CN209938949U

CN209938949U - Detachable combined type unmanned aerial vehicle

Info

Publication number: CN209938949U
Application number: CN201821948364.2U
Authority: CN
Inventors: 龙莹
Original assignee: Nanchong Chuangnian Three-Dimensional Technology Co Ltd
Current assignee: Nanchong Chuangnian Three-Dimensional Technology Co Ltd
Priority date: 2018-11-23
Filing date: 2018-11-23
Publication date: 2020-01-14
Anticipated expiration: 2028-11-23

Abstract

The utility model discloses a detachable combined type unmanned aerial vehicle, fuselage including unmanned aerial vehicle, the fuselage head is equipped with the power thick liquid, the fuselage both sides are equipped with the detachable stationary vane, stationary vane middle part position is equipped with the rotor that is used for providing VTOL power, still include the pluggable electrical connection structure who lays on the stationary vane, this electrical connection structure includes the fuselage cable that the control panel in the fuselage was drawn forth and buries the wing cable in the wing under the stationary vane underground, the end of drawing forth of fuselage cable is connected with first connector, the end of drawing forth of wing cable is connected with the second connector, first connector is connected with the detachable ground electricity of second connector, the other end of wing cable is connected with the motor of rotor and other electrical component electricity in the stationary vane. The utility model discloses a but lay the electric connection structure of the plug-in on the stationary vane and can swiftly dismantle the separation with the stationary vane from the fuselage both sides, avoid it to receive the control of cable, the transportation of the compound unmanned aerial vehicle of being convenient for and the dismantlement after the equipment are maintained.

Description

Detachable combined type unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned air vehicle technique field, concretely relates to detachable combined type unmanned aerial vehicle that convenient transportation was carried.

Background

The combined type unmanned aerial vehicle is an unmanned aerial vehicle with a rotor and a fixed horn, and has the unmanned aerial vehicle with vertical take-off and landing and long-time stagnation cruising at the same time. For the combined type unmanned aerial vehicle, the combined type unmanned aerial vehicle has the characteristics of long cruising time and convenience in take-off, but due to the existence of the fixed wings, the occupied space is overlarge during ground transportation or cluster throwing, and the transportation cost is increased. At present, the composite unmanned aerial vehicle is mainly characterized in that the fixed wings are fixed on two sides of the body, and power supply cables for connecting the rotor steering engine on the fixed wings and the control panel in the body are integrally arranged on the fixed wings, so that the composite unmanned aerial vehicle is not convenient to disassemble, assemble and maintain.

SUMMERY OF THE UTILITY MODEL

In order to solve the defect that above-mentioned technique exists, the utility model provides a detachable combined type unmanned aerial vehicle that convenient transportation was carried.

The utility model discloses realize that the technical scheme that above-mentioned technological effect adopted is:

the utility model provides a detachable combined type unmanned aerial vehicle, includes unmanned aerial vehicle's fuselage, the head of fuselage is equipped with the power thick liquid, the both sides of fuselage are equipped with the detachable stationary vane, the middle part position of stationary vane is equipped with the rotor that is used for providing VTOL power, its characterized in that still including laying pluggable's electrical connection structure on the stationary vane, this electrical connection structure includes certainly fuselage cable that control panel in the fuselage was drawn forth and bury underground in wing cable in the lower flank of stationary vane, the end of drawing forth of fuselage cable is connected with first connector, the end of drawing forth of wing cable is connected with the second connector, first connector with the detachable ground electricity of second connector is connected, the other end of wing cable with the motor of rotor and other electrical component electricity in the stationary vane are connected.

Preferably, in the above detachable combined type unmanned aerial vehicle, two sides of the fuselage are fixed with fixed wing roots which are integrally formed with the fuselage, and the corresponding fixed wings are detachably connected to the fixed wing roots on the corresponding sides through connecting pieces.

Preferably, in the above detachable combined type unmanned aerial vehicle, the fixed wing includes a solid main wing plate made of polyseleon PP1120HF, a wire embedding groove for embedding the wing cable is provided on a lower wing surface of the main wing plate, and a protective cover plate is further wrapped on the lower wing surface of the main wing plate.

