flight of flapping wing aircraft.

Disclosure of utility model

In order to solve the technical problems, the utility model provides a bionic butterfly ornithopter.

The embodiment of the application provides a bionic butterfly ornithopter, which comprises the following components:

A body;

The wing comprises a first flying wing and a second flying wing which are symmetrically arranged on two sides of the fuselage by the central axis of the fuselage; the first flying wing and the second flying wing comprise flying wing connectors, a front framework and a rear framework, the flying wing connectors are arranged on the outer side of the airframe in a swinging mode, the front framework and the rear framework are connected with the flying wing connectors, the front framework is positioned in front of the rear framework, a front film and a rear film are respectively bonded on the front framework and the rear framework, and a superposition area is formed between the front film and the rear film in a superposition mode;

The driving mechanism is arranged on the aircraft body and is configured to drive the flying wing connecting piece to swing so as to drive the wing to flap up and down.

In one embodiment, the overlap region is divided into a first overlap region and a second overlap region, the first overlap region is adjacent to the flying wing connector, the front film in the first overlap region is bonded to the rear film, and the front film in the second overlap region is unbonded to the rear film.

In one embodiment, the flying wing connector comprises a connector body and a plurality of columns in fan-shaped distribution, wherein one end of the connector body, which is close to the body, is connected with the driving mechanism, the columns are fixed on the connector body, and each column is provided with a fixing hole for fixing the front framework and the rear framework.

In an embodiment, the front skeleton includes first skeleton strip, second skeleton strip and third skeleton strip, first skeleton strip with the direction that the fuselage was kept away from is all followed to the second skeleton strip, first skeleton strip with the second skeleton strip is close to one end of fuselage is pegged graft respectively to in the fixed orifices of two adjacent cylinders, first skeleton strip is located in the place ahead of second skeleton strip, follows the extending direction of first skeleton interval distribution has a plurality of in proper order third skeleton strip, third skeleton strip with first skeleton strip and second skeleton strip are connected, preceding film with first skeleton strip second skeleton strip and third skeleton strip bonds.

In one embodiment, the rear skeleton comprises a fourth skeleton strip, two ends of the fourth skeleton strip are respectively inserted into the fixing holes of two adjacent columns to form a second flapping wing area, and the rear film is adhered to the fourth skeleton strip and covers the second flapping wing area.

In one embodiment, the driving mechanism comprises a first steering engine and a second steering engine which are symmetrically arranged along the central axis of the fuselage, the first steering engine and the second steering engine are fixed on the fuselage, the power output end of the first steering engine is connected with one end, close to the fuselage, of the wing connecting piece of the first flying wing, and the power output end of the second steering engine is connected with one end, close to the fuselage, of the wing connecting piece of the second flying wing.

In one embodiment, the steering engine comprises a steering engine seat, wherein the steering engine seat is embedded in the engine body, a first installation position and a second installation position which are symmetrical to the central axis of the engine body are formed in the steering engine seat, and the first steering engine and the second steering engine are respectively fixed in the first installation position and the second installation position.

In an implementation mode, a strip cavity and a fixing cavity for fixing the steering engine seat are formed in the machine body, the strip cavity is formed in the center axis direction of the machine body and located behind the fixing cavity, a connecting strip is arranged in the strip cavity, and one end of the connecting strip extends into the fixing cavity and is connected with the steering engine seat.

Compared with the prior art, the technical scheme provided by the embodiment of the application has the beneficial effects that:

The front framework and the rear framework are respectively bonded with the front film and the rear film, and a superposition area is formed between the front film and the rear film in a superposition manner, so that in the process that the flying wing connector is driven by the driving mechanism to swing downwards, the parts of the front film and the rear film positioned in the superposition area are subjected to downward pressure to be matched with each other to close the superposition area, the lifting force of the bionic butterfly flapping wing aircraft can be improved, and in the process that the flying wing connector is driven to swing upwards, the parts of the front film and the rear film positioned in the superposition area are opened by upward acting force, so that resistance penetrates through the superposition area, the resistance received in the wing flapping-up process is effectively reduced, and the aerodynamic performance of the bionic butterfly flapping wing aircraft is provided.

