CN110641713A

CN110641713A - Jet unmanned aerial vehicle's rotating nozzle

Info

Publication number: CN110641713A
Application number: CN201911050171.4A
Authority: CN
Inventors: 万勇
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-10-31
Filing date: 2019-10-31
Publication date: 2020-01-03

Abstract

The invention discloses a rotary nozzle of a jet unmanned aerial vehicle, which comprises a fixed pipe, a first pipeline, a second pipeline and a tail pipe, wherein the fixed pipe is a straight pipe, two end surfaces of the fixed pipe are vertical end surfaces perpendicular to the axis of the fixed pipe, the first pipeline comprises a first inclined end surface and a straight end surface which is nested and connected with the fixed pipe, the outer side wall of the fixed pipe is provided with a first motor, the output shaft of the first motor is parallel to the axis of the fixed pipe, the outer edge of the straight end surface on the first pipeline is provided with a first gear ring, the first motor is meshed and driven to the first gear ring through a first gear, and the second pipeline comprises a second inclined end surface and a third inclined end surface. The invention can realize 90-degree turning and multi-angle deflection motion of the nozzle, can realize vertical lifting and flexible turning of the unmanned aerial vehicle, and has high precision and good reliability through meshing transmission of the motor and the gear.

Description

Jet unmanned aerial vehicle's rotating nozzle

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to a rotary nozzle of a jet unmanned aerial vehicle.

Background

The prior art jet-propelled unmanned aerial vehicle mostly can take off only after sliding on a runway for a long distance, the field is limited and large, and the use is inconvenient.

Disclosure of Invention

The invention aims to solve the technical problem of providing a rotary nozzle of a jet unmanned aerial vehicle, and aims to solve the problems that most of the jet unmanned aerial vehicles in the prior art can take off only after long-distance sliding on a runway, the field is limited greatly, and the use is inconvenient.

In order to solve the technical problem, an embodiment of the present invention provides a rotary nozzle of a jet unmanned aerial vehicle, including a fixed pipe, a first pipe, a second pipe and a tail pipe, where the fixed pipe is a straight pipe, both end surfaces of the fixed pipe are vertical end surfaces perpendicular to an axis of the fixed pipe, the first pipe includes a first oblique end surface and a straight end surface nested and connected with the fixed pipe, a first motor is disposed on an outer side wall of the fixed pipe, an output shaft of the first motor is parallel to the axis of the fixed pipe, a first gear ring is disposed on an outer edge of the straight end surface on the first pipe, the first motor is engaged and driven to the first gear ring through a first gear, the second pipe includes a second oblique end surface and a third oblique end surface, the second pipe is nested and connected to the first oblique end surface of the first pipe through the second oblique end surface, and a second motor is disposed on an outer side wall of the first pipe, the output shaft of second motor is on a parallel with the axis of the first inclined end face of first pipeline, the inclined end face outer fringe of second pipeline is equipped with the second ring gear, the second motor passes through second gear engagement transmission in the second ring gear, the tail pipe includes a shrink port and a fourth inclined end face, the tail pipe passes through the nested third inclined end face department in the second pipeline of fourth inclined end face, be equipped with the third motor on the lateral wall of second pipeline, the output shaft of third motor is on a parallel with the axis of the third inclined end face of second pipeline, the inclined end face outer fringe of fourth of tail pipe is equipped with the third ring gear, the third motor passes through third gear engagement transmission in the third ring gear.

Further, the second inclined end face and the third inclined end face are symmetrically arranged.

Further, the included angle between the second inclined end face and the third inclined end face is 45 degrees.

Further, sliding seals are arranged between the fixed pipe and the first pipeline, between the first pipeline and the second pipeline and between the second pipeline and the tail pipe.

Further, the axis of the contraction port is the same as the axis of the tail pipe.

The technical scheme of the invention has the following beneficial effects:

the invention can realize 90-degree turning and multi-angle deflection motion of the nozzle, can realize vertical lifting and flexible turning of the unmanned aerial vehicle, and has high precision and good reliability through meshing transmission of the motor and the gear.

Drawings

Fig. 1 is a front view structural view of the present invention.

Fig. 2 is a schematic perspective view of the present invention.

Fig. 3 is a first schematic diagram of the explosion structure of the present invention.

Fig. 4 is a schematic diagram of an explosive structure according to the present invention.

Detailed Description

In order to make the technical problems, technical solutions and advantages of the present invention more apparent, the following detailed description is given with reference to the accompanying drawings and specific embodiments.

