Unmanned aerial vehicle structure without rotor wings

Abstract

The invention provides a rotor-free unmanned aerial vehicle structure, and relates to the technical field of deformation unmanned aerial vehicles, the rotor-free unmanned aerial vehicle structure comprises a main vehicle body, the top of the main vehicle body is provided with four groups of air inlet channels penetrating up and down, the inner side of the bottom of each air inlet channel is of a bucket-shaped structure, and the outer side of the bottom of each air inlet channel is fixedly provided with a motor bin; branches are arranged outside the upper portion of the motor bin, air outlet bent pipes are rotationally arranged outside the branches in cooperation with the light bearings, and the air outlet bent pipes are bent downwards by a quarter of a circle. Two groups of limiting guide rods are fixedly arranged at the top of the main machine body; the side auxiliary wing frames are arranged, an auxiliary flight structure capable of deforming is provided, stretching and retracting of the side auxiliary wing frames and the auxiliary wings are driven by the control lead screws, storage and placement in a conventional state are not affected, the angles of the auxiliary wings can be independently adjusted and controlled, the auxiliary flight effect is achieved, power consumption is saved, and the endurance is prolonged; the problem that an existing unmanned aerial vehicle lacks an auxiliary flight structure is solved.

Description

Technical Field

[0001] The invention relates to the technical field of deformable unmanned aerial vehicles, and in particular to a rotorless unmanned aerial vehicle structure. Background Art

[0002] Conventional UAVs are mainly rotor UAVs, which have four or six sets of wing brackets to carry lift blades. The UAV is lifted by spiral lift. In order to ensure lift, the blades are generally exposed and lack protection. Therefore, there are great hidden dangers in the blades. They are easy to touch external obstacles during the mission, affecting flight or even causing damage.

[0003] The drones currently in use have the following disadvantages: 1. The propeller blades are moved in and out directly to control the airflow for flight, which increases the overall occupancy of the drone and is inconvenient to store. All propeller blades need to work synchronously during flight, and there is a lack of auxiliary flight structure that does not affect storage and can be deformed; 2. There is a lack of a stable and controllable jet angle control structure. The method of flying by differential speed will produce more losses, which is not conducive to continuous flight; 3. There is a lack of an easily replaceable battery life structure, and the charging time is long. Summary of the invention

[0004] In view of this, the present invention provides a rotorless UAV structure to address the deficiencies in the above-mentioned prior art.

[0005] The present invention provides a rotorless drone structure, specifically comprising: a main body, wherein four groups of air intake channels running through the upper and lower parts are provided on the top of the main body, the bottom inner side of the air intake channel is a bucket-shaped structure, and a motor compartment is fixedly arranged on the bottom outer side of the air intake channel; branches are arranged on the upper and outer sides of the motor compartment, and air outlet elbows are rotatably arranged on the outside of the branches in cooperation with light bearings, and the air outlet elbows are turned downward by a quarter of a circle; two groups of limiting guide rods are fixedly arranged on the top of the main body, antennas are arranged inside the limiting guide rods to provide signal transmission, and a deflector is slidably arranged on the top of the main body in cooperation with the two groups of limiting guide rods; side auxiliary wing frames are slidably arranged on the upper middle parts of both sides of the main body, auxiliary wings are hingedly arranged on the outside of the side auxiliary wing frames, and flange structures for limiting are integrally arranged on the outside of the auxiliary wings; a detachable battery is fixedly installed in the middle of the bottom of the main body through a threaded connection; four groups of level sensors are also arranged on the two side ends of the main body; the outer edges of the main body and the auxiliary wings are chamfered to adapt to the airflow and reduce wind resistance.

[0006] Optionally, a lift rotating frame for maintaining lift is fixedly arranged on the upper part of the interior of the air inlet passage, and a double-slope structure is arranged on the upper part of both sides of the rotating frame; a lift motor is fixedly arranged on the inside of the motor compartment, and lift blades are fixedly arranged on the outside of the rotor end of the lift motor, and the rotor end of the lift motor is rotatably arranged in the rotating frame.

[0007] Optionally, the air deflector is integrated with four groups of cylindrical structures that fit and slide with the air intake channel. After the side auxiliary wing frame is extended, the air deflector can naturally fall into the air intake channel, and the bottom edge of the air deflector is set as a slope structure with high sides and low middle.

[0008] Optionally, an internal control motor is fixedly installed in the middle and upper part of the air deflector; two grooves are opened on both sides of the middle of the main body, and control screws are rotatably installed in the grooves. The internal control motor and the two sets of control screws are connected by bevel gear transmission; a protrusion is provided at the bottom of one end of the side auxiliary wing frame located in the main body and is threadedly connected to the control screw to form a threaded transmission.

