CN112478147A

CN112478147A - Wing adjusting device and method for unmanned aerial vehicle

Info

Publication number: CN112478147A
Application number: CN202011393343.0A
Authority: CN
Inventors: 张晋明
Original assignee: Xingtai Polytechnic College
Current assignee: Xingtai Polytechnic College
Priority date: 2020-12-02
Filing date: 2020-12-02
Publication date: 2021-03-12

Abstract

The invention relates to the technical field of unmanned aerial vehicles, in particular to a wing adjusting device and an adjusting method of an unmanned aerial vehicle. The invention achieves the purpose of preventing or reducing the damage to the rotor wing of the unmanned aerial vehicle when the unmanned aerial vehicle encounters hail, and reduces the risk of crash of the unmanned aerial vehicle.

Description

Wing adjusting device and method for unmanned aerial vehicle

Technical Field

The invention relates to the field of unmanned aerial vehicles, in particular to a wing adjusting device and an adjusting method of an unmanned aerial vehicle.

Background

The unmanned plane is called unmanned plane for short, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. The machine has no cockpit, but is provided with an automatic pilot, a program control device and other equipment. The personnel on the ground, the naval vessel or the mother aircraft remote control station can track, position, remotely control, telemeter and digitally transmit the personnel through equipment such as a radar.

The unmanned aerial vehicle flies, firstly, lift force is generated, the fixed wing generates the lift force according to the Bernoulli principle, namely, the sum of a pressure term, a speed peak and a liquid high pressure term is a constant, the wing is generally in a shape of being upwards convex and downwards flat, so that the flow velocity above the wing is large, the pressure intensity is small, the flow velocity below the wing is small, the pressure intensity is large, the lift force is generated by pressure difference, when the helicopter flies, the rotor wing continuously rotates, air flows through the upper surface of the blade, the flow velocity is accelerated, and the pressure is reduced; when air flows through the lower surface of the blade, the flow speed is reduced, the pressure is increased, and the four-rotor unmanned aerial vehicle substantially belongs to the category of helicopters.

The existing unmanned aerial vehicle is generally an unmanned aerial vehicle with four rotors or six rotors, the flying height of the unmanned aerial vehicle is very high, other devices can be carried to be used for detecting air cleanliness, shooting and framing and the like, under severe environments, the unmanned aerial vehicle is in operation, if hail formed by sudden high-altitude cold airflow is encountered, the hail can cause destructive injury to the rotors of the unmanned aerial vehicle, and even cause the unmanned aerial vehicle to crash, therefore, the invention provides a wing adjusting device and an adjusting method of the unmanned aerial vehicle.

Disclosure of Invention

In order to solve the problems in the prior art, the invention provides a wing adjusting device and an adjusting method of an unmanned aerial vehicle.

In order to achieve the purpose, the invention adopts the following technical scheme:

a wing adjusting device and method of an unmanned aerial vehicle comprise an unmanned aerial vehicle body, wherein four first flying devices are arranged on the side wall of the unmanned aerial vehicle body, and are connected with the unmanned aerial vehicle body through hollow pipes;

the hollow pipes are fixedly connected with L-shaped fixing frames, the L-shaped fixing frames are provided with second take-off devices, and the second take-off devices are located below the first take-off devices;

the first flying device comprises a rotating motor and a rack for fixing the rotating motor, the rack is rotatably connected with a hollow pipe, semi-cylindrical blocks are fixedly connected to ports, close to the rack, of the hollow pipe, through grooves are formed in one end face of each semi-cylindrical block, turbines and connecting columns are arranged in the through grooves, the turbines are fixedly connected with the connecting columns, the connecting columns are rotatably connected with the through grooves, the turbines are meshed with worms, and the worms are rotatably connected with the hollow pipe;

one end of each connecting column extends to the outside of the bottom end of the semi-cylindrical block and is fixedly connected with a conical gear, the conical gears are meshed with semi-annular crown gears, and the semi-annular crown gears are fixedly connected with the rack;

the output shaft of the rotating motor is fixedly connected with a first rotor and a rotating box, two sides of the rotating box are fixedly connected with telescopic rotor sheaths, the rotor sheaths are sleeved outside the first rotor, and the top surface and the bottom surface of each rotor sheath are identical in shape;

the output shaft of the rotating motor is sleeved with hollow threaded columns, the hollow threaded columns are fixedly connected with a shell of the rotating motor, the outer portions of the hollow threaded columns are in threaded connection with first gears, the top surfaces of the first gears are fixedly connected with hollow fixing sleeves, the hollow fixing sleeves are sleeved on the outer portions of the output shaft, the top ends of the hollow fixing sleeves are rotatably connected with fixing plates, connecting rods are fixedly connected to two sides of each fixing plate, fixing columns are fixedly connected to the connecting rods, and the fixing columns are used for fixing the contracted rotor wing sheaths;

the first gears are all meshed with first crown gears, and the first crown gears are all fixedly connected with the hollow pipe.

