Vertical unmanned aerial vehicle with telescopic wings

Abstract

The vertical unmanned aerial vehicle comprises a fuselage, fixed side wings are arranged on the two sides of the fuselage, telescopic side wings are arranged in the fixed side wings in a sliding mode, and the ends, away from the fuselage, of the telescopic side wings penetrate through the side walls of the fixed side wings and extend outwards. Telescopic driving assemblies are further arranged in the fixed side wings and used for driving the telescopic side wings to slide. Through the telescopic driving assembly, the fixed side wings and the telescopic side wings can adjust the aspect ratio according to the flight mode; when the endurance needs to be improved, the extension length of the telescopic side wings is maximum, the lift-drag ratio is increased, the gliding performance is improved, and the endurance is improved; when the aircraft needs to fly in severe weather or take off in a narrow space, the telescopic side wings are contracted, and the power and wind resistance of the engine are improved; when the unmanned aerial vehicle needs to be stored, the telescopic side wings are contracted to the minimum, and the design size of the hangar is reduced.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicles, and in particular to a vertical take-off unmanned aerial vehicle with retractable wings. Background Art

[0002] Vertical take-off and landing fixed-wing aircraft can take off and land vertically like a helicopter, and can cruise forward in a fixed-wing manner. Compared with traditional helicopters, vertical take-off and landing fixed-wing aircraft have significant advantages such as fast forward flight speed, long range, and long flight time. Compared with conventional fixed-wing aircraft, vertical take-off and landing fixed-wing aircraft can take off and land at a fixed point and hover, and have no dependence on airport runways, and their mission capabilities are significantly enhanced. The above advantages have made this type of aircraft a hot research field in the world today.

[0003] However, in most operating scenarios, this type of aircraft also has the following problems:

[0004] 1. The flight range is generally between 200 and 360 km, and frequent return flights are required to replace the battery.

[0005] 2. For drones with a wingspan of more than five meters, operation and transportation require frequent disassembly and assembly, which requires an average of two people to work together. The operation takes a long time and is relatively cumbersome.

[0006] 3. The hangar for large-sized and medium-sized vertical take-off drones is too large to be conveniently deployed in the field, which is not conducive to unmanned operation.

[0007] In the existing technology, hybrid vertical take-off and landing UAVs are used to improve their endurance. Chengdu Zongheng Co., Ltd. is the first to launch a new product for various industries - "CW-25 hybrid vertical take-off and landing fixed-wing UAV", which can realize functions such as automatic inspection, automatic charging, remote deployment, remote planning and command, and automatic data transmission. It has a maximum load of 6 kg, a maximum cruising speed of 100 km / h, and a maximum load-carrying flight time of 360 minutes.

[0008] However, this solution still has shortcomings. Although the endurance of the drone has been improved, the size of the unmanned hangar built for this type of aircraft is large, with a wingspan of 4 meters. The long wingspan is also not conducive to taking off in a small space. Summary of the invention

[0009] In view of this, the present invention provides a vertical take-off drone with retractable wings to solve the problems raised in the above background technology, and specifically discloses the following contents:

[0010] A vertical take-off drone with telescopic wings comprises a fuselage, fixed wings are arranged on both sides of the fuselage, telescopic wings are slidably arranged inside the fixed wings, one end of the telescopic wing away from the fuselage penetrates the side wall of the fixed wing and extends outward, a telescopic drive component is also arranged inside the fixed wing, and the telescopic drive component is used to drive the telescopic wing to slide.

[0011] Furthermore, the telescopic drive assembly includes a motor, an active roller, a driven roller and a belt. A plurality of fixed wing ribs are evenly fixed inside the fixed wing, a plurality of telescopic wing ribs are evenly fixed inside the telescopic wing, the fixed wing ribs are provided with avoidance grooves matched with the telescopic wing ribs, the motor is fixedly arranged in the fuselage, the output end of the motor is fixedly connected to the active roller, the driven roller is installed on the fixed wing rib located on the outside through a mounting seat, one end of the belt is sleeved on the active roller, and the other end passes through the avoidance groove and is sleeved on the driven roller, a connecting block is fixedly provided on the belt, and the connecting block is fixedly connected to the telescopic wing rib located on the inside.