Preferably, in foretell a detachable combined type unmanned aerial vehicle, the main pterygoid lamina with the terminal surface that fixed wing root is connected is equipped with and is used for accommodating first connector with the chamber that holds of second connector, hold the chamber with the buried line groove intercommunication.

Preferably, in the above detachable composite type unmanned aerial vehicle, at least two mutually isolated first wire slots penetrating through the first connector are arranged in the first connector, a first lead wire slot is formed in a slot wall of the first wire slot, a slot opening of the first wire slot is larger than a slot opening of the first lead wire slot, a wire pressing block for pressing an access end of the body cable in the first lead wire slot is arranged in the first wire slot, at least two mutually isolated second wire slots penetrating through the second connector are arranged in the second connector, a second lead wire slot is formed in a slot wall of the second wire slot, a slot opening of the second wire slot is larger than a slot opening of the second lead wire slot, a wire pressing block for pressing an access end of the wing cable in the second lead wire slot is arranged in the second wire slot, and a first electric contact terminal is arranged on an outer end surface of the first wire slot, and a second electric contact terminal which is oppositely matched with the first electric contact terminal is arranged on the outer end face of the second wire slot, the first electric contact terminal is electrically connected with the access end of the fuselage cable, and the second electric contact terminal is electrically connected with the access end of the wing cable.

Preferably, in foretell combined type unmanned aerial vehicle of detachable, be equipped with the interlock board that can press the perk on the second connector, the interlock end of interlock board is equipped with the interlock tooth, be equipped with on the first connector with the spacing step of interlock tooth complex.

The utility model has the advantages that: the utility model discloses a but lay the electric connection structure of the plug-in on the stationary vane and can swiftly dismantle the separation with the stationary vane from the fuselage both sides, avoid it to receive the control of cable, the transportation of the compound unmanned aerial vehicle of being convenient for and the dismantlement after the equipment are maintained.

Drawings

Fig. 1 is a schematic perspective view of the present invention;

fig. 2 is a top view of the present invention;

fig. 3 is a schematic partial cross-sectional view of a stationary vane according to the present invention;

fig. 4 is a schematic view of a partial structure of the fixed wing and the fixed wing root of the present invention;

fig. 5 is a perspective view of the electrical connection structure of the present invention;

fig. 6 is a schematic view illustrating the snap-fit of the first connector and the second connector according to the present invention;

FIG. 7 is a schematic view of the structure of FIG. 6 at another viewing angle;

fig. 8 is a schematic structural diagram of fig. 6 at another viewing angle.

Detailed Description

In order to make the invention more comprehensible, the invention is further described with reference to the accompanying drawings and specific examples.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.

Please refer to fig. 1 and fig. 2, an embodiment of the present invention provides a detachable composite unmanned aerial vehicle, which includes an unmanned aerial vehicle body 1, a power slurry (not shown) is disposed at the head of the unmanned aerial vehicle body 1, and an empennage (not shown) is disposed at the tail of the unmanned aerial vehicle body 1. The both sides of fuselage 1 are equipped with detachable stationary vane 2, and the middle part position of stationary vane 2 is equipped with the rotor 3 that is used for providing VTOL power. Wherein, as the utility model discloses an improve, this compound unmanned aerial vehicle still includes the pluggable electrical connection structure who lays on stationary wing 2, and this electrical connection structure includes fuselage cable 7 that the control panel in fuselage 1 was drawn forth and buries the wing cable 8 in the lower flank of stationary wing 2 underground. The end of drawing forth of fuselage cable 7 is connected with first connector 5, and the end of drawing forth of wing cable 8 is connected with second connector 6, and first connector 5 is connected with the detachable ground electricity of second connector 6. The other end of the wing cable 8 is electrically connected to the motor of the rotor 3 and other electrical components in the fixed wing 2. As an illustration of an embodiment, the other electrical component in the fixed wing 2 is a servomotor for controlling a deceleration flap (not shown) at the trailing edge of the fixed wing 2.