Further, the rotor sheaths each comprise a first sheath, a second sheath, a third sheath, and a fourth sheath;

the first protective shells are fixedly connected with the rotating box, the first protective shells wrap the second protective shells and are in sliding connection with the second protective shells, the second protective shells wrap the third protective shells and are in sliding connection with the third protective shells, and the third protective shells wrap the fourth protective shells and are in sliding connection with the fourth protective shells;

clamping pieces used for being connected with each other are arranged between the first protective shell and the second protective shell, between the second protective shell and the third protective shell and between the third protective shell and the fourth protective shell.

Furthermore, the clamping piece comprises a limiting ring, the limiting ring is fixedly connected with the corresponding first protective shell, the second protective shell, the third protective shell and the fourth protective shell, and limiting grooves matched with the limiting ring are formed in the inner walls of the first protective shell, the second protective shell, the third protective shell and the fourth protective shell.

Further, the top surface of first protective case, second protective case, third protective case and fourth protective case all sets up rather than the recess of looks adaptation, all be equipped with the guard plate in the recess, guard plate and recess sliding connection, all be equipped with a plurality of springs between guard plate and the recess, the spring all with guard plate fixed connection.

The invention has the beneficial effects that:

the rotor wing protective sleeve is rotated to block hailstones falling in the air, so that the normal work of the second takeoff device is guaranteed, the second takeoff device is protected, the aim of preventing or reducing the damage to the rotor wing of the unmanned aerial vehicle when the unmanned aerial vehicle encounters hailstones formed by sudden high cold airflow is fulfilled, and the risk of crash of the unmanned aerial vehicle is reduced.

Drawings

FIG. 1 is a schematic view of the overall structure of the present invention;

FIG. 2 is a bottom view of the first lift device of the present invention;

FIG. 3 is an enlarged view A of the present invention;

FIG. 4 is an exploded view of a portion of the structure of the present invention;

FIG. 5 is a schematic structural diagram of a first flying apparatus of the present invention;

FIG. 6 is a schematic structural view of a rotor sheath of the present invention;

fig. 7 is a schematic structural view of the protection plate of the present invention.

Reference numbers in the figures: 1 unmanned aerial vehicle body, 2 rotate the box, 3 rotor sheaths, 4 first rotors, 5 second take-off devices, 6 hollow tubes, 7L shape mount, 8 fixed columns, 9 connecting rods, 10 fixed plates, 11 first gears, 12 rotating electrical machines, 13 frames, 14 through grooves, 15 turbines, 16 semicylindrical blocks, 17 conical gears, 18 connecting columns, 19 semiannular crown gears, 20 worms, 21 first crown gears, 22 hollow fixed sleeves, 23 hollow threaded columns, 24 springs, 25 protection plates, 26 grooves, 27 first protection shells, 28 second protection shells, 29 third protection shells, 30 fourth protection shells.

Detailed Description

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.

Referring to fig. 1-7, a wing adjusting device and an adjusting method of an unmanned aerial vehicle comprise an unmanned aerial vehicle body 1, wherein four first flying devices are arranged on the side wall of the unmanned aerial vehicle body 1, the four first flying devices are all connected with the unmanned aerial vehicle body 1 through hollow pipes 6, and the hollow pipes 6 are all fixedly connected with the unmanned aerial vehicle body 1;

the hollow pipes 6 are fixedly connected with L-shaped fixing frames 7, the L-shaped fixing frames 7 are provided with second take-off devices 5, the second take-off devices 5 are located below the first take-off devices, the second take-off devices 5 comprise second rotors and power sources for driving the second rotors to rotate, such as first rotating motors, the second rotors are fixedly connected with output shafts of the first rotating motors, and the first rotating motors are fixedly connected with one side of the L-shaped fixing frames 7;

