CN113911333A - Novel unmanned aerial vehicle - Google Patents

Abstract

The invention provides a novel unmanned aerial vehicle which comprises a vehicle body, wherein a duck wing is arranged on each of the left side and the right side of the front part of the vehicle body, an aileron is arranged on the rear side of the duck wing, and a propeller for flying the unmanned aerial vehicle is arranged on the front side of the duck wing. When the novel unmanned aerial vehicle is implemented by adopting a design scheme without a main wing and a vertical wing, the novel unmanned aerial vehicle can be used as a rotor unmanned aerial vehicle; when the novel unmanned aerial vehicle is implemented by adopting a design scheme with a main wing and a vertical wing, the novel unmanned aerial vehicle can serve as a fixed-wing unmanned aerial vehicle; the ailerons and the propellers are arranged on the canard wings, so that when the unmanned aerial vehicle takes off and lands, the ailerons and the propellers can be kept at a certain distance from the ground; in the taking-off and landing process, the ailerons and the propellers are far away from the ground, so that the blocking effect of the ground on the air flow is effectively reduced, the attitude control effect of the ailerons and the propellers on the unmanned aerial vehicle is favorably improved, and the taking-off and landing stability of the unmanned aerial vehicle can be improved.

Description

Novel unmanned aerial vehicle

Technical Field

The invention relates to a novel unmanned aerial vehicle.

Background

The many rotor unmanned aerial vehicle of current tradition (like four rotors, six rotors, eight rotor unmanned aerial vehicle) is symmetrical overall arrangement basically, and the storage box is usually length width nearly equals, and area is big, also is not favorable to taking off and land and catch the recovery in finite space.

In the process, the conversion efficiency of converting fuel oil heat energy into electric energy is low, the energy loss is serious, and the efficiency is far inferior to that of a helicopter with a rotor wing directly driven by an engine; however, helicopter mechanical structure is complicated, and the potential safety hazard is greater than many rotor unmanned aerial vehicle far away.

The applicant filed a chinese utility model patent on 12/04/2021 with the patent names: a main wing of the novel vertical type vertical take-off and landing fixed wing unmanned aerial vehicle (application number: 2021207430684) is arranged on two sides of the tail of a vehicle body, an aileron and a propeller of the unmanned aerial vehicle are respectively arranged on the rear side and the front side of the main wing, and in the take-off and landing process of the unmanned aerial vehicle, when the tail of the unmanned aerial vehicle is close to the ground, airflow is blocked by the ground, deflection control of the aileron on the airflow is influenced, so that the attitude control of the unmanned aerial vehicle is inefficient, and the control stability is seriously influenced; furthermore, the ailerons are arranged at the rear side of the main wing, and generate negative lift force in the process of flat flight, so that the overall aerodynamic efficiency of the unmanned aerial vehicle is low, and the load and the cruising ability of the unmanned aerial vehicle are influenced; the applicant filed a chinese utility model patent on 2021, month 07 and day 01, with the patent names: an unmanned aerial vehicle automatic retraction base station (application number: 2021214918974); the unmanned aerial vehicle taking-off and landing device mainly comprises a box body, a taking-off and landing mechanism and an active capturing device, wherein the box body is used for storing the unmanned aerial vehicle, the taking-off and landing mechanism is used for lifting the active capturing device in the box body, and the active capturing device mainly realizes the taking-off and landing capturing of the unmanned aerial vehicle; when unmanned aerial vehicle takes off and land, for preventing that the aileron or the screw of unmanned aerial vehicle afterbody from colliding with the box lateral wall, before taking off and land, need utilize the mechanism of taking off and land to rise the initiative trapping apparatus and exceed the box top, then, carry out unmanned aerial vehicle's transmission again or descend and catch, the mechanism of taking off and land and initiative trapping apparatus structure and control process in the above-mentioned box are complicated.

Disclosure of Invention

The invention aims to provide a novel unmanned aerial vehicle which can be used as a rotor unmanned aerial vehicle and a vertical take-off and landing fixed wing unmanned aerial vehicle, and has multiple functions;

when rotor unmanned aerial vehicle used, only fuselage both sides duck wing and screw are flat structure because of it, and it is little to store the long and narrow space of taking up an area of box, if store the box and regard as the recovery platform of taking off and land simultaneously, can realize taking off and land the recovery independently entirely in finite space, have great practical value. Meanwhile, in order to improve the sailing time and the load carrying capacity, the propellers on the two sides of the canard wing can be directly driven by two oil-driven engines, the mechanical structure is simple and reliable, and the energy efficiency is greatly improved compared with an oil power generation mode.