[0012] Furthermore, it also includes a fixed wing beam and a telescopic wing beam, one end of the fixed wing beam is fixedly connected to the fuselage, and the other end passes through the fixed wing rib located on the inner side and is sleeved on the telescopic wing beam, the fixed wing beam is fixedly connected to the fixed wing rib, the fixed wing beam is slidably connected to the telescopic wing beam, the end of the telescopic wing beam away from the fixed wing beam passes through a plurality of telescopic wing ribs, and the telescopic wing beam is fixedly connected to the telescopic wing rib.

[0013] Furthermore, a waterproof section is provided at the outer edge of the fixed side wing, and the waterproof section is inclined and arranged close to the direction of the telescopic side wing.

[0014] Furthermore, it also includes a tail wing and a vertical arm, the front end of the vertical arm is fixedly installed on the bottom of the fixed side wing, and the top of the rear end is fixedly connected to the tail wing, and the tail wing is located behind the fuselage.

[0015] Furthermore, the tail wing is an inverted V-shaped structure.

[0016] The beneficial effects of the present invention are:

[0017] The present invention can adjust the aspect ratio of the fixed wing and the telescopic wing according to the flight mode through the telescopic drive assembly; when the endurance needs to be improved, the telescopic wing is extended to the maximum length to increase the lift-to-drag ratio, improve the gliding performance, and increase the endurance; when it is necessary to fly in bad weather or take off in a small space, the telescopic wing is retracted to improve the engine power and wind resistance; when the UAV needs to be stored, the telescopic wing is retracted to the minimum to reduce the design volume of the hangar;

[0018] The present invention realizes the telescopic function of the telescopic wing and reduces the total weight of the UAV through the transmission combination of the motor and the belt;

[0019] The fixed wing beam of the present invention is sleeved on the telescopic wing beam, and the telescopic wing beam is slidably connected with the fixed wing beam to jointly share the bending moment from the fixed side wing and the telescopic side wing;

[0020] The waterproof section is inclined close to the telescopic side wing to reduce the gap at the connection between the fixed side wing and the telescopic side wing. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0022] Figure 1 The present invention is a three-dimensional diagram of a vertical take-off UAV with retractable wings.

[0023] Figure 2 The present invention is a front view of a vertical take-off UAV with retractable wings.

[0024] Figure 3 The present invention is a top view of a vertical take-off UAV with retractable wings.

[0025] Figure 4 It is a stereoscopic diagram of the telescopic drive assembly in the present invention.

[0026] Figure 5 It is a front view of the telescopic drive assembly in the present invention.

[0027] Figure 6 The schematic diagram of the circuit of the telescopic drive assembly controller in the present invention.

[0028] Among them, in the figure:

[0029] 1-fuselage; 2-fixed wing; 21-fixed wing rib; 22-fixed wing beam; 23-waterproof section; 3-telescopic wing; 31-telescopic wing rib; 32-telescopic wing beam; 4-vertical arm; 5-tail; 61-motor; 62-active roller; 63-driven roller; 64-belt; 641-connecting block. DETAILED DESCRIPTION

[0030] The technical solutions in the embodiments of the present invention are described clearly and completely below. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0031] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present application described here. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or components is not necessarily limited to those steps or components that are clearly listed, but may include other steps or components that are not clearly listed or inherent to these processes, methods, products or devices.

[0032] In the present application, the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings. These terms are mainly used to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to have a specific orientation, or to be constructed and operated in a specific orientation.

[0033] In addition, some of the above terms may be used to express other meanings in addition to indicating orientation or positional relationship. For example, the term "on" may also be used to express a certain dependency or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in this application can be understood according to specific circumstances.

[0034] In addition, the terms "installed", "set", "provided with", "connected", "connected", and "socketed" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection, or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be an internal connection between two devices, elements, or components. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0035] See attached Figure 1-6The present invention discloses a vertical take-off UAV with telescopic wings, comprising a fuselage 1, fixed wings 2 are arranged on both sides of the fuselage 1, telescopic wings 3 are slidably arranged inside the fixed wings 2, the telescopic wings 3 penetrate the side walls of the fixed wings 2 at one end away from the fuselage 1 and extend outward, a telescopic driving component is also arranged inside the fixed wings 2, and the telescopic driving component is used to drive the telescopic wings 3 to slide.