the second takeoff device 5 is a standby flying device, the unmanned aerial vehicle flies by using the first takeoff device in a benign weather environment, and flies by using the second takeoff device 5 in a hail weather condition;

the first flying devices comprise rotating motors 12 and racks 13 used for fixing the rotating motors 12, the racks 13 are rotatably connected with hollow pipes 6, the racks 13 are conventional devices, and are not illustrated too much, ports, close to the racks 13, of the hollow pipes 6 are fixedly connected with semi-cylindrical blocks 16, one end faces of the semi-cylindrical blocks 16 extend to the outside of the hollow pipes 6, through grooves 14 are formed in one end faces of the semi-cylindrical blocks 16, turbines 15 and connecting columns 18 are arranged in the through grooves 14, the turbines 15 are fixedly connected with the connecting columns 18, the connecting columns 18 are rotatably connected with the top faces and the bottom faces of the through grooves 14, the turbines 15 are meshed with worms 20, the worms 20 are rotatably connected with the hollow pipes 6, and one ends of the worms 20 extend into the unmanned aerial vehicle body 1;

one end of each connecting column 18 extends to the outside of the bottom end of the semi-cylindrical block 16 and is fixedly connected with a conical gear 17, the conical gears 17 are meshed with semi-annular crown gears 19, and the semi-annular crown gears 19 are fixedly connected with the bottom surface of the rack 13;

a first rotor wing 4 and a rotating box 2 are fixedly connected to an output shaft of a rotating motor 12 of the first flying device, the diameter of the first rotor wing 4 is larger than that of the second rotor wing, the rotating box 2 is sleeved outside part of the first rotor wing 4, two sides of the rotating box 2 are fixedly connected with telescopic rotor wing sheaths 3, the rotor wing sheaths 3 are sleeved outside the first rotor wing 4, the top surface and the bottom surface of each rotor wing sheath 3 are identical in shape, in benign weather, the unmanned aerial vehicle flies by using the first flying device, and at the moment, the rotor wing sheaths 3 are in a contracted state;

under the condition of hail weather, the second take-off device 5 is utilized to fly, at the moment, the first rotor 4 still rotates, the rotor sheath 3 is in an extension state, the first rotor 4 is wrapped, the first rotor 4 is protected from being damaged, and along with the synchronous rotation of the first rotor 4, because the top surface and the bottom surface of the rotor wing sheath 3 have the same shape, the air flow velocity passing through the top surface and the bottom surface of the rotor wing sheath 3 in unit time is the same, so that the first rotor 4 loses the function of generating lift force, so as to prevent hail from hitting the first rotor 4, avoid causing unstable rotation of the first rotor 4, thereby avoiding the unstable flight of the unmanned aerial vehicle and the crash of the unmanned aerial vehicle, meanwhile, the rotor wing sheath 3 plays a role in protecting the second take-off device 5, and by utilizing the rotation of the rotor wing sheath 3, the hail falling in the air is blocked, so that the normal work of the second takeoff device 5 is ensured;

the outer portion of an output shaft of the rotating motor 12 is sleeved with a hollow threaded column 23, the hollow threaded columns 23 are fixedly connected with a shell of the rotating motor 12, the outer portion of the hollow threaded column 23 is in threaded connection with a first gear 11, the top surface of the first gear 11 is fixedly connected with a hollow fixing sleeve 22, the hollow fixing sleeve 22 is sleeved on the outer portion of the output shaft, the top end of the hollow fixing sleeve 22 is rotatably connected with a fixing plate 10, two sides of the fixing plate 10 are fixedly connected with connecting rods 9, the connecting rods 9 are fixedly connected with fixing columns 8, the fixing columns 8 are used for fixing the rotor wing sheaths 3 after contraction, and therefore when the first flying device is used for flying, the rotor wing sheaths 3 in a contraction state are contracted and fixed through the fixing columns 8;

first crown gears 21 are meshed with the first gears 11, and the first crown gears 21 are fixedly connected with the hollow pipe 6.

