CN219584490U

CN219584490U - Unmanned aerial vehicle

Info

Publication number: CN219584490U
Application number: CN202320561896.5U
Authority: CN
Inventors: 杨益见; 代杨仲
Original assignee: Sichuan Sunrain Sign & Display System Co ltd
Current assignee: Sichuan Sunrain Sign & Display System Co ltd
Priority date: 2023-03-21
Filing date: 2023-03-21
Publication date: 2023-08-25
Anticipated expiration: 2033-03-21

Abstract

The utility model relates to the field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle, which comprises a flight part and a machine body connected below the flight part, wherein fins are arranged on the flight part, fins are symmetrically arranged on two sides of the machine body, spoilers are arranged on the upper end faces of the fins in parallel along the direction of the machine body, tail fins are arranged at one end of the machine body far away from the flight part, and the tail fins are symmetrically arranged on two sides of the machine body and are perpendicular to the fins.

Description

Unmanned aerial vehicle

Technical Field

The utility model relates to the field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle.

Background

Nowadays, unmanned aerial vehicle is a common aircraft, unmanned aerial vehicle has aroused extensive concern because of its advantages that have flexibility, small in size, quick, unmanned aerial vehicle flies and operation requirement is low, especially in civil aspect, most people can utilize unmanned aerial vehicle to carry out topography reconnaissance and flight beat, along with unmanned aerial vehicle's kind increases day by day, the problem that it produced also stands out more and more, for example tube-shape unmanned aerial vehicle, when flying because the lower extreme is the tube-shape, the air resistance that receives is great for flight speed slows down, and if the condition that wind-force is great appears, the control is unstable can appear, unmanned aerial vehicle turns to with the inconvenient problem of flight:

disclosure of Invention

The utility model aims at: the unmanned aerial vehicle aims at solving the problems that a cylindrical aircraft in the prior art is large in air resistance and low in flying speed in the flying process.

In order to achieve the above purpose, the technical scheme adopted by the utility model is as follows:

the utility model provides an unmanned aerial vehicle, includes the flight portion and connects the fuselage of flight portion below, be equipped with the fin on the flight portion, fuselage bilateral symmetry is equipped with the fin, the fin up end is equipped with the spoiler, the spoiler is followed fuselage direction parallel arrangement, the fuselage is keeping away from the one end of flight portion is equipped with the fin, the fin symmetry set up the fuselage both sides just with the fin is perpendicular.

The utility model relates to an unmanned aerial vehicle, which is characterized in that a pair of fins and tail fins are symmetrically arranged on a fuselage, so that the aircraft can ascend through the operation of a flight part at the top, the whole aircraft can incline through the rotation of the flight part after ascending, at the moment, the whole aircraft can be lifted to a horizontal state through the difference of air flow rates at two sides of the fins, a lifting force is provided for the flight of the aircraft, the tail of the fuselage is provided with the tail fins, the balance effect in the flight is achieved, the area of the traditional cylindrical aircraft influenced by air resistance in the flight is reduced through the arrangement of the fins and the tail fins on the fuselage of the aircraft, the fuselage of the cylindrical aircraft can fly horizontally in the flight through the fins, the stressed area in the flight is reduced, the aircraft can be flexible, and the flight speed is faster.

The utility model relates to an unmanned aerial vehicle, when the aircraft is in a static state, the aircraft is vertically placed, the unmanned aerial vehicle can be stably placed on a plane through the contact of a vertical plate and a spoiler with the ground, when the aircraft is ready for taking off, two flying parts at the upper end of the aircraft relatively rotate to drive the aircraft to rise, the aircraft is in a straight rising state, when the flying parts are turned through a universal turning device connected with a central shaft, fins at two ends of the flying parts disturb the air flow direction to enable the aircraft body to rotate, and because the wing pieces are arranged on the aircraft body, the aircraft body is subjected to larger lifting force through the wing pieces, when the aircraft body is in a horizontal state, the flying parts on the aircraft are not rotated to be slowly reset, and at the moment, the aircraft is in a horizontal state as a whole and can fly in a horizontal state, so that the flying speed is improved.

As the preferable scheme of the utility model, the fuselage comprises an upper fuselage and a lower fuselage, the upper fuselage is cylindrical and is positioned between the flight part and the lower fuselage, the lower fuselage is conical and round table-shaped, and one end with larger radius is connected with the upper fuselage, so that the whole fuselage presents a streamline shape with a front round and a rear sharp, and the air resistance is more beneficial to being reduced during flight.