[0009] Optionally, a control micro-electric cylinder is fixedly arranged in the middle of the outer side of the side auxiliary wing frame, the control micro-electric cylinder is installed in a horizontal direction, and a control shaft rod is fixedly arranged outside the telescopic end of the control micro-electric cylinder.

[0010] Optionally, a groove is provided at the upper middle portion of one side of the auxiliary wing close to the side auxiliary wing frame, a control bevel groove is provided on the inner wall of the groove, and the control shaft rods are fitted and slid in one of the control bevel grooves.

[0011] Optionally, an outer ring cover is integrally provided on the outside of the mounting end of the air outlet bend pipe, and a gear ring structure is integrally provided on the edge of the portion of the air outlet bend pipe located inside the outer ring cover; a micro servo motor is fixedly provided on the outside of the branch of the motor compartment, and gears are fixedly provided on the shaft ends of the micro servo motors to mesh with the gear ring outside the air outlet bend pipe; a protective shell is also provided on the outside of the micro servo motor.

[0012] Optionally, two columns of battery contacts are fixedly disposed at the middle of the top of the disassembled battery, and two groups of electrode rings are fixedly disposed at the bottom of the main body, and each column of battery contacts can fit with a group of electrode rings.

[0013] Optionally, the main body and auxiliary wings are made of low-weight carbon fiber material, and the motor compartment and the air outlet elbow are made of low-weight propylene polymer plastic material.

[0014] The beneficial effects are as follows: 1. The present invention is provided with a side auxiliary wing frame, which provides a deformable auxiliary flight structure. The extension and retraction of the side auxiliary wing frame and the auxiliary wing are driven by a control screw, which does not affect the storage and placement in a normal state, and does not affect the air passing through the rotating frame during operation. The rotating frame is centrally arranged, which can replace the drive of the rotor and avoid the risk of collision. In addition, the angle of the auxiliary wing can also be adjusted and controlled separately to achieve the auxiliary flight effect, save power consumption, and increase endurance.

[0015] 2. An air outlet bend is set up to provide a stably controllable jet structure. The micro servo motor is started to drive the air outlet bend to rotate, so that the air outlet angle of the air outlet bend can be adjusted, and then the rotation speed of each lift blade can be adjusted to achieve directional movement. In addition, the auxiliary wing can assist in gliding, using the rear lift blades as the main thrust and reducing the power consumption of the front lift blades to reduce power consumption. Multiple flight modes can be used flexibly.

[0016] 3. The removable battery provides a battery life structure that is easy to replace. The removable battery can be removed for replacement. Power can be provided by contacting the electrode ring with the battery contacts, which is more convenient than charging. The removable battery also serves as a counterweight to maintain the balance of the drone. It also serves as a fault-tolerant structure. If the removable battery is not installed, it cannot provide power. Therefore, installing a removable battery will inevitably provide a counterweight. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A schematic diagram of the working state structure of an embodiment of the present invention is shown; Figure 2 A schematic diagram of the structure in a contracted state of an embodiment of the present invention is shown; Figure 3 A schematic diagram of a three-dimensional disassembled structure of an embodiment of the present invention is shown; Figure 4 The embodiment of the present invention is shown Figure 3 A schematic diagram of the structure from another angle; Figure 5 The embodiment of the present invention is shown Figure 4 Schematic diagram of the side elevation structure; Figure 6 The embodiment of the present invention is shown Figure 5 Schematic diagram of the back structure; Figure 7 A schematic diagram of the three-dimensional structure of the auxiliary wing in an embodiment of the present invention is shown; Figure 8 The embodiment of the present invention is shown Figure 4 Schematic diagram of the local enlarged structure at A in the figure.

[0018] Reference numerals list 1. Main body; 101. Air inlet channel; 102. Rotating frame; 103. Motor compartment; 104. Lift blades; 2. Fairing; 3. Internal control motor; 4. Control screw; 5. Side auxiliary wing frame; 501. Control micro-electric cylinder; 502. Control shaft; 6. Auxiliary wing; 601. Control chute; 7. Air outlet elbow; 701. Outer ring cover; 8. Micro servo motor; 9. Disassemble battery; 901. Battery contacts; 10. Electrode ring. DETAILED DESCRIPTION

[0019] In order to make the purpose, scheme and advantages of the technical solution of the present invention clearer, the technical solution of the embodiment of the present invention will be clearly and completely described below in conjunction with the drawings of specific embodiments of the present invention.