When the vertical take-off and landing fixed wing unmanned aerial vehicle is used, the ailerons and the propellers of the unmanned aerial vehicle are arranged on the canard wings at the two sides of the front part of the unmanned aerial vehicle body, so that the ailerons and the propellers can be ensured to keep a certain distance with the ground when the unmanned aerial vehicle takes off and lands; in the taking-off and landing process, the ailerons and the propellers are far away from the ground, so that the blocking effect of the ground on airflow is effectively reduced, the attitude control effect of the ailerons and the propellers on the unmanned aerial vehicle is further improved, and the taking-off and landing stability of the unmanned aerial vehicle can be improved; the unmanned aerial vehicle taking-off and landing stability is improved, and then the unmanned aerial vehicle capturing mechanism and the related control program are conveniently and subsequently simplified.

The technical scheme adopted by the invention for solving the technical problems is as follows: the utility model provides a novel unmanned aerial vehicle, includes the organism the anterior left and right sides of organism respectively sets up a duck wing the rear side of duck wing is provided with the aileron the front side of duck wing is provided with the screw for the unmanned aerial vehicle flight.

Preferably, a main wing is respectively arranged at the left side and the right side of the rear part of the machine body, and at least one vertical wing is arranged at the upper side of the rear part of the machine body.

Preferably, the main wing comprises a fixed main wing and a foldable main wing, the foldable main wing can automatically swing, fold and fix towards the abdomen direction of the body through a first driving mechanism, and can automatically unfold and fix; the vertical wings comprise fixed vertical wings and foldable vertical wings, and the foldable vertical wings can automatically swing, fold, retract and fix towards the main wings through a second driving mechanism and can automatically unfold and fix.

Furthermore, the lower side of the joint of the foldable main wing and the fixed main wing is hinged through at least one damping hinge, and the first driving mechanism is arranged at the joint of the foldable main wing and the fixed main wing; the outer side of the butt joint of the fixed vertical wing and the foldable vertical wing is hinged through at least one damping hinge, and the second driving mechanism is arranged at the butt joint of the fixed vertical wing and the foldable vertical wing.

Further, the first driving mechanism comprises a first steering engine, and a first steering engine arm of the first steering engine is fixedly connected with the lower side wall of the foldable main wing; the second driving mechanism comprises a second steering engine, and a second steering engine arm of the second steering engine is fixedly connected with the outer side wall of the foldable vertical wing.

Preferably, the main wings comprise a fixed main wing and a foldable main wing, the foldable main wing can swing and fold towards the abdomen of the body in a manual mode, and can be unfolded and fixed through a first connecting mechanism; the vertical wings comprise fixed vertical wings and foldable vertical wings, the foldable vertical wings can be folded and folded towards the main wings in a manual mode, the foldable vertical wings can be unfolded and fixed through a second connecting mechanism, and the abdomen of the body is provided with a supporting rod capable of automatically swinging.

Further, the lower side of the joint of the foldable main wing and the fixed main wing is hinged through at least one damping hinge, and the first connecting mechanism comprises at least one first buckle which is arranged on the upper side of the joint of the foldable main wing and the fixed main wing; the outer side of the butt joint of the fixed vertical wing and the foldable vertical wing is hinged through at least one damping hinge, and the second connecting mechanism comprises at least one second buckle which is arranged on the inner side of the butt joint of the fixed vertical wing and the foldable vertical wing.

Preferably, the main wing is an integral non-foldable part, a support rod capable of automatically swinging is arranged on the belly of the aircraft body, the support rod is opened for supporting during takeoff and landing, and the support rod is folded and attached to the belly of the aircraft body during flat flight.

