CN214566119U

CN214566119U - Dual-form unmanned aerial vehicle applying folding wings and coaxial double-propeller power module

Info

Publication number: CN214566119U
Application number: CN202023083433.8U
Authority: CN
Inventors: 李昊天
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-12-18
Filing date: 2020-12-18
Publication date: 2021-11-02
Anticipated expiration: 2030-12-18

Abstract

The application discloses a dual-form unmanned aerial vehicle applying folding wings and a coaxial double-propeller power module, which comprises rear end covers, front end covers, a folding mechanism and a flying mechanism, wherein the rear end covers, the front end covers, the folding mechanism and the flying mechanism are arranged on two sides of an aircraft shell; the folding mechanism comprises a folding wing, a connecting shaft, a transmission bevel gear and an output bevel gear; the flying mechanism includes a first motor housing, a connection platform, and a second motor housing. The unmanned aerial vehicle control system has the advantages that the coaxial double-oar power module is used for providing vector power of the unmanned aerial vehicle, the unmanned aerial vehicle control system has higher flight efficiency and load performance, power and control required by the stability of the aircraft are provided in the hovering mode, the coaxial double-oar power module is used for pushing and controlling the aircraft, and therefore the unmanned aerial vehicle is controlled to be in the stable state in the hovering or flying mode; utilize folding wing to provide the required lift of aircraft, folding wing can be convenient folding accomodate, and the fuselage is more regular folding, portable and transportation greatly improve the voyage, the ability of staying empty and the functionality of aircraft.

Description

Dual-form unmanned aerial vehicle applying folding wings and coaxial double-propeller power module

Technical Field

The application relates to an unmanned aerial vehicle, specifically is a dual form unmanned aerial vehicle of wing and coaxial double oar power module is folded in application.

Background

Unmanned aerial vehicles are commonly known as unmanned airplanes, unmanned aerial vehicles, unmanned combat airplanes, and bee-type machines; the airplane is a wide range of remote control aircrafts without the need of a pilot to board and pilot, and is generally in particular to an unmanned reconnaissance airplane of the military.

Unmanned aerial vehicle installs equipment such as autopilot, program control device, and ground, naval vessel are gone up or mother's aircraft remote control station personnel pass through equipment such as radar, carry out tracking, location, remote control, telemetering measurement and digital transmission to it, and unmanned aerial vehicle carries the heavy capability poor at present, and the time of endurance is short, is difficult to accomplish a series of actions such as take-off, investigation when unmanned aerial vehicle reconnaissance, and unmanned aerial vehicle is difficult to be in steady state and effective lift when reconnaissance. Therefore, a dual-form unmanned aerial vehicle using folding wings and a coaxial double-oar power module is provided for solving the problems.

Disclosure of Invention

A dual-form unmanned aerial vehicle applying folding wings and coaxial double-propeller power modules comprises rear end covers, front end covers, a folding mechanism and a flying mechanism, wherein the rear end covers, the front end covers, the folding mechanism and the flying mechanism are arranged on two sides of an aircraft shell;

the folding mechanism comprises a folding wing, a connecting shaft, a transmission bevel gear and an output bevel gear, the folding wing is fixedly connected with the transmission bevel gear through the connecting shaft, the connecting shaft is rotatably connected with the side wall of the aircraft shell, the output bevel gear is rotatably connected with the inside of the aircraft shell, and the output bevel gear is meshed with the transmission bevel gear;

flight mechanism includes first motor casing, connecting platform and second motor casing, first motor casing passes through connecting platform and second motor casing fixed connection, first motor casing is inside to rotate with first end and is connected, first end surface is equipped with first screw, the inside and second end of second motor rotate to be connected, just second end surface is equipped with the second screw.

Further, aircraft casing cross-section is square structure, aircraft casing four corners all is equipped with the chamfer, aircraft casing four sides all is equipped with folding wing, every folding wing all with aircraft casing surface laminating is connected.

Furthermore, aircraft casing one end and rear end cap fixed connection, modules such as investigation, data transmission and power supply are equipped with inside the rear end cap.

Furthermore, the other end of the aircraft shell is provided with a front end cover, and the front end cover is rotatably connected with the first motor shell through a pin shaft.

Furthermore, four transmission bevel gears are arranged inside the aircraft shell, the four transmission bevel gears are distributed in the aircraft shell in a centrosymmetric mode, and the four bevel gears are located on the periphery of the output bevel gear respectively.

Further, the inside of the first motor shell is respectively penetrated and rotatably connected with the inside of a second motor shell and a second end head, the second end head and the first end head are coaxial and rotatably connected with each other, and the rotating directions of the second end head and the first end head are opposite.

