CN213168535U

CN213168535U - Can accomodate VTOL unmanned aerial vehicle of screw

Info

Publication number: CN213168535U
Application number: CN202021563670.1U
Authority: CN
Inventors: 孙亚飞; 张田
Original assignee: Shenzhen Be Better Technology Industrial Co ltd
Current assignee: Shenzhen Be Better Technology Industrial Co ltd
Priority date: 2020-07-31
Filing date: 2020-07-31
Publication date: 2021-05-11
Anticipated expiration: 2030-07-31

Abstract

The utility model provides a vertical take-off and landing unmanned aerial vehicle capable of accommodating propellers, which comprises a body, propellers fixedly arranged at the head and the tail of the body and a plurality of vertical take-off wings, wherein the vertical take-off wings are rotatably arranged at the two sides of the body; the fuselage is provided with an accommodating groove for accommodating the vertical flying wing, and the accommodating groove is provided with a cover plate; the detection device detects the position of the vertical flying wing in the accommodating groove, and the driving device drives the cover plate to close the accommodating groove according to a signal of the monitoring device; after the accommodating groove accommodates the vertical flying wing, the streamline of the body is formed after the accommodating groove is closed by the cover plate, and the subsequent flight of the unmanned aerial vehicle is not influenced, so that the flight resistance is reduced, the low-speed operation safety of the unmanned aerial vehicle is improved, and the flight efficiency of the unmanned aerial vehicle is improved; the vertical flying wing after being stored is also protected; so that the utility model is not damaged by external factors.

Description

Can accomodate VTOL unmanned aerial vehicle of screw

Technical Field

The utility model relates to an unmanned air vehicle technique field especially relates to a can accomodate VTOL unmanned aerial vehicle of screw.

Background

In recent years, along with popularization of unmanned aerial vehicle application, the application field of the unmanned aerial vehicle is also continuously expanded, and the unmanned aerial vehicle on the market is generally divided into a fixed-wing unmanned aerial vehicle and a multi-axis unmanned aerial vehicle according to the structural form and the flight principle of unmanned aerial vehicle products.

The fixed-wing unmanned aerial vehicle has the advantages of high efficiency, heavy load, long dead time and high flying speed, but the requirements on a take-off and landing site are very strict, so that the application of the fixed-wing unmanned aerial vehicle is severely limited by the site; the requirement of multiaxis unmanned aerial vehicle to the place of taking off and landing is not high to control is convenient, can fix a height to hover at the fixed point, can take off and land perpendicularly, can take off and land and shuttle through in narrow and small space, but, it compares in fixed wing unmanned aerial vehicle inefficiency, the load is little, flight speed is slow.

The vertical take-off and landing fixed-wing unmanned aerial vehicle is released in the current market, the advantages of the fixed-wing unmanned aerial vehicle and a multi-shaft unmanned aerial vehicle are combined, the flight performance of the unmanned aerial vehicle is guaranteed, the problem that the unmanned aerial vehicle is limited by a take-off and landing site is solved, but the unmanned aerial vehicle is usually only formed by simply superposing the fixed-wing unmanned aerial vehicle and the multi-shaft unmanned aerial vehicle, the vertical take-off and landing are carried out by utilizing the related structure of the multi-shaft unmanned aerial vehicle, the unmanned aerial vehicle is converted into a fixed-wing flight mode after taking off, however, multi-shaft propellers of the existing unmanned aerial vehicle are directly exposed, very large flight resistance is generated, the energy consumption of the unmanned aerial vehicle is greatly increased, the corresponding flight time and the highest flight speed are also obviously reduced, meanwhile, the propellers are; and the accommodating cavity formed after the accommodating has an influence on the overall shape of the airframe, so that the airframe easily generates vortex to influence the flight when the airflow passes through the accommodating cavity.

Therefore, a vertical take-off and landing unmanned aerial vehicle with a more reasonable structure and capable of containing propellers is needed at present.

SUMMERY OF THE UTILITY MODEL

Aiming at the existing technologies such as: in the VTOL unmanned aerial vehicle design that has adopted two sets of driving system in going up and down and having advanced, do not have the structure that can fine accomodate the lift rotor, play the protection to the rotor simultaneously to guarantee that the design of fuselage streamline structure is more few again. Therefore, the vertical flying wing can be accommodated, and the structure that the aircraft body is streamlined is designed.

