CN216887216U - Vertical take-off and landing jettisonable combined unmanned aerial vehicle - Google Patents

Abstract

The utility model discloses a vertical take-off and landing throwing combined unmanned aerial vehicle, which comprises a sleeving mechanism and four small unmanned aerial vehicles which are identical in structure and can be separated from each other, wherein the sleeving mechanism is detachably connected with the small unmanned aerial vehicles, the small unmanned aerial vehicles are centrosymmetric about the sleeving mechanism, the sleeving mechanism comprises a base, a connecting disc is arranged on the base, supporting rods are arranged in the connecting disc, a duct motor is arranged on the supporting rods, a duct fan is arranged on the duct motor, the small unmanned aerial vehicle comprises a machine head and a machine body, wings are arranged on the machine body, a rocker arm rod is arranged at the tail part of the machine body, a driving motor is arranged on the rocker arm rod, and propellers are arranged on the driving motor.

Description

Vertical take-off and landing jettisonable combined unmanned aerial vehicle

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a vertical take-off and landing combined unmanned aerial vehicle capable of launching.

Background

The unmanned aerial vehicle generally comprises a fixed-wing unmanned aerial vehicle and a rotor unmanned aerial vehicle, the fixed-wing unmanned aerial vehicle has certain requirements on the field, and the rotor unmanned aerial vehicle is not limited by the field, but the rotor unmanned aerial vehicle has small flying speed and is inconvenient for long-time endurance, so that the utility model aims to provide the vertical take-off and landing jettisonable combined unmanned aerial vehicle which overcomes the problems by combining the advantages of the fixed-wing unmanned aerial vehicle and the rotor unmanned aerial vehicle.

SUMMERY OF THE UTILITY MODEL

The utility model aims to solve the technical problems in the prior art and provides a vertical take-off and landing throwing combined unmanned aerial vehicle.

In order to realize the purpose, the technical scheme provided by the utility model is as follows: the utility model provides a but combined type unmanned aerial vehicle can be put in VTOL, includes that cup joint mechanism and four structures are the same and the small unmanned aerial vehicle of alternate segregation, cup joint mechanism with small unmanned aerial vehicle can dismantle the connection, small unmanned aerial vehicle about cup joint mechanism central symmetry, cup joint mechanism includes the base, be provided with the connection pad on the base, be provided with the bracing piece in the connection pad, be provided with the duct motor on the bracing piece, be provided with the duct fan on the duct motor, small unmanned aerial vehicle includes aircraft nose, fuselage, be provided with the wing on the fuselage, the fuselage afterbody is provided with the rocking arm pole, be provided with driving motor on the rocking arm pole, the last screw that is provided with of driving motor.

Preferably, a steering engine is arranged on the airplane body and connected with the wings.

Preferably, the length of the wing is from the wing mounting position to the tail of the fuselage.

Preferably, a clamping groove is formed in the machine head, a clamping ring is arranged on the connecting disc, and the clamping ring is connected with the clamping groove in a matched mode.

The utility model has the beneficial effects that:

according to the utility model, four small unmanned aerial vehicles are combined and connected through the sleeving mechanism, and the propeller at the tail part of the body of the small unmanned aerial vehicle and the ducted fan in the sleeving mechanism provide upward lifting force to vertically take off and land.

Drawings

The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the description serve to explain the utility model and not to limit the utility model.

FIG. 1 is an isometric view of the present invention;

fig. 2 is an isometric view of a front flight of an individual drone;

FIG. 3 is an isometric view of the connection device;

FIG. 4 is a partially enlarged view of a steering engine;

fig. 5 is a cross-sectional view of a handpiece card slot.

The attached drawings are marked as follows:

1-machine head 2-machine body 3-wing 4-propeller 5-connecting disc 6-base 7-ducted fan 8-rocker arm 9-driving motor 10-support rod 11-snap ring 12-ducted motor 13-steering engine 14-neck.

Detailed Description

Reference will now be made in detail to the present preferred embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to like elements throughout.

In the description of the present invention, it should be understood that the orientation or positional relationship referred to in the description of the orientation, such as the upper, lower, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.

In the description of the present invention, the meaning of a plurality of means is one or more, the meaning of a plurality of means is two or more, and larger, smaller, larger, etc. are understood as excluding the number, and larger, smaller, inner, etc. are understood as including the number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.

In the description of the present invention, unless otherwise explicitly limited, terms such as arrangement, installation, connection and the like should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above terms in the present invention in combination with the specific contents of the technical solutions.

