CN112849390A

CN112849390A - Dual-form unmanned aerial vehicle applying folding wings and coaxial double-propeller power module

Info

Publication number: CN112849390A
Application number: CN202011502679.6A
Authority: CN
Inventors: 李昊天
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-12-18
Filing date: 2020-12-18
Publication date: 2021-05-28

Abstract

The invention 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 structure includes a first motor housing, a connection platform, and a second motor housing. The invention provides the vector power of the unmanned aerial vehicle by using the coaxial double-oar power module, has higher flight efficiency and load performance, provides the power and control required by the stability of the aircraft in the hovering mode, and finishes the pushing and control of the aircraft by using the coaxial double-oar power module, thereby controlling the unmanned aerial vehicle 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 invention relates to an unmanned aerial vehicle, in particular to a dual-form unmanned aerial vehicle applying folding wings and a coaxial double-propeller power module.

Background

The unmanned aerial vehicle is an unmanned aerial vehicle operated by using a radio remote control device and a self-contained program control device, or is completely or intermittently and autonomously operated by a vehicle-mounted computer, can be divided into military use and civil use according to the application field, and has the advantages of small volume, low manufacturing cost, convenient use, low requirement on the use environment and the like compared with the organic aerial vehicle.

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 structure includes first motor casing, connection platform and second motor casing, first motor casing passes through connection 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, the inside modules such as being used for investigation, data transmission and power supply that are equipped with of rear end cap.

Furthermore, the other end of the aircraft shell is provided with or connected 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 invention has the beneficial effects that: the invention provides a dual-form unmanned aerial vehicle which has a high-efficiency flight function and a high load-carrying performance and can improve the air-stagnation capacity and is manufactured by using folding wings and a coaxial double-propeller power module.

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 only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without inventive exercise.

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

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

FIG. 3 is a schematic top view of the interior of an aircraft shell according to one embodiment of the invention;

fig. 4 is a schematic diagram of a partial enlarged structure at a in fig. 1 according to an embodiment of the present invention.

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 of the present invention better understood, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the 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 invention.

It should be noted that the terms "first," "second," and the like in the description and claims of the present invention 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 is to be understood that the data so used may be interchanged under appropriate circumstances in order to facilitate the description of the embodiments of the invention herein. 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 the present invention, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "center", "vertical", "horizontal", "lateral", "longitudinal", and the like indicate an orientation or positional relationship based on the orientation or positional relationship shown in the drawings. These terms are used primarily to better describe the invention and its embodiments and are not intended 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 meanings of these terms in the present invention can be understood by those skilled 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 meanings of the above terms in the present invention can be understood by those of ordinary skill in the art according to specific situations.

It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention 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;

the flight structure 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 9 rotates 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 for detection, data transmission, power source and the like are arranged in the rear end cover 2; the other end of the aircraft shell 1 is provided with or connected 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 shell 9 is respectively penetrated and rotatably connected with the interior of a second motor shell 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 rotating directions of the second end 14 and the first end 12 are opposite.

When the folding wing type aircraft is used, electrical elements in the folding wing type aircraft 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, so that 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 parking performance is improved, and in a folding state, the folding wing type aircraft can be attached to the four sides of the aircraft shell 1, the occupied space is further reduced, and the flight in a hovering mode is not influenced; 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 invention has the advantages that:

1. the unmanned aerial vehicle is provided with vector power by the coaxial double-oar power module, 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 finishes the pushing and control of the unmanned aerial vehicle by the coaxial double-oar power module, so that the unmanned aerial vehicle is controlled in a stable state in the hovering or flight mode;

2. the folding wing is used for providing the lifting force required by the aircraft, the folding wing can be conveniently folded and stored, a complex arm folding and locking mechanism of a multi-rotor aircraft is not needed, the folded aircraft body is more regular, the folding aircraft is convenient to carry and transport, and the range, the air stagnation capacity and the functionality of the aircraft are greatly improved.

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

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);

the flight structure comprises a first motor shell (9), a connecting platform (10) and a second motor shell (11), wherein the first motor shell (9) is fixedly connected with the second motor shell (11) through the connecting platform (10), the inside of the first motor shell (9) is rotatably connected with a first end (12), a first propeller (13) is arranged on the surface of the first end (12), the inside of the second motor is rotatably connected with a second end (14), and a second propeller (15) is arranged on the surface of the second end (14).

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, rear end cap (2) are inside to be equipped with and to be used for modules such as investigation, data transmission and power supply.

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 the other end of the aircraft shell (1) is provided with or connected with a front end cover (3), 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.