As the preferable scheme of the utility model, one end surface of the wing is a plane, and the other end surface is designed into a streamline shape, so that the air flow speeds born by the two surfaces of the wing are different, the lifting effect is achieved on the flight of the unmanned aerial vehicle, and meanwhile, the air resistance can be reduced.

As a preferred embodiment of the present utility model, the wing panel has a trapezoidal cross section, and a shorter side length is equal to the length of the lower body, which is provided because of lower induced resistance and cheaper manufacturing cost.

As the preferable scheme of the utility model, the wing panel and the machine body are integrated into a whole, so that the structure is more stable and the machine body is convenient to manufacture.

As a preferred embodiment of the present utility model, the airfoil is made of an alloy material.

As a preferable scheme of the utility model, one end of the spoiler exceeds the bottom end of the wing piece, the tail end is vertically provided with a vertical plate, and one end of the vertical plate exceeds the bottom end of the tail wing, so that the effect of balancing the aircraft is achieved and the aircraft is used as a bracket when the aircraft is placed on the ground.

As a preferable scheme of the utility model, the height of the bottom end of the upright plate from the ground is the same as the height of the bottom end of the spoiler from the ground, so that stable placement can be ensured when the aircraft is placed.

As a preferable scheme of the utility model, the flying part comprises two pairs of fins which are arranged up and down, each pair of fins comprises two fins which are connected oppositely, and the power of the aircraft is provided for the aircraft through the two flying parts and the fins on each flying part.

As a preferable mode of the utility model, a central shaft is provided in the middle of the flying part, the flying part can rotate around the central shaft, a fuselage is provided at the lower end of the flying part, the flying part is connected with the fuselage through the central shaft, and the flying part and the fuselage form an aircraft.

As a preferable scheme of the utility model, the middle part of the flying part is provided with the universal rotating device, and the universal rotating device is connected with the central shaft and rotates based on the central shaft, so that the steering and the flying posture conversion of the aircraft are facilitated.

As a preferred embodiment of the utility model, both of the flight parts are rotated relatively in operation.

As a preferred embodiment of the utility model, the actual construction of the said universal rotation device mentioned in this patent is of two interconnected ring-shaped constructions.

In summary, due to the adoption of the technical scheme, the beneficial effects of the utility model are as follows:

1. the utility model relates to an unmanned aerial vehicle, which is characterized in that a pair of fins and tail fins are symmetrically arranged on a fuselage, so that the aircraft can ascend through the operation of a flight part at the top, the whole aircraft can incline through the rotation of the flight part after ascending, at the moment, the whole aircraft can be lifted to a horizontal state through the difference of air flow rates at two sides of the fins, a lifting force is provided for the flight of the aircraft, the tail of the fuselage is provided with the tail fins, the balance effect in the flight is achieved, the area of the traditional cylindrical aircraft influenced by air resistance in the flight is reduced through the arrangement of the fins and the tail fins on the fuselage of the aircraft, the fuselage of the cylindrical aircraft can fly horizontally in the flight through the fins, the stressed area in the flight is reduced, the aircraft can be flexible, and the flight speed is faster.

Drawings

FIG. 1 is a schematic diagram of the structure of the present utility model;

FIG. 2 is a schematic side elevational view of the present utility model;

FIG. 3 is a schematic view of an isometric structure of the present utility model;

FIG. 4 is a schematic top view of the present utility model;

FIG. 5 is a schematic view of the fuselage structure of the present utility model;

FIG. 6 is a schematic illustration of the flow of air in-flight of a airfoil of the present utility model;

FIG. 7 is an enlarged partial schematic view of the portion of FIG. 3A;

fig. 8 is a schematic representation of the attitude transformation of an aircraft of the present utility model.

Icon: 1-an aircraft; 2-a central axis; 11-flight part; 12-fuselage; 111-fins; 112-universal rotation device; 121-fins; 122-tail wing; 123-upper fuselage; 124-lower fuselage; 1211-spoilers; 1221-riser.

Detailed Description

The present utility model will be described in detail with reference to the accompanying drawings.

The present utility model will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present utility model more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the utility model.