[0020] Example 1: Please refer to the attached drawings in the specification. Figures 1 to 8 As shown: The present invention proposes a rotorless drone structure, comprising: a main body 1, four groups of air intake channels 101 penetrating up and down are opened on the top of the main body 1, the bottom inner side of the air intake channel 101 is a bucket-shaped structure, and the bottom outer side of the air intake channel 101 is fixedly provided with a motor compartment 103; branches are provided on the upper outer side of the motor compartment 103, and air outlet elbows 7 are rotatably provided on the outside of the branches in cooperation with light bearings, and the air outlet elbows 7 are bent downward by a quarter of a circle; two groups of limiting guide rods are fixedly provided on the top of the main body 1, and antenna lifting devices are provided inside the limiting guide rods. For signal transmission, a deflector 2 is slidably arranged on the top of the main body 1 in cooperation with two groups of limiting guide rods; side auxiliary wing frames 5 are slidably arranged on the upper middle of both sides of the main body 1, and auxiliary wings 6 are hingedly arranged on the outside of the side auxiliary wing frames 5, and the outside of the auxiliary wings 6 are integrally provided with a flange structure for limiting; a disassembly battery 9 is fixedly installed in the middle of the bottom of the main body 1 through a threaded connection; four groups of level sensors are also arranged on both side ends of the main body 1; the outer edges of the main body 1 and the auxiliary wings 6 are chamfered to adapt to the airflow and reduce wind resistance.

[0021] Among them, a lift rotating frame 102 for holding the lift is fixedly arranged on the upper part of the interior of the air inlet channel 101, and a double-slope structure is arranged on the upper part of both sides of the rotating frame 102; a lift motor is fixedly arranged on the inside of the motor compartment 103, and lift blades 104 are fixedly arranged on the outside of the rotor end of the lift motor, and the rotor end of the lift motor is rotatably arranged in the rotating frame 102.

[0022] Among them, the air deflector 2 is integrated by four groups of cylindrical structures that fit and slide with the air intake channel 101. After the side auxiliary wing frame 5 is extended, the air deflector 2 can naturally fall into the air intake channel 101, and the bottom edge of the air deflector 2 is set as a slope structure with high sides and low middle.

[0023] Among them, an internal control motor 3 is fixedly installed in the middle and upper part of the air deflector 2; two grooves are opened on both sides of the middle of the main body 1, and control screws 4 are rotatably installed in the grooves. The internal control motor 3 and the two sets of control screws 4 are connected by bevel gear transmission; a convex piece is set at the lower part of one end of the side auxiliary wing frame 5 located in the main body 1 and is threadedly connected with the control screw 4 to form a threaded transmission.

[0024] Among them, a control micro-electric cylinder 501 is fixedly arranged in the middle of the outer side of the side auxiliary wing frame 5. The control micro-electric cylinder 501 is installed in a horizontal direction. A control shaft rod 502 is fixedly arranged outside the telescopic end of the control micro-electric cylinder 501.

[0025] A groove is provided at the upper middle part of one side of the auxiliary wing 6 close to the side auxiliary wing frame 5 , and a control inclined groove 601 is provided on the inner wall of the groove. The control shaft rod 502 fits and slides in one of the control inclined grooves 601 .

[0026] Among them, the installation end of the air outlet bend pipe 7 is integrally provided with an outer ring cover 701 on the outside, and the edge of the part of the air outlet bend pipe 7 located inside the outer ring cover 701 is integrally provided with a gear ring structure; the branch of the motor compartment 103 is fixedly provided with a micro servo motor 8 on the outside, and the shaft end of the micro servo motor 8 is fixedly provided with a gear that meshes with the gear ring outside the air outlet bend pipe 7; a protective shell is also provided on the outside of the micro servo motor 8.

[0027] Among them, two rows of battery contacts 901 are fixedly arranged at the middle of the top of the disassembled battery 9 , and two groups of electrode rings 10 are fixedly arranged at the bottom of the main body 1 , and each row of battery contacts 901 can fit with a group of electrode rings 10 .

[0028] The main body 1 and the auxiliary wing 6 are made of low-weight carbon fiber material, and the motor compartment 103 and the air outlet elbow 7 are made of low-weight propylene polymer plastic material.