The invention has the beneficial effects that:

1. after this novel unmanned aerial vehicle adopted the design that does not have main wing and perpendicular wing to implement, this unmanned aerial vehicle acts as rotor unmanned aerial vehicle promptly and uses because only two screws that are the in-line distribution for its unmanned aerial vehicle's thickness is narrower, is convenient for realize then that unmanned aerial vehicle retrieves in the box, and the box structure size that corresponds is narrow, thereby the transportation and the carrying of the box of also being convenient for. Furthermore, if two oil-driven engines are adopted to directly drive the propellers, compared with a helicopter, the mechanical mechanism is simple and reliable, and compared with an oil power generation mode, the energy efficiency is greatly improved;

2. on a traditional canard layout fixed wing aircraft, an aileron is arranged on a main wing, and generates downward negative lift force to keep pitching aerodynamic balance in the process of flat flying, so that the lift force efficiency is reduced, and the load and the endurance of the unmanned aerial vehicle are influenced; when the unmanned aerial vehicle is used as a fixed-wing unmanned aerial vehicle, the ailerons are arranged on the canard wings, and the canard wings and the main wings all generate positive lift in the process of flying flatly, so that the lift efficiency in the process of flying flatly is effectively improved, and the load and the cruising ability are increased.

3. When the unmanned aerial vehicle is used as a vertical take-off and landing fixed wing unmanned aerial vehicle, the ailerons and the propellers of the unmanned aerial vehicle are arranged on the canard wings at two sides of the head of the unmanned aerial vehicle, and then when the unmanned aerial vehicle takes off and lands, the ailerons and the propellers can keep a certain distance from the ground, so that the blocking effect of the ground on airflow can be effectively reduced, the control effect of the ailerons and the propellers on the airflow is improved, and the stability of the unmanned aerial vehicle in the take-off and landing process is improved; the stability of the unmanned aerial vehicle in the taking-off and landing process is improved, so that the unmanned aerial vehicle can accurately and stably land; the unmanned aerial vehicle can accurately and stably land, so that the unmanned aerial vehicle capturing mechanism and the related control program are conveniently and subsequently simplified.

4. When this unmanned aerial vehicle used as VTOL fixed wing unmanned aerial vehicle, unmanned aerial vehicle's perpendicular wing and main wing can be folded, have reduced unmanned aerial vehicle's the occupation space of depositing, and the carrying and the transportation of being convenient for unmanned aerial vehicle also do benefit to and reduce the box structural dimension who is used for unmanned aerial vehicle to take off and land.

5. When this unmanned aerial vehicle used as VTOL fixed wing unmanned aerial vehicle, unmanned aerial vehicle's perpendicular wing and main wing can realize folding automatically to reduce unmanned aerial vehicle take off and land in-process area of catching by wind by a wide margin, improve wind resistance, be favorable to increasing control stability and realize accurate descending and catch.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are part of the preferred embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.

Fig. 1 is a schematic view of the overall structure of a main wing and a vertical wing of an unmanned aerial vehicle during flat flight, wherein the main wing and the vertical wing have an automatic folding function;

FIG. 2 is a side view of the overall structure of an embodiment of the main wing and vertical wing of the UAV with automatic folding function in a flat flight;

FIG. 3 is a schematic view showing the folding state of the main wing and the vertical wing of the UAV during the taking off and landing in the box body, according to an embodiment of the UAV with an automatic folding function;

FIG. 4 is a schematic view of the main wing and vertical wing of the UAV with automatic folding function in folded state during taking off and landing on the ground;

FIG. 5 is an enlarged view taken at A in FIG. 1;

FIG. 6 is an enlarged view of FIG. 2 at B;

fig. 7 is a schematic view of the overall structure of the unmanned aerial vehicle when flying in a flat plane, in which the main wing and the vertical wing are manually folded;

FIG. 8 is a side view of the overall structure of a drone in flat flight with manual folding of the main and vertical wings;

FIG. 9 is a schematic view of an embodiment of the unmanned aerial vehicle with manually foldable main wings and vertical wings in a vertical take-off and landing state;

FIG. 10 is an enlarged view at C of FIG. 7;

FIG. 11 is an enlarged view of FIG. 7 at D;

FIG. 12 is an enlarged view at E in FIG. 7;

FIG. 13 is an enlarged view at F of FIG. 8;

fig. 14 is a schematic view of the overall structure of an embodiment in which neither the main wing nor the vertical wing of the drone is foldable;

FIG. 15 is a schematic view of the overall structure of an embodiment of the drone without the main wing and the vertical wing;

FIG. 16 is a schematic view of an embodiment of the drone with vertical wings only and no main wings, taken off and landing on the ground;