Example 1

The unmanned aerial vehicle as shown in fig. 1-2 comprises a flight part 11 and a machine body 12 connected below the flight part 11, wherein fins 111 are arranged on the flight part 11, fins 121 are symmetrically arranged on two sides of the machine body 12, a spoiler 1211 is arranged on the upper end surface of each fin 121, the spoilers 1211 are arranged in parallel along the direction of the machine body 12, a tail wing 122 is arranged at one end of the machine body 12 far away from the flight part 11, the tail wings are symmetrically arranged on two sides of the machine body 12 and are perpendicular to the fins 121, the machine body 11 works to drive the machine body 1 to take off, the flight part 11 rotates during flight, so that the whole of the machine body 1 is deflected angularly, at the moment, due to the effect of the fins on the two sides of the machine body, a part of air flow lifts the whole of the machine body, the machine body 12 becomes a horizontal state, and the tail wing 122 arranged at the tail part of the machine body 12 keeps balance during flight, so that the air resistance borne by the machine body 1 is reduced, and the speed of the machine is improved.

The above-mentioned fuselage 12 includes upper fuselage 123 and lower fuselage 124, the upper fuselage 123 is cylindric and is located between the flight portion 11 and the lower fuselage 124, the lower fuselage 124 is conical round platform form, and the great one end of radius with the upper fuselage 123 is connected, sets up like this and makes fuselage 12 streamline, and the air resistance that receives when fuselage 12 keeps the horizontality to fly reduces, as shown in fig. 5.

One end surface of the fin 121 is a plane, the other end surface is designed into a streamline shape, and the fin 121 is provided with a device which makes the air flow rates of two surfaces different when flying, thereby playing a role in lifting the aircraft 1, as shown in fig. 5-6.

The fin 121 is trapezoidal in cross section and has a shorter side length equal to the length of the lower body 124, which is provided because of lower induced resistance and cheaper manufacturing cost, as shown in fig. 1.

The fin 121 and the machine body 12 are integrally formed, which is convenient for manufacturing.

The fin 121 is made of an alloy material.

The above spoiler 1211 has one end extending beyond the bottom end of the fin 121, the tail 122 has a vertical plate 1221 vertically disposed at the end, and one end of the vertical plate 1221 extends beyond the bottom end of the tail 122, so as to adjust the airflow and serve as a support for placement when the aircraft 1 is not in use, as shown in fig. 1 and 7.

The above-mentioned vertical plate 1221 has the same bottom end as the spoiler 1211 and the same bottom end as the ground, so that the aircraft 1 can be stably placed when not in use, as shown in fig. 7.

The flying part 11 comprises two pairs of fins 111 arranged up and down, each pair of fins 111 comprises two fins 111 which are connected oppositely, and the two flying parts 11 are used for ensuring the stability in the operation of the aircraft 1 and ensuring the steering sensitivity of the aircraft 1, as shown in figures 1-3.

The middle part of the flying part 11 is provided with a central shaft 2, the flying part 11 can rotate by taking the central shaft 2 as a center, the lower end of the flying part 11 is provided with a machine body 12, the flying part 11 is connected with the machine body 12 through the central shaft 2, and the flying part 11 and the machine body 12 form an aircraft 1, as shown in fig. 1-3.

The middle part of the flying part 11 is provided with a universal rotation device 112, and the universal rotation device 112 is connected with the central shaft 2 and rotates based on the central shaft 2, so that when the flying form of the aircraft 1 is changed, the flying part 11 is deflected by the universal rotation device 112 in the flying part 11, and the flying posture of the aircraft body 12 is changed, as shown in fig. 3.

The two aforementioned flight parts 11 are turned relatively during operation, so that the aircraft 1 can be operated as well as turned.

The utility model relates to an unmanned aerial vehicle, which is characterized in that a pair of fins 121 and tail fins 122 are symmetrically arranged on a machine body 12, so that the aircraft 1 can ascend through the operation of a flying part 11 at the top, after ascending, the whole aircraft 1 can incline through the rotation of the flying part 11, at the moment, the whole aircraft 1 can be lifted to a horizontal state through the difference of air flow rates at two sides of the fins 121, a lifting force is provided for the flying of the aircraft 1, the tail fins 122 are arranged at the tail part of the machine body 12, the balance effect is kept in the middle of the flying, the area of the traditional cylindrical aircraft influenced by air resistance is reduced in the middle of the flying by arranging the fins 121 and the tail fins 122 on the machine body 12 of the aircraft 1, the fuselage of the cylindrical aircraft can fly horizontally in the middle of the flying by arranging the fins 121, the stressed area in the middle of the flying is reduced, the aircraft 1 can be flexible, and the flying speed is faster.