The vertical take-off and landing unmanned aerial vehicle capable of containing propellers comprises a body, propellers fixedly arranged at the head end and the tail end of the body and a plurality of vertical take-off wings, wherein the vertical take-off wings are rotatably arranged on two sides of the body; the fuselage is provided with an accommodating groove for accommodating the vertical flying wing, and the accommodating groove is provided with a cover plate; the accommodating groove is internally provided with a detection device and a driving device, the detection device detects the position of the vertical flying wing in the accommodating groove, and the driving device drives the cover plate to close the accommodating groove according to a signal of the detection device.

Preferably, a rotating shaft is arranged in the accommodating groove, a rotating rod is sleeved on the rotating shaft, a first motor is arranged at the tail end of the rotating rod, and an output shaft of the first motor is connected with the vertical flying wing.

Preferably, the two ends of the accommodating groove are provided with the rotating shafts, the two rotating shafts at the two ends are provided with the rotating rods in a sleeved mode, and the two rotating rods drive the vertical takeoff wing to be accommodated in the accommodating groove at the same time.

Preferably, two pairs of the vertical flying wings and the receiving groove are symmetrically arranged about the body, and the receiving groove can simultaneously receive the two vertical flying wings on one side of the body.

Preferably, lateral wings are further arranged on two sides of the machine body, and the accommodating grooves are formed below the lateral wings.

Preferably, the inner surface of the accommodating groove is provided with a smooth structure layer, and when the vertical flying wing collides with the smooth structure layer, the vertical flying wing rotates around the output shaft of the first motor to a state of being in contact with the smooth structure layer without an interaction force.

Preferably, one end of the cover plate is connected with one side, close to the ground, of the accommodating groove, and the driving device drives the cover plate to upwards turn and close the accommodating groove.

Preferably, the surface of the cover plate and the fuselage form a streamlined structure.

The utility model has the advantages that: the utility model provides a vertical take-off and landing unmanned aerial vehicle capable of accommodating propellers, which comprises a body, propellers fixedly arranged at the head and the tail of the body and a plurality of vertical take-off wings, wherein the vertical take-off wings are rotatably arranged at the two sides of the body; the fuselage is provided with an accommodating groove for accommodating the vertical flying wing, and the accommodating groove is provided with a cover plate; the detection device detects the position of the vertical flying wing in the accommodating groove, and the driving device drives the cover plate to close the accommodating groove according to a signal of the detection device; after the accommodating groove accommodates the vertical flying wing, the streamline of the body is formed after the accommodating groove is closed by the cover plate, and the subsequent flight of the unmanned aerial vehicle is not influenced, so that the flight resistance is reduced, the low-speed operation safety of the unmanned aerial vehicle is improved, and the flight efficiency of the unmanned aerial vehicle is improved; the vertical flying wing after being stored is also protected; so that the utility model is not damaged by external factors.

Drawings

Fig. 1 is a perspective view of the present invention;

fig. 2 is a top view of the present invention;

fig. 3 is a perspective view of the present invention;

fig. 4 is a schematic view of the vertical takeoff wing structure of the present invention.

The main element symbols are as follows:

1. a body; 11. a propeller; 12. vertically flying the flying wing; 13. accommodating grooves; 131. a rotating shaft; 132. rotating the rod; 133. a first motor; 14. a cover plate; 15. a detection device; 16. a drive device; 17. and (4) side wings.

Detailed Description

In order to make the present invention clearer, the present invention will be further described with reference to the accompanying drawings.