FIG. 17 is a schematic view of an embodiment of a drone with only vertical wings and no main wing during vertical flight;

fig. 18 is a schematic structural view of an embodiment in which a main wing of an unmanned aerial vehicle is connected with a body in a plug-in manner;

in the figure: 1 body, 2 canard wings, 21 propellers, 3 main wings, 31 first fixed main wings, 311 first grooves, 32 first foldable main wings, 321 second grooves, 33 second fixed main wings, 34 second foldable main wings, 35 non-foldable main wings, 36 third main wings, 4 vertical wings, 41 first fixed vertical wings, 411 third grooves, 42 first foldable vertical wings, 421 fourth grooves, 43 second fixed vertical wings, 44 second foldable vertical wings, 45 non-foldable main wings, 46 third vertical wings, 47 fourth vertical wings, 5 ailerons, 6 first steering engines, 61 first rudder arms, 7 second steering engines, 71 second rudder arms, 8 first supporting rods, 9 second supporting rods, 10 third supporting rods, 101 first damping hinges, 102 second damping hinges, 201 first buckles, 202 second buckles, 301 capturing mechanisms, 401 supporting crosses.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the specific embodiments and accompanying drawings 1 to 18, and it is obvious that the described embodiments are only a part of the preferred embodiments of the present invention, and not all embodiments. Those skilled in the art can make similar modifications without departing from the spirit of the invention, and therefore the invention is not limited to the specific embodiments disclosed below.

The invention provides a novel unmanned aerial vehicle, which comprises a machine body 1, wherein a duck wing 2 is respectively arranged at the left side and the right side of the front part of the machine body 1, an aileron 5 is arranged at the rear side of the duck wing 2, a propeller 21 for flying the unmanned aerial vehicle is arranged at the front side of the duck wing 2, and the specific structure and the design method of the duck wing 2 are all common knowledge in the field, so that the detailed description of the arrangement mode of the duck wing 2 on the machine body 1 is not provided; the setting and swing control of the ailerons 5 are mature technologies in the field, so the specific setting mode of the ailerons 5 on the canard wing 2 and the swing control mode of the ailerons 5 by a flight control system are not described in detail herein; the propeller 21 is a commonly used component in the field of unmanned aerial vehicle flight, the high-speed rotation of the propeller provides power for the unmanned aerial vehicle flight, and the power assembly matched with the propeller 21 and the specific installation mode of the power assembly on the canard wing 2 are well known in the art and will not be described in detail herein.

In practical application, this unmanned aerial vehicle can a tractor serves several purposes, both can regard as rotor unmanned aerial vehicle to use, also can work as the fixed wing unmanned aerial vehicle of VTOL and use. Act as rotor unmanned aerial vehicle and use when unmanned aerial vehicle because only two are screw 21 that the in-line distributes for its unmanned aerial vehicle's thickness is narrower, is convenient for realize then that unmanned aerial vehicle retrieves in the box, and the box structure size that corresponds is narrow, thereby the transportation and the carrying of the box of also being convenient for. Further, if two oil-driven engines are adopted to directly drive the propeller 21, compared with a helicopter, the mechanical mechanism is simple and reliable, and compared with an oil power generation mode, the energy efficiency is greatly improved. When the unmanned aerial vehicle is used as a vertical take-off and landing fixed wing unmanned aerial vehicle, the ailerons 5 and the propellers 21 are both arranged on the canard wings 2 on two sides of the head of the machine body 1, and then when the unmanned aerial vehicle takes off and lands, the ailerons 5 and the propellers 21 can keep a certain distance from the ground, so that the blocking effect of the ground on airflow can be effectively reduced, the control effect of the ailerons 5 and the propellers 21 on the airflow is improved, and the stability of the unmanned aerial vehicle in the take-off and landing process is improved; the stability of the unmanned aerial vehicle in the taking-off and landing process is improved, so that the unmanned aerial vehicle can accurately and stably land; the unmanned aerial vehicle can accurately and stably land, so that the unmanned aerial vehicle capturing mechanism and related control programs can be conveniently and simply designed in the follow-up process; further, the ailerons 5 are arranged on the canard wing 2, and in the process of the flat flight, the canard wing 2 and the main wing both generate positive lift force, so that the lift force efficiency in the flat flight process is effectively improved, and the load and the cruising ability are increased.