[0036] The telescopic drive assembly includes a motor 61, an active roller 62, a driven roller 63 and a belt 64. A plurality of fixed ribs 21 are evenly fixed inside the fixed wing 2, a plurality of telescopic ribs 31 are evenly fixed inside the telescopic wing 3, the fixed ribs 21 are provided with avoidance grooves matched with the telescopic ribs 31, the motor 61 is fixedly arranged in the fuselage 1, the output end of the motor 61 is fixedly connected to the active roller 62, the driven roller 63 is installed on the fixed rib 21 located on the outside through a mounting seat, one end of the belt 64 is sleeved on the active roller 62, and the other end passes through the avoidance groove and is sleeved on the driven roller 63, a connecting block 641 is fixedly arranged on the belt 64, and the connecting block 641 is fixedly connected to the telescopic rib 31 located on the inside.

[0037] In this embodiment, the fixed rib 21 is manufactured by CNC process.

[0038] In this embodiment, the motor 61 drives the active roller 62 to rotate, causing the belt 64 to rotate, and the connecting block 641 drives the telescopic side wing 3 to slide through the telescopic wing rib 31 to achieve the telescopic side wing 3. Through the transmission combination of the motor 61 and the belt 64, the telescopic function of the telescopic side wing 3 is achieved and the total weight of the drone is reduced.

[0039] In this embodiment, the fixed wing 2 is provided with limit switches at the left and right ends, and the telescopic wing 3 is provided with convex blocks corresponding to the limit switches. The belt 64 moves to drive the telescopic wing 3 to extend and retract, and the convex blocks stop moving when they touch the limit switches at the left and right ends. The movement stroke is 900 mm on one side (not shown in the above technical solution diagram);

[0040] When the UAV is performing a mission, it executes the waypoint "Do servo" command and outputs a PWM high and low level signal to the controller of the motor 61. The controller interprets the PWM signal, which is then processed by the single-chip microcomputer in the fuselage 1 to ultimately control the movement of the two motors 61 on the left and right sides. The sub-circuit where the two motors 61 are located has two normally closed limit switch modules. When the protrusion on the telescopic wing 3 performing the telescopic movement touches the limit switch, the normally closed limit switch module circuit is disconnected and the motor 61 stops working, thereby realizing the limit control of the telescopic wing 3.

[0041] The UAV also includes a fixed wing beam 22 and a telescopic wing beam 32. One end of the fixed wing beam 22 is fixedly connected to the fuselage 1, and the other end passes through the fixed wing rib 21 located on the inner side and is sleeved on the telescopic wing beam 32. The fixed wing beam 22 is fixedly connected to the fixed wing rib 21, and the fixed wing beam 22 is slidably connected to the telescopic wing beam 32. The end of the telescopic wing beam 32 away from the fixed wing beam 22 passes through multiple telescopic wing ribs 31, and the telescopic wing beam 32 is fixedly connected to the telescopic wing rib 31.

[0042] In this embodiment, the fixed wing beam 22 and the telescopic wing beam 32 are both carbon fiber tubes, which share the bending moments from the fixed wing 2 and the telescopic wing 3 .

[0043] A waterproof section 23 is provided at the outer edge of the fixed side wing 2 , and the waterproof section 23 is inclined toward the telescopic side wing 3 to reduce the gap at the connection between the fixed side wing 2 and the telescopic side wing 3 .

[0044] The UAV further includes a tail 5 and a vertical arm 4. The front end of the vertical arm 4 is fixedly installed at the bottom of the fixed wing 2, and the top of the rear end is fixedly connected to the tail 5. The tail 5 is located behind the fuselage 1.

[0045] The tail wing 5 is an inverted V-shaped structure.