The beneficial effect of this application is: the application provides a two form unmanned aerial vehicle of wing and coaxial double oar power module are folded in application that has high-efficient flight function and load performance and can improve the ability of staying empty.

Drawings

In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without inventive exercise.

FIG. 1 is a schematic overall perspective view of an embodiment of the present application;

FIG. 2 is a schematic front view of an embodiment of the present application;

FIG. 3 is a schematic illustration of a top view of the interior of an aircraft shell according to an embodiment of the present application;

fig. 4 is a schematic view of a portion a of fig. 1 according to an embodiment of the present disclosure.

In the figure: 1. aircraft casing, 2, rear end cap, 3, front end cap, 4, folding wing, 5, connecting axle, 6, transmission bevel gear, 7, output bevel gear, 8, round pin axle, 9, first motor casing, 10, connecting platform, 11, second motor casing, 12, first end, 13, first screw, 14, second end, 15, second screw.

Detailed Description

In order to make the technical solutions better understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only partial embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It should be understood that the data so used may be interchanged under appropriate circumstances such that embodiments of the application described herein may be used. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.

In this application, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings. These terms are used primarily to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to a particular orientation or to be constructed and operated in a particular orientation.

Moreover, some of the above terms may be used to indicate other meanings besides the orientation or positional relationship, for example, the term "on" may also be used to indicate some kind of attachment or connection relationship in some cases. The specific meaning of these terms in this application will be understood by those of ordinary skill in the art as appropriate.

Furthermore, the terms "mounted," "disposed," "provided," "connected," and "sleeved" are to be construed broadly. For example, it may be a fixed connection, a removable connection, or a unitary construction; can be a mechanical connection, or an electrical connection; may be directly connected, or indirectly connected through intervening media, or may be in internal communication between two devices, elements or components. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.

Referring to fig. 1-4, a dual-mode unmanned aerial vehicle using folding wings and coaxial double-oar power modules comprises a rear end cover 2, a front end cover 3, a folding mechanism and a flying mechanism, which are arranged on two sides of an aircraft shell 1;

the folding mechanism comprises a folding wing 4, a connecting shaft 5, a transmission bevel gear 6 and an output bevel gear 7, wherein the folding wing 4 is fixedly connected with the transmission bevel gear 6 through the connecting shaft 5, the connecting shaft 5 is rotatably connected with the side wall of the aircraft shell 1, the output bevel gear 7 is rotatably connected with the inside of the aircraft shell 1, and the output bevel gear 7 is meshed with the transmission bevel gear 6;

flight mechanism includes first motor casing 9, connection platform 10 and second motor casing 11, first motor casing 9 passes through connection platform 10 and second motor casing 11 fixed connection, inside and the first end 12 of first motor casing rotate to be connected, first end 12 surface is equipped with first screw 13, inside and the second end 14 rotation of second motor are connected, just second end 14 surface is equipped with second screw 15.

The section of the aircraft shell 1 is of a square structure, chamfers are arranged on four corners of the aircraft shell 1, folding wings 4 are arranged on four sides of the aircraft shell 1, and each folding wing 4 is attached to the surface of the aircraft shell 1; one end of the aircraft shell 1 is fixedly connected with a rear end cover 2, and modules such as a detection module, a data transmission module, a power source module and the like are arranged in the rear end cover 2; the other end of the aircraft shell 1 is provided with a front end cover 3, and the front end cover 3 is rotationally connected with a first motor shell 9 through a pin shaft 8; four transmission bevel gears 6 are arranged inside the aircraft shell 1, the four transmission bevel gears 6 are distributed in the aircraft shell 1 in a centrosymmetric manner, and the four bevel gears are respectively positioned around an output bevel gear 7; the interior of the first motor housing 9 is respectively penetrated and rotatably connected with the interior of a second motor housing 11 and a second end 14, the second end 14 and the first end 12 are coaxial and rotatably connected with each other, and the second end 14 and the first end 12 rotate in opposite directions.

When the folding wing type aircraft is used, electrical elements appearing in the application are externally connected with a power supply and a control switch, modules for detection, data transmission, power supply and the like are installed in a rear end cover 2, when a folding wing 4 rotates, a motor arranged in an aircraft shell 1 drives an output bevel gear 7 to rotate, the output bevel gear 7 drives four transmission bevel gears 6 to simultaneously rotate, the four transmission bevel gears drive the folding wing 4 to rotate, the four folding wing 4 rotates on four sides of the aircraft shell 1 through a connecting shaft 5, the folding wing 4 is unfolded or stored, when the folding wing 4 is unfolded, a horizontal cruise mode is entered, the suspended suspension performance is improved, and in a folded state, the folding wing type aircraft can be attached to the aircraft shell 1 on four sides, the occupied space is further reduced, and the flight in a hovering mode is not affected; meanwhile, when the folding wings 4 are unfolded, the lifting force can be rapidly provided;