As shown in fig. 1 to 4, an embodiment of the present invention provides a rotary nozzle of a jet drone, including a fixed pipe 1, a first pipe 2, a second pipe 3 and a tail pipe 4, where the fixed pipe 1 is a straight pipe, both end surfaces of the fixed pipe 1 are vertical end surfaces perpendicular to an axis of the fixed pipe, the first pipe 2 includes a first inclined end surface 201 and a straight end surface 202 nested and connected with the fixed pipe 1, an outer side wall of the fixed pipe 1 is provided with a first motor 5, an output shaft of the first motor 5 is parallel to the axis of the fixed pipe 1, an outer edge of the straight end surface 202 on the first pipe 2 is provided with a first gear ring 6, the first motor 5 is engaged and driven to the first gear ring 6 through a first gear 7, the second pipe 3 includes a second inclined end surface 301 and a third inclined end surface 302, the second pipe 3 is nested and connected to the first inclined end surface 201 of the first pipe 2 through the second inclined end surface 301, be equipped with second motor 8 on the lateral wall of first pipeline 2, the output shaft of second motor 8 is on a parallel with the axis of the first skew terminal surface 201 of first pipeline 2, the second skew terminal surface 301 outer fringe of second pipeline 3 is equipped with second ring gear 9, second motor 8 meshes the transmission in second ring gear 9 through second gear 10, tail pipe 4 includes a shrink port 401 and a fourth skew terminal surface 402, tail pipe 4 is nested in the third skew terminal surface 302 department of second pipeline 3 through fourth skew terminal surface 402, be equipped with third motor 11 on the lateral wall of second pipeline 3, the output shaft of third motor 11 is on a parallel with the axis of the third skew terminal surface 302 of second pipeline 3, the fourth skew terminal surface 402 outer fringe of tail pipe 4 is equipped with third ring gear 12, third motor 11 meshes the transmission in third ring gear 12 through third gear 13.

The second inclined end surface 301 and the third inclined end surface 302 are symmetrically arranged. The included angle between the second inclined end surface 301 and the third inclined end surface 302 is 45 °.

And sliding seals are arranged between the fixed pipe 1 and the first pipeline 2, between the first pipeline 2 and the second pipeline 3 and between the second pipeline 3 and the tail pipe 4.

The axis of the retraction port 401 is the same as the axis of the tailpipe 4.

The whole nozzle is set to be in an initial state when being in a horizontal straight line state, the second motor is started, the second gear is meshed with the second rack to drive the second pipeline and the tail pipe to rotate 180 degrees, the contraction port of the tail pipe can deflect 45 degrees, the third motor is restarted, the third gear is meshed with the third rack to drive the tail pipe to rotate 180 degrees, the contraction port of the tail pipe can deflect 45 degrees, the contraction port of the tail pipe is vertically arranged downwards, and the first motor is started to realize the deflection motion of the contraction port of the tail pipe.

While the foregoing is directed to the preferred embodiment of the present invention, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention as defined in the appended claims.

Claims

1. The rotary nozzle of the jet unmanned aerial vehicle is characterized by comprising a fixed pipe, a first pipeline, a second pipeline and a tail pipe, wherein the fixed pipe is a straight pipe, two end faces of the fixed pipe are vertical end faces perpendicular to the axis of the fixed pipe, the first pipeline comprises a first inclined end face and a straight end face nested and connected with the fixed pipe, a first motor is arranged on the outer side wall of the fixed pipe, an output shaft of the first motor is parallel to the axis of the fixed pipe, a first gear ring is arranged on the outer edge of the straight end face on the first pipeline, the first motor is in meshing transmission with the first gear ring through a first gear, the second pipeline comprises a second inclined end face and a third inclined end face, the second pipeline is nested at the first inclined end face of the first pipeline through the second inclined end face, a second motor is arranged on the outer side wall of the first pipeline, the output shaft of second motor is on a parallel with the axis of the first inclined end face of first pipeline, the inclined end face outer fringe of second pipeline is equipped with the second ring gear, the second motor passes through second gear engagement transmission in the second ring gear, the tail pipe includes a shrink port and a fourth inclined end face, the tail pipe passes through the nested third inclined end face department in the second pipeline of fourth inclined end face, be equipped with the third motor on the lateral wall of second pipeline, the output shaft of third motor is on a parallel with the axis of the third inclined end face of second pipeline, the inclined end face outer fringe of fourth of tail pipe is equipped with the third ring gear, the third motor passes through third gear engagement transmission in the third ring gear.

2. The rotary nozzle of a jet drone according to claim 1, characterized in that the second and third beveled surfaces are symmetrically arranged.

3. The jet drone rotary nozzle of claim 2, wherein the second and third angled end faces are angled at 45 °.

4. The rotary nozzle of a jet drone according to claim 1, characterized in that sliding seals are provided between the fixed pipe and the first pipe, between the first pipe and the second pipe, and between the second pipe and the tailpipe.

5. The rotary nozzle of a jet drone according to claim 1, characterized in that the axis of the convergent port is the same as the axis of the tailpipe.