[0046] In this embodiment, the telescopic drive assembly can adjust the aspect ratio of the fixed wing 2 and the telescopic wing 3 according to the flight mode, and freely switch between the three modes:

[0047] 1. Economic cruise mode: When the endurance needs to be increased, the retractable side wings 3 are extended to the maximum length, with an aspect ratio of 14.36, which increases the lift-to-drag ratio and improves the gliding performance. It is expected to increase the range by an additional 35%, with an estimated range of 450-650km;

[0048] 2. Strong wind resistance mode: When flying in bad weather or taking off in a small space, the retractable side wings 3 are retracted, with an aspect ratio of 9.7, which increases the engine power and wind resistance performance and enhances the safety of operations in extreme weather conditions;

[0049] When the wind speed reaches level 5, the flight control outputs a PWM signal to the motor 61 controlling the extension and retraction of the telescopic wing 3 according to the detection signal of the airspeed meter, so that the motor 61 drives the belt 64 to move, thereby retracting the telescopic wing 3. When the aspect ratio reaches 9.7, the fixed block touches the limit switch, and the motor 61 stops moving.

[0050] When the wind speed does not reach level 5, the flight control outputs a PWM signal to the motor 61 controlling the extension and retraction of the retractable wing 3 according to the detection signal of the airspeed meter, so that the motor 61 drives the belt 64 to move, thereby extending the retractable wing 3. When the display ratio reaches 14.36, the fixed block touches the limit switch, and the motor 61 stops moving;

[0051] 3. Hangar storage mode: When the drone needs to be stored, the retractable wings 3 are retracted to the minimum to reduce the design volume of the hangar.

[0052] The above are only preferred embodiments of the present application and are not intended to limit the present application. For those skilled in the art, the present application may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A vertical take-off drone with retractable wings, characterized in that: The invention comprises a fuselage (1), wherein fixed side wings (2) are arranged on both sides of the fuselage (1), and telescopic side wings (3) are slidably arranged inside the fixed side wings (2), and the telescopic side wings (3) extend outwardly through the side walls of the fixed side wings (2) at one end away from the fuselage (1), and further extend outwardly, and a telescopic driving component is arranged inside the fixed side wings (2), and the telescopic driving component is used to drive the telescopic side wings (3) to slide.

2. A vertical take-off drone with retractable wings according to claim 1, characterized in that: The telescopic drive assembly comprises a motor (61), an active roller (62), a driven roller (63) and a belt (64); a plurality of fixed ribs (21) are evenly fixedly arranged inside the fixed wing (2); a plurality of telescopic ribs (31) are evenly fixedly arranged inside the telescopic wing (3); the fixed ribs (21) are provided with avoidance grooves matched with the telescopic ribs (31); the motor (61) is fixedly arranged in the fuselage (1); the output end of the motor (61) is fixedly connected to the active roller (62); the driven roller (63) is mounted on the fixed rib (21) located on the outside through a mounting seat; one end of the belt (64) is sleeved on the active roller (62); the other end passes through the avoidance groove and is sleeved on the driven roller (63); a connecting block (641) is fixedly arranged on the belt (64); the connecting block (641) is fixedly connected to the telescopic rib (31) located on the inside.

3. A vertical take-off drone with retractable wings according to claim 2, characterized in that: It also includes a fixed wing beam (22) and a telescopic wing beam (32), one end of the fixed wing beam (22) is fixedly connected to the fuselage (1), and the other end passes through the fixed wing rib (21) located on the inner side and is sleeved on the telescopic wing beam (32), the fixed wing beam (22) is fixedly connected to the fixed wing rib (21), the fixed wing beam (22) is slidably connected to the telescopic wing beam (32), the end of the telescopic wing beam (32) away from the fixed wing beam (22) passes through a plurality of telescopic wing ribs (31), and the telescopic wing beam (32) is fixedly connected to the telescopic wing rib (31).

4. The vertical take-off drone with retractable wings according to claim 1, characterized in that: A waterproof section (23) is provided on the outer edge of the fixed side wing (2), and the waterproof section (23) is arranged obliquely in a direction close to the telescopic side wing (3).

5. The vertical take-off drone with retractable wings according to claim 1, characterized in that: It also includes a tail wing (5) and a vertical arm (4), wherein the front end of the vertical arm (4) is fixedly mounted on the bottom of the fixed wing (2), and the top of the rear end is fixedly connected to the tail wing (5), and the tail wing (5) is located behind the fuselage (1).

6. A vertical take-off drone with retractable wings according to claim 5, characterized in that: The tail wing (5) is an inverted V-shaped structure.

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