In some embodiments, fixed wing roots 11 integrally formed with the fuselage 1 are fixed to the left and right sides of the fuselage 1, and the corresponding fixed wing 2 is detachably connected to the fixed wing root 11 on the corresponding side by a connecting member 4. The fixed wing 2 comprises a solid main wing plate 21 made of the poly sialon PP1120HF, the poly sialon PP1120HF is light in weight, the weight of the airplane body can be reduced, the cruising ability is improved, the shock and noise are reduced, the impact resistance of the whole airplane is improved, the interference of a metal material on a remote signal is reduced, and the process for integrally forming the poly sialon PP1120HF is simple. The solid main wing plate 21 can properly increase the weight of the fixed wing 2, and the shake of the unmanned aerial vehicle caused by the excessively light and thin wing during flying is avoided.

In some embodiments, as shown in fig. 3 and 4, the lower wing surface of the main wing panel 21 is provided with a wire burying groove 22 for burying the wing cable 8, and the fixed wing root 11 is also correspondingly provided with a wire groove (not shown) for leading out the fuselage cable 7. When a sensor is arranged in the fixed wing 2 or a signal wire is required to be connected with a motor of the rotor 3, the signal wire can also be accessed through the wire embedding groove 22 of the lower wing surface of the main wing plate 21. The lower wing surface of the main wing plate 21 is further coated with a protective cover plate 23, when maintenance is needed, the wire embedding groove 22 can be exposed by removing the protective cover plate 23, and maintenance of the wing cable 8 is facilitated. The protective cover plate 23 may be fixed to the main wing plate 21 in the form of edge bayonet, or may be fixed to the main wing plate 21 by screws. The main wing plate 21 is provided with a receiving cavity 24 for receiving the first connector 5 and the second connector 6 on one end surface connected with the fixed wing root 11, and the receiving cavity 24 is communicated with the wire burying groove 22. After the first connecting head 5 and the second connecting head 6 are connected, they are placed into the accommodating cavity 24, and then the fixed wing 2 is fixedly connected with the fixed wing root 11 through the connecting piece 4.

In some embodiments, as shown in fig. 5 to 8, the first connector 5 and the second connector 6 are electrically connected in a plugging manner. At least two mutually isolated first wire grooves 51 penetrating the first connecting head 5 are arranged in the first connecting head 5, a first wire groove 52 is formed in the wall of each first wire groove 51, and the machine body cable 7 is arranged in the first wire groove 52. The notch of the first wire groove 51 is larger than the notch of the first lead wire groove 52, and a wire pressing block (not shown in the figure) for pressing the access end of the body cable 7 in the first lead wire groove 52 is arranged in the first wire groove 51, so that the access end of the body cable 7 is prevented from being pulled out. At least two mutually isolated second wire grooves 61 penetrating through the second connector 6 are formed in the second connector 6, a second wire leading groove 62 is formed in the wall of each second wire groove 61, and the wing cable 8 is arranged in the second wire leading groove 62. The notch of the second wire groove 61 is larger than the notch of the second wire guiding groove 62, and a wire pressing block (not shown in the figure) for pressing the access end of the wing cable 8 in the second wire guiding groove 62 is arranged in the second wire groove 61, so that the access end of the wing cable 8 is prevented from being pulled out. The outer end face of the first wire slot 51 is provided with a first electric contact terminal 521, the outer end face of the second wire slot 61 is provided with a second electric contact terminal 621 oppositely matched with the first electric contact terminal 521, the first electric contact terminal 521 is electrically connected with the access end of the body cable 7, and the second electric contact terminal 621 is electrically connected with the access end of the wing cable 8. When the first connector 5 is inserted into the second connector 6, the first electrical contact terminal 521 abuts against the second electrical contact terminal 621, and the two are electrically connected.

In some embodiments, the second connector 6 is provided with a snap-in plate 63 that can be pressed and tilted, the snap-in end of the snap-in plate 63 is provided with snap teeth 631, and the first connector 5 is provided with a limit step 53 that is matched with the snap teeth 631. In order to facilitate the insertion or extraction of the first connector 5 engaged with the second connector 6, two opposite sidewalls of the first connector 5 are provided with anti-slip portions 54, the anti-slip portions 54 are provided with anti-slip teeth, the anti-slip portions 54 are triangular structures, and the anti-slip portions 54 have pressing slopes in the insertion direction and the extraction direction, respectively.