The rotor sheaths 3 each comprise a first sheath 27, a second sheath 28, a third sheath 29 and a fourth sheath 30;

the bottoms of the first protective shell 27, the second protective shell 28, the third protective shell 29 and the fourth protective shell 30 are all provided with holes matched with the fixing column 8, and the top surfaces and the bottom surfaces of the first protective shell 27, the second protective shell 28, the third protective shell 29 and the fourth protective shell 30 are all planes;

the first protective shells 27 are fixedly connected with the rotating box 2, the first protective shells 27 wrap the second protective shells 28 and are in sliding connection with the second protective shells 28, the second protective shells 28 wrap the third protective shells 29 and are in sliding connection with the third protective shells 29, and the third protective shells 29 wrap the fourth protective shells 30 and are in sliding connection with the fourth protective shells 30;

when the rotor sheath 3 is in the retracted state, the second sheath 28 is located in the first sheath 27, the third sheath 29 is located in the second sheath 28, and the fourth sheath 30 is located in the third sheath 29;

clamping pieces for mutual connection are arranged between the first protective shell 27 and the second protective shell 28, between the second protective shell 28 and the third protective shell 29 and between the third protective shell 29 and the fourth protective shell 30, each clamping piece comprises a limiting ring, each limiting ring is fixedly connected with the corresponding first protective shell 27, the corresponding second protective shell 28, the corresponding third protective shell 29 and the corresponding fourth protective shell 30, and limiting grooves matched with the limiting rings are arranged on the inner walls of the first protective shell 27, the corresponding second protective shell 28, the corresponding third protective shell 29 and the corresponding fourth protective shell 30;

first protective housing 27, second protective housing 28, third protective housing 29 and fourth protective housing 30's top surface all seted up rather than the recess 26 of looks adaptation, all be equipped with the guard plate 25 in the recess 26, guard plate 25 and recess 26 sliding connection, all be equipped with a plurality of springs 24 between guard plate 25 and the recess 26, springs 24 all with guard plate 25 fixed connection.

The purpose of setting up guard plate 25 and spring 24 etc. here is that spring 24 plays the cushioning effect to thereby combine the guard action of guard plate 25 to protect first protective housing 27, second protective housing 28, third protective housing 29 and fourth protective housing 30, prolong rotor cover 3's life, at the in-process that the hail was hit simultaneously, spring 24's cushioning effect also does benefit to the stable flight of unmanned aerial vehicle.

The wing adjusting method of the unmanned aerial vehicle is described as follows.

The working principle is as follows: in a benign weather environment, the first flying device is utilized to fly, the second flying device 5 is closed, when hail is encountered, the second flying device 5 is started, the worm 20 is rotated to drive the turbine 15 to rotate, the connecting column 18 and the conical gear 17 are further driven to rotate, the conical gear 17 drives the semi-annular crown gear 19 to rotate, the rack 13 is further driven to rotate, synchronously, the rack 13 rotates to enable the first gear 11 and the first crown gear 21 to rotate relatively, the first crown gear 21 is fixedly connected with the hollow tube 6, the first gear 11 rotates, the first gear 11 is in threaded connection with the hollow threaded column 23 fixed on the shell of the rotating motor 12, the first gear 11 moves towards the direction close to the rotating motor 12, and the fixing plate 10 is pulled downwards to enable the fixing column 8 to leave the first protective shell 27 and the second protective shell 28, The holes in the third protecting shell 29 and the fourth protecting shell 30, the second protecting shell 28, the third protecting shell 29 and the fourth protecting shell 30 extend away under the action of the centrifugal force of the output shaft of the rotating motor 12 to wrap the first rotor 4, so that the first rotor 4 is protected from being damaged, the first rotor 4 rotates synchronously, because the shapes of the top surface and the bottom surface of the rotor sheath 3 are the same, the air flow rate passing through the top surface and the bottom surface of the rotor sheath 3 in unit time is the same, so that the first rotor 4 loses the function of generating lift force, so as to prevent the hail from hitting the first rotor 4, avoid the unstable rotation of the first rotor 4, avoid the unstable flight of the unmanned aerial vehicle, avoid the crash of the unmanned aerial vehicle, and simultaneously, the unmanned aerial vehicle utilizes the rotation of the rotor sheath 3 to block hail falling in the air, and play a protection function on the second take-off device 5, thereby ensuring the normal work of the second take-off device 5, thereby reach unmanned aerial vehicle when meetting the hail that the high cold air current of proruption formed, avoid or reduce unmanned aerial vehicle's rotor and receive the purpose of damage, reduced the risk of unmanned aerial vehicle crash.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the equipment or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.