the first motor shell 9 and the second motor shell 11 are fixedly connected through a connecting platform 10, the first motor shell 9 is used for driving the first end head 12 and the first propeller 13 to rotate, the second motor shell 11 is used for driving the second end head 14 and the second propeller 15 to rotate, meanwhile, the first end head 12 and the second end head 14 coaxially rotate, the vector power of the unmanned aerial vehicle is provided by using a coaxial double-propeller power module, provides the power and control required by the stability of the airplane in the hovering mode, and realizes the fine angle adjustment of the first motor shell 9 and the second motor shell 11 through a vector power propulsion system arranged in the front end cover 3 during the control, the angle adjustment is realized through the pin shaft 8, the moment control of the aircraft in the rolling direction is provided by utilizing the differential control of the two motors, therefore, the aircraft can be controlled to obtain good stability in hovering and flying states, and meanwhile, the flying mode can be switched at any time.

The application has the advantages that:

1. the unmanned aerial vehicle control system has the advantages that the coaxial double-propeller power module is used for providing vector power of the unmanned aerial vehicle, has larger rotor wing area and higher flight efficiency and load performance, provides power and control required by the stability of the unmanned aerial vehicle in a hovering mode, and completes pushing and controlling of the unmanned aerial vehicle by the coaxial double-propeller power module, so that the unmanned aerial vehicle is controlled to be in a stable state in the hovering or flight mode;

2. this application utilizes folding wing to provide the required lift of aircraft, and folding wing can be convenient folding accomodate, does not have the comparatively complicated horn folding locking mechanical system of many rotor crafts, and it is more regular to fold the fuselage, and portable and transportation greatly improve the journey, the ability of staying empty and the functionality of aircraft.

The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. The utility model provides an application folding wing and coaxial double-oar power module's bimorph unmanned aerial vehicle which characterized in that: the aircraft comprises rear end covers (2) and front end covers (3) on two sides of an aircraft shell (1), a folding mechanism and a flying mechanism;

the folding mechanism comprises a folding wing (4), a connecting shaft (5), a transmission bevel gear (6) and an output bevel gear (7), the folding wing (4) is fixedly connected with the transmission bevel gear (6) through the connecting shaft (5), the connecting shaft (5) is rotatably connected with the side wall of the aircraft shell (1), the output bevel gear (7) is rotatably connected with the inside of the aircraft shell (1), and the output bevel gear (7) is meshed with the transmission bevel gear (6);

flight mechanism includes first motor casing (9), connection platform (10) and second motor casing (11), first motor casing (9) are through connection platform (10) and second motor casing (11) fixed connection, first motor casing (9) are inside to be connected with first end (12) rotation, first end (12) surface is equipped with first screw (13), the inside second end (14) rotation of second motor is connected, just second end (14) surface is equipped with second screw (15).

2. The dual-configuration drone applying the folding wings and the coaxial double-oar power module according to claim 1, characterized in that: aircraft casing (1) cross-section is square structure, aircraft casing (1) four corners all is equipped with the chamfer, aircraft casing (1) four sides all is equipped with folding wing (4), every folding wing (4) all with aircraft casing (1) surface laminating is connected.

3. The dual-configuration drone applying the folding wings and the coaxial double-oar power module according to claim 1, characterized in that: aircraft casing (1) one end and rear end cap (2) fixed connection, module such as investigation, data transmission and power supply are equipped with in rear end cap (2).

4. The dual-configuration drone applying the folding wings and the coaxial double-oar power module according to claim 1, characterized in that: the aircraft is characterized in that a front end cover (3) is arranged at the other end of the aircraft shell (1), and the front end cover (3) is rotatably connected with a first motor shell (9) through a pin shaft (8).

5. The dual-configuration drone applying the folding wings and the coaxial double-oar power module according to claim 1, characterized in that: the four transmission bevel gears (6) are arranged in the aircraft shell (1), the four transmission bevel gears (6) are distributed in the aircraft shell (1) in a central symmetry mode, and the four bevel gears are located on the periphery of the output bevel gear (7) respectively.

6. The dual-configuration drone applying the folding wings and the coaxial double-oar power module according to claim 1, characterized in that: the inner part of the first motor shell (9) is respectively penetrated and rotatably connected with the inner parts of a second motor shell (11) and a second end head (14), the second end head (14) and the first end head (12) are coaxial and are mutually rotatably connected, and the rotating directions of the second end head (14) and the first end head (12) are opposite.