Drawings

FIG. 1 is a schematic diagram of a bionic butterfly ornithopter of the present application;

FIG. 2 is a schematic view of a bionic butterfly ornithopter of the present application with the front and rear membranes removed;

FIG. 3 is a schematic view of the fuselage and wing connector of a bionic butterfly ornithopter of the present application;

FIG. 4 is a schematic diagram of the drive mechanism and the winged connector of the bionic butterfly ornithopter of the present application;

fig. 5 is a schematic structural view of a fuselage of a bionic butterfly ornithopter according to the present application.

Reference numerals in the drawings:

10. A body; 10a, a strip cavity; 10b, a fixation cavity; 21. a first flying wing; 211. a flying wing connector; 2111. a connector body; 2112. a column; 2112a, fixation hole; 212. a front skeleton; 212a, a first skeleton strip; 212b, a second skeleton strip; 212c, a third skeleton strip; 213. a rear skeleton; 213a, a fourth skeleton strip; 214. a front film; 215. a rear film; 22. a second flying wing; 30. a driving mechanism; 31. the first steering engine; 32. the second steering engine; 40. a rudder mount; 40a, a first mounting location; 40b, a second installation position; 50. and (5) connecting strips.

Detailed Description

For a clearer understanding of technical features, objects and effects of the present utility model, a detailed description of embodiments of the present utility model will be made with reference to the accompanying drawings. In the following description, it should be understood that the directions or positional relationships indicated by "front", "rear", "upper", "lower", "left", "right", "longitudinal", "transverse", "vertical", "horizontal", "top", "bottom", "inner", "outer", "head", "tail", etc. are configured and operated in specific directions based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present utility model, and do not indicate that the apparatus or element to be referred to must have specific directions, and thus should not be construed as limiting the present utility model.

The following describes in further detail the embodiments of the present utility model with reference to the drawings and examples. The following examples are illustrative of the utility model and are not intended to limit the scope of the utility model.

Referring to fig. 1 to 5, an embodiment of the present disclosure provides a bionic butterfly ornithopter, which includes a fuselage 10, wings and a driving mechanism 30.

Specifically, the wing includes a first flying wing 21 and a second flying wing 22 symmetrically disposed at both sides of the fuselage 10 with respect to the central axis of the fuselage 10. Wherein, the first flying wing 21 and the second flying wing 22 each comprise a flying wing connector 211, a front skeleton 212 and a rear skeleton 213, the flying wing connector 211 is arranged outside the fuselage 10 in a swinging way, the front skeleton 212 and the rear skeleton 213 are connected with the flying wing connector 211, the front skeleton 212 is positioned in front of the rear skeleton 213, and a front film 214 and a rear film 215 are respectively bonded on the front skeleton 212 and the rear skeleton 213, and a superposition area formed by superposition between the front film 214 and the rear film 215 is formed. A drive mechanism 30 is mounted to the fuselage 10, the drive mechanism 30 being configured to drive the wing attachment 211 in a swinging motion to cause the wing to flutter up and down.

Here, it should be noted that the above-mentioned "central axis of the fuselage 10" is a reference line introduced for convenience in describing the relative positions of the first flying wing 21 and the second flying wing 22, and may be specifically referred to as O-O' in fig. 1.

Illustratively, the fuselage 10 may be supported by carbon fiber materials, so that the overall weight of the bionic butterfly ornithopter may be effectively reduced, which is beneficial to improving the flight stability of the bionic butterfly ornithopter. Those skilled in the art will appreciate that the above materials are examples only and are not limited thereto.

Illustratively, the front and rear films 214, 215 may be attached to the front and rear frames 212, 213, respectively, by adhesive means. For the sake of easy understanding, the following description will be given by taking the connection between the front membrane 214 and the front skeleton 212 as an example, specifically: the front frame 212 may be coated with an adhesive or a tacky film at the position where the front frame 212 is connected to the front film 214, or an adhesive or a tacky film may be coated at the position where the front frame 212 is connected to the front film 214. The adhesive or the adhesive film can solve the problems of poor adhesiveness and incapability of accurately controlling the size of the transparent adhesive or the double-sided adhesive flanging caused by using the transparent adhesive or the double-sided adhesive, and is beneficial to improving the production precision of wings and the consistency of products. It will be appreciated by those skilled in the art that the above adhesives or adhesive films are merely examples and are not limited thereto.