The VTOL unmanned aerial vehicle has the advantages of a gyroplane and a fixed-wing unmanned aerial vehicle, can vertically take off and land and hover like the gyroplane, has the characteristics of high speed and long range of the fixed-wing unmanned aerial vehicle, and has a better development prospect. Through the analysis to each type of VTOL unmanned aerial vehicle, discover that combined type VTOL fixed wing unmanned aerial vehicle compares in other VTOL unmanned aerial vehicles, have that the technique realizability is strong, stability is higher, advantage such as the cost is lower. However, the wings of the fixed-wing unmanned aerial vehicle are large in unfolding size, large in occupied space, difficult to manufacture, transport, store and the like, and not beneficial to batch production, storage and carrying; moreover, most of the existing accommodating structures are externally connected structures for accommodating vertical flying wings or are arranged in the cabin, but the former can influence the flight speed and performance of the unmanned aerial vehicle, and the latter can influence the streamline structure of the unmanned aerial vehicle body, so that the use performance of the unmanned aerial vehicle is influenced; a more preferable structure is required to house the vertical takeoff flyer.

Specifically, referring to fig. 1-4, the vertical take-off and landing unmanned aerial vehicle capable of accommodating propellers comprises a vehicle body 1, propellers 11 fixedly arranged at the head and tail ends of the vehicle body, and a plurality of vertical take-off wings 12, wherein the vertical take-off wings 12 are rotatably arranged at two sides of the vehicle body 1; the fuselage 1 is provided with an accommodating groove 13 for accommodating the vertical flying wing 12, and the accommodating groove 13 is provided with a cover plate 14; a detection device 15 and a driving device 16 are further arranged in the accommodating groove 13, the detection device 15 detects the position of the vertical flying wing 12 in the accommodating groove 13, and the driving device 16 drives the cover plate 14 to close the accommodating groove 13 according to signals of the detection device; the detection device can be that a distance sensor is arranged in the accommodating groove, the vertical takeoff wing is determined whether to be accommodated in the accommodating groove or not by sensing the positions of the vertical takeoff wing and the distance sensor, the driving device can be a motor and a hinge, and the motor pulls the hinge to close the accommodating groove; the signal for opening the cover plate can carry out the opening action of the cover plate by depending on the takeoff command of the unmanned aerial vehicle; when the vertical flying wing is used for carrying out the height climbing of the unmanned aerial vehicle, the vertical flying wing stops rotating after reaching a preset position and is stored in the containing groove, then the detection device detects the relative distance of the vertical flying wing, when the vertical flying wing is judged to be completely stored in the containing groove, the driving device receives a detection signal of the detection device, the cover plate is closed, the body forms a complete streamline structure, and the flight performance of the unmanned aerial vehicle is ensured; meanwhile, the vertical flying wing is protected from interfering with other structures of the airplane body; and when the holding tank is opened to needs, unmanned aerial vehicle or host computer end control drive arrangement open the apron, work behind the perpendicular flywing roll-out holding tank.

In this embodiment, a rotating shaft 131 is disposed in the accommodating groove 13, a rotating rod 132 is sleeved on the rotating shaft 131, a first motor 133 is disposed at the end of the rotating rod 132, and an output shaft of the first motor 133 is connected to the vertical flying wing 12; the motor is also arranged on the rotating shaft for driving, and the first motor for driving the vertical flying wing is directly arranged at the tail end of the rotating rod, so that the debugging is convenient, and the heat dissipation performance and the take-off performance are ensured.

In this embodiment, two ends of the accommodating groove 13 are both provided with rotating shafts, two rotating shafts at two ends are both sleeved with rotating rods, and the two rotating rods drive the vertical takeoff wing to be accommodated in the accommodating groove at the same time; the two ends of the accommodating tank are provided with vertical flying wings, two pairs of vertical flying wings and the accommodating tank are symmetrically arranged about the fuselage, and the accommodating tank can accommodate the two vertical flying wings on one side of the fuselage at the same time; the aircraft can obtain larger takeoff power, and the length of the accommodating groove is at least equal to the sum of the lengths of the two rotating rods and the length of the vertical takeoff wing. And in order to prevent the two vertical takeoff wings from colliding with each other, the rotating rods are arranged on different horizontal planes and are contained in the containing grooves in a staggered mode.

In this embodiment, the two sides of the body 1 are further provided with side wings 17, and the accommodating grooves 13 are arranged below the side wings 17; this position does not impede the airflow generated by the vertical takeoff wing.