When this unmanned aerial vehicle uses as rotor unmanned aerial vehicle, it has two kinds of embodiments, and the concrete implementation of an embodiment (as shown in fig. 15) is: the rear part of the machine body 1 is not provided with a main wing and a vertical wing, only one supporting cross 401 is arranged, the supporting cross 401 is fixedly connected with the machine body 1, and the machine body 1 can stably take off and land on the ground by using the support of the supporting cross 401 in the taking off and landing process. Another embodiment (shown in fig. 16 and 17) is as follows: the rear portion of organism 1 is provided with at least one third vertical wing 46, set up one at the belly of organism 1 and can realize wobbling third bracing piece 10 automatically, third bracing piece 10 descends or when subaerial takeoff at unmanned aerial vehicle, expand to the belly outside automatically, so that subaerial and the support of the unmanned aerial vehicle of the joint realization of third vertical wing 46, in the unmanned aerial vehicle process of flying perpendicularly, third bracing piece 10 is automatic to the inboard packing up of belly (as shown in fig. 17), so as to improve unmanned aerial vehicle stability in the flight process, the technical scheme that third bracing piece 10 realized automatic wobbling is the well-known technique in the art, so here, do not do the detailed description to the concrete structure, the working method and the control process of the drive mechanism who drives the wobbling of third bracing piece 10.

When the unmanned aerial vehicle is used as a vertical take-off and landing fixed-wing unmanned aerial vehicle, a main wing and a vertical wing are arranged on a machine body 1, one specific embodiment of the main wing and the vertical wing arranged on the machine body 1 is shown in fig. 18, two fourth vertical wings 47 are arranged on two sides of the rear part of the machine body 1, and two third main wings 36 are in plug-in connection with corresponding positions of the rear part of the machine body 1 in a plug-in manner; in the above embodiment, two third main wings 36 can be detached from the airframe 1, so that the unmanned aerial vehicle can be directly used as a rotor unmanned aerial vehicle, and the application of the unmanned aerial vehicle is flexible.

The main wing and the vertical wing can also be connected by adopting a connection mode of being an integral part with the machine body 1, and on the basis that the main wing and the vertical wing are both connected by adopting an integral part with the machine body 1, the main wing and the vertical wing have the following specific combination structure forms: when the main wing has a folding function, the vertical wing has the folding function or does not have the folding function; when the main wing does not have the folding function, the vertical wing has the folding function or does not have the folding function.

When perpendicular wing and main wing can be folded, reduced unmanned aerial vehicle's the occupation space of depositing, be convenient for unmanned aerial vehicle carry and transport also do benefit to and reduce the box structural dimension who is used for unmanned aerial vehicle to take off and land. In the embodiment that the main wing and the vertical wing can be folded, the two embodiments are included, and in one embodiment, the main wing and the vertical wing have an automatic folding function; in another specific embodiment, the main wing and the vertical wing both adopt a manual mode to realize the folding function.