Referring to fig. 1 to 5, in a preferred embodiment of the present invention, a vertical take-off and landing deployable combined unmanned aerial vehicle includes a socket mechanism and four mutually separable small unmanned aerial vehicles having the same structure, the socket mechanism is detachably connected to the small unmanned aerial vehicles, the small unmanned aerial vehicles are centrally symmetrical with respect to the socket mechanism, the socket mechanism includes a base 6, a connection disc 5 is disposed on the base 6, a support rod 10 is disposed in the connection disc 5, a duct motor 12 is disposed on the support rod 10, a duct fan 7 is disposed on the duct motor 12, the duct fan 7 provides a lifting force for the socket mechanism, when the present invention is raised to a certain height, the socket mechanism can be separated from the small unmanned aerial vehicle, and then the socket mechanism is retracted, the small unmanned aerial vehicle includes a machine head 1 and a machine body 2, the machine body 2 is provided with wings 3, the tail part of the machine body 2 is provided with a rocker arm rod 8, the rocker arm rod 8 is provided with a driving motor 9, and the driving motor 9 is provided with a propeller 4.

The propeller 4 can deflect through the rocker arm rod 8 connected to the tail part of the machine body 2, when the unmanned aerial vehicle vertically takes off, the propeller 4 deflects to a vertical position through controlling the rocker arm rod 8, the propeller 4 provides upward lifting force for the unmanned aerial vehicle, after the unmanned aerial vehicle ascends to a certain height, the small unmanned aerial vehicle is separated from the sleeving mechanism, namely when the unmanned aerial vehicle is thrown in the air, the small unmanned aerial vehicle controls the wings 3 to be unfolded, the propeller 4 tilts to a horizontal distance, and the small unmanned aerial vehicle independently provides front flying power for the small unmanned aerial vehicle.

According to the utility model, four small unmanned aerial vehicles are combined and connected through the sleeve mechanism, and the propeller 4 at the tail part of the body 2 of the small unmanned aerial vehicle and the ducted fan 7 in the sleeve mechanism provide upward lifting force to enable the small unmanned aerial vehicle to take off and land vertically.

As a preferred embodiment of the present invention, it may also have the following additional technical features:

in the embodiment, the fuselage 2 is provided with the steering engine 13, the steering engine 13 is connected with the wings 3, the steering engine 13 is used for controlling the wings 13 to be folded and unfolded, when the airplane vertically takes off, the wings 3 are folded on the upper surface of the fuselage 2, and when the airplane independently flies in the air, the steering engine 13 controls the wings 3 to be horizontally unfolded.

In this embodiment, the length of the wing 3 is the length from the installation position of the wing 3 to the tail of the fuselage 2, so that the wing 3 is just attached to the upper surface of the fuselage 2 when being folded.

In this embodiment, be provided with draw-in groove 14 on the aircraft nose 1, draw-in groove 14 be used for with unmanned aerial vehicle with the coupling mechanism is connected, be provided with snap ring 11 on the connection pad 5, snap ring 11 with draw-in groove 14 cooperation is connected.

The above additional technical features can be freely combined and used in superposition by those skilled in the art without conflict.

The above description is only a preferred embodiment of the present invention, and the technical solutions that achieve the objects of the present invention by basically the same means are all within the protection scope of the present invention.

Claims (4)

1. The utility model provides a but vertical take-off and landing puts in combination formula unmanned aerial vehicle which characterized in that: but including socket joint mechanism and four structure the same and alternate segregation's unmanned aerial vehicle, socket joint mechanism with unmanned aerial vehicle can dismantle the connection, unmanned aerial vehicle about socket joint mechanism central symmetry, socket joint mechanism includes base (6), be provided with connection pad (5) on base (6), be provided with bracing piece (10) in connection pad (5), be provided with duct motor (12) on bracing piece (10), be provided with duct fan (7) on duct motor (12), unmanned aerial vehicle includes aircraft nose (1), fuselage (2), be provided with wing (3) on fuselage (2), fuselage (2) afterbody is provided with rocking arm pole (8), be provided with driving motor (9) on rocking arm pole (8), be provided with screw (4) on driving motor (9).

2. The VTOL jettisonable combined UAV of claim 1, wherein: the aircraft body (2) is provided with a steering engine (13), and the steering engine (13) is connected with the wings (3).

3. The VTOL jettisonable combined UAV of claim 1, wherein: the length of the wing (3) is the length from the installation position of the wing (3) to the tail part of the fuselage (2).

4. The VTOL jettisonable combined UAV of claim 1, wherein: the head is characterized in that a clamping groove (14) is formed in the head (1), a clamping ring (11) is arranged on the connecting disc (5), and the clamping ring (11) is connected with the clamping groove (14) in a matched mode.

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