In addition, the front membrane 214 may be made of a high strength membrane or cloth (e.g., kite cloth) to increase the strength of the front membrane 214 while also reducing the overall weight of the bionic butterfly ornithopter.

Illustratively, the overlapping area formed in the above embodiment is based on that after the front film 214 and the rear film 215 are adhered to the front skeleton 212 and the rear skeleton 213, respectively, a portion of the front film 214 is overlapped with a portion of the rear film 215, and the portion of the front film 214 may be located above the rear film 215, or the front film 214 may be located below the rear film 215, which may be determined according to practical situations, and is not limited thereto.

The bionic butterfly ornithopter based on the technical characteristics comprises a front framework 212 and a rear framework 213 which are adopted by a first flying wing 21 and a second flying wing 22, wherein a front film 214 and a rear film 215 are respectively adhered to the front framework 212 and the rear framework 213, a superposition area is formed between the front film 214 and the rear film 215 in a superposition mode, so that in the process that the flying wing connector 211 is driven to swing downwards by the driving mechanism 30, the parts of the front film 214 and the rear film 215 positioned in the superposition area are subjected to downward pressure to be matched with each other to close the superposition area, the lift force of the bionic butterfly ornithopter can be improved, and in the process that the flying wing connector 211 is driven to swing upwards, the parts of the front film 214 and the rear film 215 positioned in the superposition area are subjected to upward acting force to be opened, the resistance penetrates through the superposition area, the resistance applied in the wing flapping process is effectively reduced, and the aerodynamic performance of the bionic butterfly ornithopter is provided.

In one embodiment, the overlap region is divided into a first overlap region proximate to the flying wing connector 211, the front film 214 in the first overlap region bonded to the rear film 215, and the front film 214 in the second overlap region unbonded to the rear film 215.

Illustratively, the front film 214 and the rear film 215 located in the first overlapped region are adhered by an adhesive to prevent the front frame 212 or the rear frame 213 from being detached from each other by a force during the flying process. In addition, the front film 214 and the rear film 215 located in the second overlapping area are not bonded, so that in the process of upward flapping, the front film 214 and the rear film 215 located in the second overlapping area are blown upwards due to acting force to open the second overlapping area, and the resistance of the wing can be reduced; in the down-flapping process, the front film 214 and the rear film 215 positioned in the second superposition area are covered downwards by acting force, so that the second superposition area is closed under the mutual cooperation of the front film 214 and the rear film 215, and the lifting force of the bionic butterfly ornithopter can be improved.

In one embodiment, the flying wing connector 211 comprises a connector body 2111 and a plurality of columns 2112 distributed in a fan shape, wherein one end of the connector body 2111 close to the fuselage 10 is connected with the driving mechanism 30, the columns 2112 are fixed on the connector body 2111, and each column 2112 is provided with a fixing hole 2112a for fixing with the front skeleton 212 and the rear skeleton 213.

Illustratively, connector body 2111 and post 2112 may be integrally formed to provide a wing connector that is more integral and has greater compressive strength. The connector body 2111 and the column 2112 are made of carbon fiber materials, so that the connector body 2111 and the column 2112 have high strength and light weight, the overall weight of the butterfly-simulated flapping-wing aircraft can be effectively reduced, and the flight effect is improved.

In one embodiment, the front skeleton 212 includes a first skeleton bar 212a, a second skeleton bar 212b and a third skeleton bar 212c, where the first skeleton bar 212a and the second skeleton bar 212b extend along a direction far away from the fuselage 10, one ends of the first skeleton bar 212a and the second skeleton bar 212b near the fuselage 10 are respectively inserted into the fixing holes 2112a of two adjacent columns 2112, the first skeleton bar 212a is located in front of the second skeleton bar 212b, a plurality of third skeleton bars 212c are sequentially and alternately distributed along the extending direction of the first skeleton, the third skeleton bars 212c are connected with the first skeleton bar 212a and the second skeleton bar 212b, and the front film 214 is adhered to the first skeleton bar 212a, the second skeleton bar 212b and the third skeleton bar 212 c.