To sum up, the utility model discloses a lay the connection structure of pluggable formula on the stationary vane but swiftly dismantle the separation with the stationary vane from the fuselage both sides, avoid it to receive the control of cable, the transportation of the compound unmanned aerial vehicle of being convenient for and the dismantlement after the equipment are maintained.

The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, but rather is described in the foregoing embodiments and the description with reference to the principles of the invention and that various changes and modifications may be made without departing from the spirit and scope of the invention, and it is intended that all such changes and modifications fall within the scope of the invention as claimed, which is defined by the claims appended hereto and their equivalents.

Claims

1. The utility model provides a detachable combined type unmanned aerial vehicle, which is characterized in that, includes unmanned aerial vehicle's fuselage (1), the head of fuselage (1) is equipped with power thick liquid, the both sides of fuselage (1) are equipped with detachable stationary vane (2), the middle part position of stationary vane (2) is equipped with rotor (3) that are used for providing VTOL power, still including laying pluggable electrical connection structure on stationary vane (2), this electrical connection structure includes fuselage cable (7) of drawing forth from the control panel in fuselage (1) and buries underground in wing cable (8) in the lower flank of stationary vane (2), the end of drawing forth of fuselage cable (7) is connected with first connector (5), the end of drawing forth of wing cable (8) is connected with second connector (6), first connector (5) with the detachable ground electricity of second connector (6) is connected, the other end of the wing cable (8) is electrically connected with the motor of the rotor wing (3) and other electrical components in the fixed wing (2).

2. A detachable composite unmanned aerial vehicle according to claim 1, wherein the two sides of the fuselage (1) are fixed with fixed wing roots (11) integrally formed with the fuselage (1), and the corresponding fixed wings (2) are detachably connected to the fixed wing roots (11) on the corresponding sides through connecting pieces (4).

3. A demountable composite drone according to claim 2, wherein the fixed wing (2) comprises a solid main wing panel (21) made of polyseleon PP1120HF, the lower wing surface of the main wing panel (21) being provided with a slot (22) for embedding the wing cable (8), the lower wing surface of the main wing panel (21) being further covered with a protective cover plate (23).

4. A demountable composite drone according to claim 3, characterised in that the main wing panel (21) is provided, on one end face connected to the fixed wing root (11), with a housing cavity (24) for housing the first connector (5) and the second connector (6), the housing cavity (24) communicating with the slot (22).

5. The detachable composite unmanned aerial vehicle of claim 1, wherein the first connector (5) is provided with at least two mutually isolated first wire slots (51) penetrating through the first connector (5), the wall of each first wire slot (51) is provided with a first wire guiding slot (52), the opening of each first wire slot (51) is larger than the opening of each first wire guiding slot (52), the first wire slot (51) is provided with a wire pressing block for pressing the access end of the fuselage cable (7) in the first wire guiding slot (52), the second connector (6) is provided with at least two mutually isolated second wire slots (61) penetrating through the second connector (6), the wall of each second wire slot (61) is provided with a second wire guiding slot (62), and the opening of each second wire slot (61) is larger than the opening of each second wire guiding slot (62), be equipped with in second wire casing (61) and be used for with the incoming end of wing cable (8) compresses tightly line ball piece in second lead wire casing (62), the outer terminal surface of first wire casing (51) is equipped with first electric contact terminal (521), the outer terminal surface of second wire casing (61) be equipped with first electric contact terminal (521) complex second electric contact terminal (621) relatively, first electric contact terminal (521) with the incoming end electricity of fuselage cable (7) is connected, second electric contact terminal (621) with the incoming end electricity of wing cable (8) is connected.

6. The detachable composite unmanned aerial vehicle of claim 5, wherein the second connector (6) is provided with a snap-in plate (63) which can be pressed and tilted, the snap-in end of the snap-in plate (63) is provided with snap-in teeth (631), and the first connector (5) is provided with a limit step (53) which is matched with the snap-in teeth (631).