The utility model relates to an unmanned aerial vehicle, when an aircraft 1 is in a static state, the aircraft 1 is vertically arranged, the unmanned aerial vehicle can be stably arranged on a plane through contact of a vertical plate 1221 and a spoiler 1211 with the ground, when the aircraft 1 is ready to take off, two flying parts 11 at the upper end of the aircraft 1 relatively rotate to drive the aircraft 1 to ascend, at the moment, the aircraft 1 is in a straight ascending state, when the flying parts 11 are turned by a universal turning device 112 connected with a central shaft 2, at the moment, the fins 111 at the two ends of the flying parts 11 disturb the airflow direction to enable the airframe 12 of the aircraft 1 to rotate, and because the airframe 12 of the aircraft 1 is provided with a wing piece 121, the airframe 12 of the aircraft 1 is subjected to larger lifting force through the wing piece 121, when the airframe 12 is in a horizontal state, the flying parts 11 on the aircraft 1 are not rotated to slowly reset, at the moment, the whole aircraft 1 is in the horizontal state, and can be kept in the horizontal state to fly, and the flying speed is improved.

Example 2

As shown in fig. 8, the present utility model is an unmanned aerial vehicle, and the attitude of the unmanned aerial vehicle from take-off to stable flight is changed as follows:

the aircraft 1 is in the vertical state in the middle of the flight fuselage 12, and the flight portion 11 carries out the transformation of direction through universal rotating device 112 at this moment, and two upper and lower flight portion 11 steering angle difference, the fin 111 on further flight portion 11 turns to, fin 111 changes the air current direction and makes aircraft 1 take place the skew, thereby fuselage 12 inclines, and the air velocity of the air velocity difference of two terminal surfaces of fin 121 that fuselage 12 both ends set up makes fuselage 12 slowly go up to the horizontality, and keep aircraft 1's equilibrium through the fin 122 at fuselage 12 afterbody, in order to reduce the size of the air resistance area that receives in the middle of the flight of aircraft 1, improve the flight speed.

The foregoing description of the preferred embodiments of the utility model is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the utility model.

Claims

1. The utility model provides an unmanned aerial vehicle, its characterized in that, including flight portion (11) and connection fuselage (12) of flight portion (11) below, be equipped with fin (111) on flight portion (11), fuselage (12) bilateral symmetry is equipped with fin (121), fin (121) up end is equipped with spoiler (1211), spoiler (1211) are followed fuselage (12) direction parallel arrangement, fuselage (12) are keeping away from one end of flight portion (11) is equipped with fin (122), fin symmetry set up fuselage (12) both sides and with fin (121) are perpendicular.

2. The unmanned aerial vehicle according to claim 1, wherein the main body (12) comprises an upper main body (123) and a lower main body (124), the upper main body (123) is cylindrical and is located between the flight part (11) and the lower main body (124), the lower main body (124) is conical and circular truncated cone, and one end with a larger radius is connected with the upper main body (123).

3. A unmanned aerial vehicle according to claim 1, wherein one end face of the wing (121) is planar and the other end face is streamlined.

4. A drone according to claim 3, wherein the fins (121) are trapezoidal in cross section and have a shorter side length equal to the length of the lower fuselage (124).

5. A drone according to claim 1, wherein the fins (121) are integral with the fuselage (12).

6. The unmanned aerial vehicle according to claim 1, wherein one end of the spoiler (1211) exceeds the bottom end of the fin (121), the tail (122) is provided with a vertical plate (1221) vertically at the end, and one end of the vertical plate (1221) exceeds the bottom end of the tail (122).

7. The unmanned aerial vehicle of claim 6, wherein the height of the bottom end of the riser (1221) from the ground is the same as the height of the bottom end of the spoiler (1211) from the ground.

8. A drone according to claim 1, wherein the flight portion (11) comprises two pairs of fins (111) arranged one above the other, each pair of fins (111) comprising two fins (111) connected in opposition.

9. An unmanned aerial vehicle according to any of claims 1 to 8, wherein a central shaft (2) is provided in the middle of the flight part (11), the flight part (11) rotates around the central shaft (2), a fuselage (12) is provided at the lower end of the flight part (11), the flight part (11) is connected to the fuselage (12) through the central shaft (2), and the flight part (11) and the fuselage (12) form the aircraft (1).

10. An unmanned aerial vehicle according to claim 9, wherein a universal rotation device (112) is provided in the middle of the flight part (11), and wherein the universal rotation device (112) is connected to the central shaft (2) and is rotationally movable on the basis of the central shaft (2).