The specific implementation manner of the specific embodiment that the main wing and the vertical wing both have the automatic folding function is as follows: the main wings comprise fixed main wings and foldable main wings, and the foldable main wings can automatically swing, fold, retract and fix towards the abdomen direction of the machine body through a first driving mechanism and can automatically unfold and fix; the vertical wings comprise fixed vertical wings and foldable vertical wings, and the foldable vertical wings can automatically swing, fold, retract and fix towards the main wings through a second driving mechanism and can automatically unfold and fix. Specifically, as shown in fig. 1 to 6, the main wing has the following specific embodiments: the main wing 3 comprises a first fixed main wing 31 and a first foldable main wing 32, the first foldable main wing 32 can realize automatic swinging, folding and folding towards the belly direction of the machine body 1 through a first driving mechanism and is folded and fixed, and can realize automatic unfolding and fixing, in particular, the lower side of the butt joint of the first foldable main wing 32 and the first fixed main wing 31 is hinged through at least one damping hinge 101, the first driving mechanism is arranged at the joint of the first foldable main wing 32 and the first fixed main wing 31, the first driving mechanism is used for the rotation driving and fixing of the first foldable main wing 32, that is, after the first driving mechanism drives the first foldable main wing 32 to be folded in place, through the positioning function of the first driving mechanism, the first foldable main wing 32 can be always kept in a folded state and cannot be automatically unfolded due to the action of external force; after the first driving mechanism drives the first foldable main wing 32 to be unfolded in place, the first foldable main wing 32 can be always kept in an unfolded state through the positioning function of the first driving mechanism, and cannot be swung and folded under the action of external force; through the driving and positioning functions of the first driving mechanism, stable unfolding and folding of the first foldable main wing 32 are ensured, and accurate control of the posture of the unmanned aerial vehicle is facilitated; the first driving mechanism is specifically implemented as follows: the first driving mechanism is a first steering engine 6, in order to facilitate the installation of the first steering engine 6 at the joint of the first fixed main wing 31 and the first foldable main wing 32 and ensure that the installation of the first steering engine 6 does not affect the unfolding and folding of the first foldable main wing 32, a first groove 311 is arranged at the corresponding position of the first fixed main wing 31, a second groove 321 corresponding to the first groove 311 is arranged at the corresponding position of the first foldable main wing 32, the first steering engine 6 is fixedly installed in the first groove 311 and the second groove 321, the rotating shaft of the first steering engine arm 61 of the first steering engine 6 is coaxial with the rotating shaft of the corresponding damping hinge 101, the first steering engine arm 61 is coaxial with the damping hinge 101, so that the first steering engine arm 61 can smoothly drive the first foldable main wing 32 to smoothly rotate around the axis of the damping hinge 101, the first steering engine arm 61 is fixedly connected with the lower side wall of the first foldable main wing 32, and then the first foldable main wing 32 and the first rudder horn 61 are ensured to rotate synchronously, and then the accurate control of the folding and unfolding positions of the first foldable main wing 32 can be realized. The specific implementation mode of the vertical wing is as follows: the vertical wing 4 comprises a first fixed vertical wing 41 and a first foldable vertical wing 42, the first foldable vertical wing 42 can automatically swing, fold and fix towards the main wing 3 through a second driving mechanism, and can automatically unfold and fix; specifically, the outer side of the joint of the first fixed vertical wing 41 and the first foldable vertical wing 42 is hinged by at least one damping hinge 101, the second driving mechanism is arranged at the joint of the first fixed vertical wing 41 and the first foldable vertical wing 42, and the second driving mechanism is used for driving and fixing the first foldable vertical wing 42 in a rotating manner; namely, after the second driving mechanism drives the first foldable vertical wing 42 to be folded in place, the first foldable vertical wing 42 can be always kept in a folded state through the positioning function of the second driving mechanism, and the first foldable vertical wing 42 cannot be automatically unfolded due to the action of external force; after the second driving mechanism drives the first foldable vertical wing 42 to be unfolded in place, the first foldable vertical wing 42 can be always kept in an unfolded state through the positioning function of the second driving mechanism, and cannot be folded due to the action of external force in a swinging manner; through the driving and positioning functions of the second driving mechanism, the stable unfolding and folding of the first foldable vertical wing 42 are ensured, and the accurate control of the posture of the unmanned aerial vehicle is facilitated; the specific implementation mode of the second driving mechanism is as follows: the second driving mechanism is a second steering engine 7, in order to facilitate the installation of the second steering engine 7 at the joint of the first fixed vertical wing 41 and the first foldable vertical wing 42 and ensure that the installation of the second steering engine 7 does not affect the unfolding and folding of the first foldable vertical wing 42, a third groove 411 is arranged at the corresponding position of the first fixed vertical wing 41, a fifth groove corresponding to the third groove 411 is arranged at the corresponding position of the first foldable vertical wing 42, the second steering engine 7 is fixedly installed in the third groove 411 and the fifth groove, the rotating shaft of a second steering engine arm 71 of the second steering engine 7 is coaxial with the rotating shaft of the corresponding damping hinge 101, the second steering engine arm 71 is coaxial with the damping hinge 101, so that the second steering engine arm 71 can smoothly drive the first foldable vertical wing 42 to smoothly rotate around the axis of the damping hinge 101, and the second steering engine arm 71 is fixedly connected with the outer side wall of the first foldable vertical wing 42, specifically, the second rudder horn 71 is fixedly clamped in the fourth groove 421 formed in the first foldable vertical wing 42, and the second rudder horn 71 is fixedly connected with the first foldable vertical wing 42, so that the first foldable vertical wing 42 and the second rudder horn 71 are ensured to synchronously rotate, and the folding and unfolding positions of the first foldable vertical wing 42 can be accurately controlled.