In this embodiment, the inner surface of the accommodating groove 13 is configured as a smooth structural layer, and when the vertical flying wing collides with the smooth structural layer, the vertical flying wing rotates around the output shaft of the first motor to a state of no interaction force contact with the smooth structural layer; because the depth of the receiving groove is limited, the vertical flying wing needs to satisfy this dimension condition when being received in the receiving groove; one way is to realize that the vertical flying wing stops at a fixed angle after stopping through the good matching of a servo motor and a position detection device, and the optimal way is to stop at a position where a rotating shaft is parallel; the vertical takeoff wing can rotate freely after the first motor stops working, and when the vertical takeoff wing stops at any angle, the vertical takeoff wing collides with the smooth structure layer of the accommodating groove, so that the vertical takeoff wing is stressed to rotate, and finally stops to be in contact with the smooth structure layer but has no interaction force. Therefore, the load of the unmanned aerial vehicle can be reduced, unnecessary structures are reduced, and instability caused by complex structures is avoided, so that the performance of the unmanned aerial vehicle is improved;

in this embodiment, one end of the cover plate 14 is connected to one side of the accommodating groove 13 close to the ground, and the driving device drives the cover plate to turn upwards to close the accommodating groove; because the setting can prevent that drive arrangement from becoming invalid and closing the condition of holding tank in advance when the lower extreme, even under abnormal conditions, the apron also can rely on self gravity to keep the state of drooping, guarantees normally opening of holding tank.

In this embodiment, the surface of apron and fuselage form streamlined structure for the holding tank can guarantee the fuselage after the closure still streamlined structure.

The utility model has the advantages that:

1) the surface of the cover plate and the machine body form a streamline structure, so that the machine body can be ensured to be in the streamline structure after the accommodating groove is closed;

2) the vertical takeoff wing is ensured to be in a state of being capable of accommodating through the light touch of the vertical takeoff wing and the accommodating groove.

The above disclosure is only for the specific embodiments of the present invention, but the present invention is not limited thereto, and any changes that can be made by those skilled in the art should fall within the protection scope of the present invention.

Claims

1. A vertical take-off and landing unmanned aerial vehicle capable of containing propellers comprises a body and propellers fixedly arranged at the head end and the tail end of the body, and is characterized by further comprising a plurality of vertical take-off wings, wherein the vertical take-off wings are rotatably arranged on two sides of the body; the fuselage is provided with an accommodating groove for accommodating the vertical flying wing, and the accommodating groove is provided with a cover plate; the accommodating groove is internally provided with a detection device and a driving device, the detection device detects the position of the vertical flying wing in the accommodating groove, and the driving device drives the cover plate to close the accommodating groove according to a signal of the detection device.

2. The unmanned aerial vehicle capable of accommodating propellers of claim 1, wherein a rotating shaft is arranged in the accommodating groove, a rotating rod is sleeved on the rotating shaft, a first motor is arranged at the tail end of the rotating rod, and the vertical takeoff and landing wing is connected with an output shaft of the first motor.

3. The unmanned aerial vehicle capable of collecting vertical take-off and landing and provided with propellers according to claim 2, wherein the two ends of the containing groove are provided with the rotating shafts, the two rotating shafts at the two ends are sleeved with the rotating rods, and the two rotating rods drive the vertical take-off wings to be simultaneously contained in the containing groove.

4. The propeller stowable vtol drone of claim 3, wherein there are two pairs of the vtol wing and the receiving slot symmetrically disposed about the fuselage, the receiving slot being able to simultaneously receive two of the vtol wings on one side of the fuselage.

5. The propeller-stowable VTOL UAV of claim 1, wherein the fuselage is further provided with side wings on both sides, and the receiving groove is provided below the side wings.

6. The propeller-stowable vtol drone of claim 2, wherein the inner surface of the housing tank is provided as a smooth structural layer, and when the vtol wing collides with the smooth structural layer, the vtol wing rotates around the output shaft of the first motor to a state of no interaction force contact with the smooth structural layer.

7. The propeller-stowable VTOL UAV of claim 1, wherein one end of the cover plate is connected to a ground-near side of the receiving groove, and the driving device drives the cover plate to turn upward to close the receiving groove.

8. The propeller-stowable VTOL drone of claim 7, wherein a surface of the cover plate forms a streamlined structure with the fuselage.