Illustratively, the front skeleton 212 is composed of a first skeleton bar 212a, a second skeleton bar 212b and a third skeleton bar 212c, and one ends of the first skeleton bar 212a and the second skeleton bar 212b are inserted into the fixing holes 2112a of the corresponding columns 2112, and then the third skeleton bar 212c is connected with the first skeleton bar 212a and the second skeleton bar 212b, so that the front skeleton 212 is assembled with a simple structure and convenient assembly and disassembly.

The connection between the front film 214 and the first, second and third frame strips 212a, 212b, 212c may be performed by applying an adhesive or a film to the front film 214 at the positions where the first, second and third frame strips 212a, 212b, 212c are connected, or by applying an adhesive or a film to the front film 214 at the positions where the first, second and third frame strips 212a, 212b, 212c are connected. Those skilled in the art will appreciate that the above adhesive or adhesive film is merely exemplary and is not limited thereto.

In addition, the adhesive or the adhesive film is adopted to realize the connection between the front film 214 and the first skeleton strip 212a, the second skeleton strip 212b and the third skeleton strip 212c, so that the problem that the adhesiveness is poor and the size of the transparent adhesive or the double-sided adhesive flange cannot be accurately controlled due to the use of the transparent adhesive or the double-sided adhesive can be solved, and the production precision of the wing and the consistency of products are improved. The adhesive or the adhesive film may be coated on the front film 214 side or the first, second and third frame strips 212a, 212b and 212c by a dispenser or the like, so that automated production and assembly may be realized, and the problem that assembly depends on manpower is overcome.

In one embodiment, the rear frame 213 includes a fourth frame strip 213a, and two ends of the fourth frame strip 213a are respectively inserted into the fixing holes 2112a of two adjacent columns 2112 to enclose a second flapping wing area, and the rear film 215 is adhered to the fourth frame strip 213a and covers the second flapping wing area.

Illustratively, the rear skeleton 213 is surrounded by a single fourth skeleton strip 213a, and has a relatively high compression resistance. The fourth frame strip 213a and the rear film 215 may be connected by applying an adhesive or a pressure-sensitive adhesive film to the position where the fourth frame strip 213a is connected to the rear film 215, or by applying an adhesive or a pressure-sensitive adhesive film to the position where the rear film 215 is connected to the fourth frame strip 213 a. Those skilled in the art will appreciate that the above adhesive or adhesive film is merely exemplary and is not limited thereto.

In one embodiment, the driving mechanism 30 includes a first steering engine 31 and a second steering engine 32 symmetrically disposed about a central axis of the fuselage 10, the first steering engine 31 and the second steering engine 32 are fixed on the fuselage 10, and a power output end of the first steering engine 31 is connected to an end of a wing connector of the first flying wing 21 near the fuselage 10, and a power output end of the second steering engine 32 is connected to an end of a wing connector of the second flying wing 22 near the fuselage 10.

Illustratively, the butterfly-like ornithopter in the present embodiment has a first flying wing 21 and a second flying wing 22 symmetrically arranged, and in order to make the butterfly-like ornithopter have a better flight effect, it is necessary to ensure the amplitude synchronization of the first flying wing 21 and the second flying wing 22. For this reason, the first steering engine 31 and the second steering engine 32 need to employ electric steering engines of the same specifications.

In one embodiment, the steering engine further comprises a steering engine base 40, the steering engine base 40 is embedded on the machine body 10, a first installation position 40a and a second installation position 40b which are symmetrical to the central axis of the machine body 10 are formed in the steering engine base 40, and the first steering engine 31 and the second steering engine 32 are respectively fixed in the first installation position 40a and the second installation position 40 b.

Illustratively, through embedding steering wheel seat 40 on fuselage 10 to set up symmetrical first installation position 40a and second installation position 40b on steering wheel seat 40, afterwards in fixing first steering wheel 31 seat and second steering wheel 32 seat in first installation position 40a and second installation position 40b, when need dismantle first steering wheel 31 or second steering wheel 32 from steering wheel seat 40, only need take out first steering wheel 31 or second steering wheel 32 from steering wheel seat 40 can, need not whole dismantlement, simple structure, easy dismounting.