In the embodiment where the first foldable main wing 32 and the first foldable vertical wing 42 both have the automatic folding function, when the unmanned aerial vehicle directly falls into the capturing mechanism 301 in a box, the first foldable main wing 32 rotates by 180 degrees, and the first foldable vertical wing 42 rotates by 90 degrees, so as to realize complete folding, which is beneficial for the unmanned aerial vehicle to enter the box, and meanwhile, is beneficial for the capturing mechanism 301 to keep the unmanned aerial vehicle in an upright state; when the unmanned aerial vehicle directly falls into the ground, the first foldable vertical wing 42 is kept unfolded and not folded, the two first foldable main wings 32 rotate by 90 degrees, and the unmanned aerial vehicle realizes the erection on the ground by utilizing the support of the first foldable vertical wing 42 and the two first foldable main wings 32. First collapsible main wing 32 and first collapsible vertical wing 42 have automatic folding function, take off perpendicularly at unmanned aerial vehicle and descend the in-process perpendicularly for first collapsible main wing 32 and first collapsible vertical wing 42 are in fold condition, can effectively reduce unmanned aerial vehicle's area of catching wind, improve the wind resistance ability, are favorable to increasing control stability and realize accurate descending and catch.

The specific implementation manner of the specific embodiment that the main wing and the vertical wing both adopt a manual mode to realize the folding function is as follows: the main wings comprise fixed main wings and foldable main wings, the foldable main wings can swing, fold and retract towards the belly direction of the machine body in a manual mode, and can be unfolded and fixed through a first connecting mechanism; the fixed vertical wing and the foldable vertical wing can swing and fold in the direction of the main wing in a manual mode, can be unfolded and fixed through a second connecting mechanism, and a supporting rod capable of automatically swinging is arranged on the belly of the machine body. Specifically, as shown in fig. 7 to 13, the main wing includes a second fixed main wing 33 and a second foldable main wing 34, the lower side of the joint of the second foldable main wing 34 and the second fixed main wing 33 is hinged by at least one second damping hinge 102, and the second foldable main wing 34 is rotated by the rotational connection function of the second damping hinge 102, so as to realize the folding function of the main wing; the first connecting mechanism comprises at least one first buckle 201, the first buckle 201 is arranged at the upper side of the joint of the second foldable main wing 34 and the second fixed main wing 33, and the stable connection of the second foldable main wing 34 and the second fixed main wing 33 can be ensured by using the connecting and fixing function of the first buckle 201, so that the main wings keep the unfolding state; the vertical wings comprise a second fixed vertical wing 43 and a second foldable vertical wing 44, the outer side of the butt joint of the second fixed vertical wing 43 and the second foldable vertical wing 44 is hinged through at least one second damping hinge 102, and the rotation of the second foldable vertical wing 44 is realized through the rotation connection function of the second damping hinge 102, so that the folding function of the vertical wings is realized; the second connecting mechanism comprises at least one second buckle 202, the second buckle 202 is arranged at the inner side of the joint of the second fixed vertical wing 43 and the second foldable vertical wing 44, and the stable connection of the second foldable vertical wing 44 and the second fixed vertical wing 43 can be ensured by using the connecting and fixing function of the second buckle 202, so that the vertical wings are kept in the unfolded state; in the above embodiment, in order to ensure that the unmanned aerial vehicle keeps a vertical state when landing on the ground and taking off on the ground, here, a first supporting rod 8 capable of automatically swinging is arranged on the abdomen of the machine body 1, and the working principle and the implementation form of the first supporting rod 8 are completely the same as those of the third supporting rod 10. In the above-mentioned embodiment of the unmanned aerial vehicle, before the unmanned aerial vehicle takes off, the first buckle 201 and the second buckle 202 are used to respectively realize the unfolding and fixing of the second foldable main wing 34 and the second foldable vertical wing 44, the first support rod 8 is used to realize the vertical support of the unmanned aerial vehicle, and then, the subsequent take-off operation can be performed; when the unmanned aerial vehicle needs to be folded, the first supporting rod 8 is automatically folded, then the first buckle 201 and the second buckle 202 are respectively opened, and then the second foldable main wing 34 and the second foldable vertical wing 44 are manually rotated, folded and folded.