Claims

1. The utility model provides an unmanned aerial vehicle's wing adjusting device, includes unmanned aerial vehicle body (1), its characterized in that: the side wall of the unmanned aerial vehicle body (1) is provided with four first flying devices, and the four first flying devices are connected with the unmanned aerial vehicle body (1) through hollow pipes (6);

the hollow pipes (6) are fixedly connected with L-shaped fixing frames (7), the L-shaped fixing frames (7) are provided with second take-off devices (5), and the second take-off devices (5) are located below the first take-off devices;

the first flying device comprises a rotating motor (12) and a rack (13) used for fixing the rotating motor (12), the rack (13) is rotatably connected with a hollow pipe (6), semi-cylindrical blocks (16) are fixedly connected to ports, close to the rack (13), of the hollow pipe (6), through grooves (14) are formed in one end face of each semi-cylindrical block (16), turbines (15) and connecting columns (18) are arranged in the through grooves (14), the turbines (15) are fixedly connected with the connecting columns (18), the connecting columns (18) are rotatably connected with the through grooves (14), the turbines (15) are meshed with worms (20), and the worms (20) are rotatably connected with the hollow pipe (6);

one end of each connecting column (18) extends to the outside of the bottom end of the semi-cylindrical block (16) and is fixedly connected with a conical gear (17), the conical gears (17) are meshed with semi-annular crown gears (19), and the semi-annular crown gears (19) are fixedly connected with the rack (13);

a first rotor wing (4) and a rotating box (2) are fixedly connected to an output shaft of the rotating motor (12), telescopic rotor wing sheaths (3) are fixedly connected to two sides of the rotating box (2), the rotor wing sheaths (3) are sleeved outside the first rotor wing (4), and the top surface and the bottom surface of each rotor wing sheath (3) are identical in shape;

the outer portion of an output shaft of the rotating motor (12) is sleeved with a hollow threaded column (23), the hollow threaded column (23) is fixedly connected with a shell of the rotating motor (12), the outer portion of the hollow threaded column (23) is in threaded connection with a first gear (11), the top surface of the first gear (11) is fixedly connected with a hollow fixing sleeve (22), the hollow fixing sleeve (22) is sleeved on the outer portion of the output shaft, the top end of the hollow fixing sleeve (22) is rotatably connected with a fixing plate (10), two sides of the fixing plate (10) are fixedly connected with connecting rods (9), fixing columns (8) are fixedly connected onto the connecting rods (9), and the fixing columns (8) are used for fixing the contracted rotor wing sheath (3);

first crown gears (21) are meshed with the first gears (11), and the first crown gears (21) are fixedly connected with the hollow pipe (6).

2. The wing adjustment device and the adjustment method of the unmanned aerial vehicle according to claim 1, wherein the rotor sheaths (3) each comprise a first sheath (27), a second sheath (28), a third sheath (29), and a fourth sheath (30);

the first protective shells (27) are fixedly connected with the rotating box (2), the first protective shells (27) wrap the second protective shells (28) and are in sliding connection with the second protective shells (28), the second protective shells (28) wrap the third protective shells (29) and are in sliding connection with the third protective shells (29), and the third protective shells (29) wrap the fourth protective shells (30) and are in sliding connection with the fourth protective shells (30);

clamping pieces for mutual connection are arranged between the first protective shell (27) and the second protective shell (28), between the second protective shell (28) and the third protective shell (29) and between the third protective shell (29) and the fourth protective shell (30).

3. The wing adjusting device and the wing adjusting method of the unmanned aerial vehicle as claimed in claim 2, wherein the clip comprises a limiting ring, the limiting ring is fixedly connected with the corresponding first protective shell (27), second protective shell (28), third protective shell (29) and fourth protective shell (30), and limiting grooves matched with the limiting ring are arranged on the inner walls of the first protective shell (27), second protective shell (28), third protective shell (29) and fourth protective shell (30).

4. The wing adjusting device and the adjusting method for the unmanned aerial vehicle according to claim 3, wherein grooves (26) matched with the first protective shell (27), the second protective shell (28), the third protective shell (29) and the fourth protective shell (30) are formed in the top surfaces of the first protective shell, the second protective shell, the third protective shell and the fourth protective shell, protection plates (25) are arranged in the grooves (26), the protection plates (25) are connected with the grooves (26) in a sliding mode, a plurality of springs (24) are arranged between the protection plates (25) and the grooves (26), and the springs (24) are fixedly connected with the protection plates (25).