In one embodiment, the body 10 is provided with a long cavity 10a and a fixing cavity 10b for fixing the rudder mount 40, the long cavity 10a is provided along the central axis direction of the body 10 and is located at the rear of the fixing cavity 10b, a connecting strip 50 is arranged in the long cavity 10a, and one end of the connecting strip 50 extends into the fixing cavity 10b to be connected with the rudder mount 40.

The foregoing is merely a preferred embodiment of the present utility model, and it should be noted that modifications and substitutions can be made by those skilled in the art without departing from the technical principles of the present utility model, and these modifications and substitutions should also be considered as being within the scope of the present utility model.

Claims (8)

1. A bionic butterfly ornithopter, comprising:

A body;

The wing comprises a first flying wing and a second flying wing which are symmetrically arranged on two sides of the fuselage by the central axis of the fuselage; the first flying wing and the second flying wing comprise flying wing connectors, a front framework and a rear framework, the flying wing connectors are arranged on the outer side of the airframe in a swinging mode, the front framework and the rear framework are connected with the flying wing connectors, the front framework is positioned in front of the rear framework, a front film and a rear film are respectively bonded on the front framework and the rear framework, and a superposition area is formed between the front film and the rear film in a superposition mode;

The driving mechanism is arranged on the aircraft body and is configured to drive the flying wing connecting piece to swing so as to drive the wing to flap up and down.

2. A bionic butterfly ornithopter as recited in claim 1, wherein the overlap area is divided into a first overlap area and a second overlap area, the first overlap area being proximate to the flying wing connector, the front film within the first overlap area being bonded to the rear film, the front film within the second overlap area being unbonded to the rear film.

3. The bionic butterfly ornithopter of claim 1, wherein the flying wing connector comprises a connector body and a plurality of columns in fan-shaped distribution, one end of the connector body, which is close to the airframe, is connected with the driving mechanism, the columns are fixed on the connector body, and each column is provided with a fixing hole for fixing the front skeleton and the rear skeleton.

4. A bionic butterfly ornithopter according to claim 3, wherein the front skeleton comprises a first skeleton strip, a second skeleton strip and a third skeleton strip, the first skeleton strip and the second skeleton strip extend along the direction far away from the fuselage, one ends of the first skeleton strip and the second skeleton strip, which are close to the fuselage, are respectively inserted into the fixing holes of two adjacent cylinders, the first skeleton strip is positioned in front of the second skeleton strip, a plurality of third skeleton strips are sequentially and alternately distributed along the extending direction of the first skeleton, the third skeleton strips are connected with the first skeleton strip and the second skeleton strip, and the front film is bonded with the first skeleton strip, the second skeleton strip and the third skeleton strip.

5. A bionic butterfly ornithopter as claimed in claim 3, wherein the rear skeleton comprises a fourth skeleton strip, two ends of the fourth skeleton strip are respectively inserted into the fixing holes of two adjacent columns to enclose a second ornithopter region, and the rear film is adhered to the fourth skeleton strip and covers the second ornithopter region.

6. A bionic butterfly ornithopter as recited in claim 1, wherein the drive mechanism comprises a first steering engine and a second steering engine symmetrically disposed about the central axis of the fuselage, the first steering engine and the second steering engine are fixed to the fuselage, the power output of the first steering engine is connected to the wing connector of the first wing near the end of the fuselage, and the power output of the second steering engine is connected to the wing connector of the second wing near the end of the fuselage.

7. A bionic butterfly ornithopter as recited in claim 6, further comprising a rudder mount, wherein the rudder mount is embedded on the fuselage and is provided with a first mounting location and a second mounting location that are symmetrical to a central axis of the fuselage, wherein the first and second steering engines are respectively fixed in the first and second mounting locations.

8. The bionic butterfly ornithopter of claim 7, wherein a long cavity and a fixing cavity for fixing the steering engine seat are formed in the airframe, the long cavity is formed in the central axis direction of the airframe and located behind the fixing cavity, a connecting strip is arranged in the long cavity, and one end of the connecting strip extends into the fixing cavity to be connected with the steering engine seat.