In practical application, the main wing also can be a whole non-folding part, and when the main wing is a whole non-folding part, for realizing that unmanned aerial vehicle keeps erectting subaerial, here, set up one at the belly of organism 1 and can realize wobbling second bracing piece 9 automatically, the theory of operation and the realization form of second bracing piece 9 are the same with the theory of operation and the realization form of above-mentioned third bracing piece 10 completely. When the main wing is an integral non-foldable part, a specific implementation of a specific embodiment of the unmanned aerial vehicle is as follows: the main wing and the fixed wing of the unmanned aerial vehicle do not have folding functions, and the structural form is as shown in fig. 14, specifically: unmanned aerial vehicle includes organism 1 the anterior left and right sides of organism 1 respectively sets up a duck wing 2 the rear side and the front side of duck wing 2 are provided with aileron 5 and screw 21 respectively the rear portion left and right sides of organism 1 respectively set up one main wing 35 that can not fold the rear portion upside of organism 1 is provided with at least one perpendicular wing 45 that can not fold, and second bracing piece 9 sets up in organism 1 belly side.

In addition to the technical features described in the specification, the technology is known to those skilled in the art.

While the preferred embodiments and examples of the present invention have been described in detail, it will be apparent to those skilled in the art that the invention is not limited thereto, and that various changes and modifications may be made without departing from the spirit and scope of the invention.

Claims (8)

1. The utility model provides a novel unmanned aerial vehicle, includes the organism, characterized by the anterior left and right sides of organism respectively sets up a duck wing the rear side of duck wing is provided with the aileron the front side of duck wing is provided with the screw for the unmanned aerial vehicle flight.

2. The novel unmanned aerial vehicle as claimed in claim 1, wherein a main wing is provided on each of the left and right sides of the rear portion of the body, and at least one vertical wing is provided on the upper side of the rear portion of the body.

3. The novel unmanned aerial vehicle as claimed in claim 2, wherein the main wing comprises a fixed main wing and a foldable main wing, and the foldable main wing can automatically swing, fold, retract and fix in the abdomen direction of the unmanned aerial vehicle body through a first driving mechanism and can automatically unfold and fix; the vertical wings comprise fixed vertical wings and foldable vertical wings, and the foldable vertical wings can automatically swing, fold, retract and fix towards the main wings through a second driving mechanism and can automatically unfold and fix.

4. The novel unmanned aerial vehicle as claimed in claim 3, wherein the lower side of the joint of the foldable main wing and the fixed main wing is hinged through at least one damping hinge, and the first driving mechanism is arranged at the joint of the foldable main wing and the fixed main wing; the outer side of the butt joint of the fixed vertical wing and the foldable vertical wing is hinged through at least one damping hinge, and the second driving mechanism is arranged at the butt joint of the fixed vertical wing and the foldable vertical wing.

5. The novel unmanned aerial vehicle as claimed in claim 4, wherein the first driving mechanism comprises a first steering engine, and a first steering engine arm of the first steering engine is fixedly connected with a lower side wall of the foldable main wing; the second driving mechanism comprises a second steering engine, and a second steering engine arm of the second steering engine is fixedly connected with the outer side wall of the foldable vertical wing.

6. The novel unmanned aerial vehicle as claimed in claim 2, wherein the main wings comprise a fixed main wing and a foldable main wing, the foldable main wing can swing and fold towards the belly of the unmanned aerial vehicle body in a manual mode, and can be unfolded and fixed through a first connecting mechanism; the vertical wings comprise fixed vertical wings and foldable vertical wings, the foldable vertical wings can be folded and folded towards the main wings in a manual mode, the foldable vertical wings can be unfolded and fixed through a second connecting mechanism, and the abdomen of the body is provided with a supporting rod capable of automatically swinging.

7. The novel unmanned aerial vehicle as claimed in claim 6, wherein the lower side of the joint of the foldable main wing and the fixed main wing is hinged through at least one damping hinge, the first connecting mechanism comprises at least one first buckle, and the first buckle is arranged on the upper side of the joint of the foldable main wing and the fixed main wing; the outer side of the butt joint of the fixed vertical wing and the foldable vertical wing is hinged through at least one damping hinge, and the second connecting mechanism comprises at least one second buckle which is arranged on the inner side of the butt joint of the fixed vertical wing and the foldable vertical wing.

8. The novel unmanned aerial vehicle as claimed in claim 2, wherein the main wing is an integral non-foldable part, and a support rod capable of automatically swinging is arranged at the belly of the body.

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