[0029] like Figure 1-8 As shown, according to the use requirements, a camera or a load is set at the bottom of the main body 1 to perform work; Start the internal control motor 3 to cooperate with the bevel gear to drive the control screws 4 on both sides to rotate, and use the control screws 4 to extend the side auxiliary wing frames 5 on both sides to a position slightly beyond the main body 1. At this time, the auxiliary wings 6 are completely extended, and the side auxiliary wing frames 5 no longer cover the air intake channel 101. The deflector 2 naturally descends into the air intake channel 101, closing the horizontal slot in the main body 1 for accommodating the side auxiliary wing frames 5, and keeping the airflow descending vertically; When taking off, the outlet elbow 7 is kept in the right direction, and the lift motor is directly started to drive each group of lift blades 104 to rotate. The lift blades 104 are used to generate airflow, and the airflow is compressed by the internal bucket-shaped structure of the air inlet channel 101 and then pressurized and ejected from the outlet elbow 7 to generate lift to lift the drone as a whole. Then, the micro servo motor 8 is started to drive the outlet elbow 7 to rotate, and the outlet angle of the outlet elbow 7 can be adjusted, and then the rotation speed of each lift blade 104 can be adjusted to achieve directional movement. The auxiliary wing 6 can assist in gliding, using the rear lift blades 104 as the main thrust, reducing the power consumption of the front lift blades 104 and thus reducing power consumption; adjusting the angle of the auxiliary wing 6 can adjust the force, using the gliding force to climb, controlling the extension and retraction of the micro-electric cylinder 501, driving the control shaft 502 to move, and the control shaft 502 sliding in the control inclined groove 601 can cause the angle of the auxiliary wing 6 to change, thereby achieving the adjustment of the angle of the auxiliary wing 6.

[0030] Embodiment 2: Based on Embodiment 1, a pulley can be installed at the bottom of the main body 1 or the motor compartment 103 to simulate the use of a model airplane. Thrust is generated by adjusting the outlet angle of the outlet elbow 7, and lift is generated by adjusting the angle of the auxiliary wing 6. By combining the two, the airplane can fly at the location of the runway, which is suitable for situations where high-altitude operations are required. The principle of airplane takeoff mainly depends on aerodynamics and wing design. When the airplane glides and accelerates on the runway, the thrust generated by the engine makes the airplane move forward. When the air flows through the wing, due to the streamlined design of the wing, the air flow speeds on the upper and lower surfaces of the wing are different. According to the Bernoulli principle, the air pressure on the upper surface with a larger flow rate is lower, while the air pressure on the lower surface is higher, thereby generating an upward pressure difference between the upper and lower surfaces, that is, lift. Therefore, this effect can be achieved by adjusting the angle of the auxiliary wing 6 and using the outlet elbow 7 to drive.

[0031] Embodiment 3: Based on Embodiment 1, when the power is insufficient, the drone returns to the home position through a program, and the battery 9 can be removed and replaced. The battery contact 901 can be used to contact the electrode ring 10 to provide power, which is more convenient than charging. The disassembled battery 9 also serves as a counterweight to maintain the balance of the drone, and also as a fault-tolerant structure. If the disassembled battery 9 is not installed, no power can be provided. Therefore, installing the disassembled battery 9 will inevitably provide a counterweight.

[0032] Specific usage and function of this embodiment: In the present invention, the signal transmission is performed through the hidden antenna, and the guide rod outside the antenna also provides the effect of limiting the deflector 2 and assisting its sliding; According to the use requirements, a camera or a load is arranged at the bottom of the main body 1 to perform the work; Start the internal control motor 3 to cooperate with the bevel gear to drive the control screws 4 on both sides to rotate, and use the control screws 4 to extend the side auxiliary wing frames 5 on both sides to a position slightly beyond the main body 1. At this time, the auxiliary wings 6 are completely extended, and the side auxiliary wing frames 5 no longer cover the air intake channel 101. The deflector 2 naturally descends into the air intake channel 101, closing the horizontal slot in the main body 1 for accommodating the side auxiliary wing frames 5, and keeping the airflow descending vertically; When taking off, the outlet elbow 7 is kept in the right direction, and the lift motor is directly started to drive each group of lift blades 104 to rotate. The lift blades 104 are used to generate airflow, and the airflow is compressed by the internal bucket-shaped structure of the air inlet channel 101 and then pressurized and ejected from the outlet elbow 7 to generate lift to lift the drone as a whole. Then, the micro servo motor 8 is started to drive the outlet elbow 7 to rotate, and the outlet angle of the outlet elbow 7 can be adjusted, and then the rotation speed of each lift blade 104 can be adjusted to achieve directional movement. The auxiliary wing 6 can assist in gliding, using the rear lift blades 104 as the main thrust, and reducing the power consumption of the front lift blades 104 can reduce power consumption; Adjusting the angle of the auxiliary wing 6 can adjust the force, and use the sliding force to climb, control the micro-electric cylinder 501 to extend and retract, drive the control shaft 502 to move, and the control shaft 502 slides in the control inclined groove 601, which can cause the angle of the auxiliary wing 6 to change, thereby realizing the adjustment of the angle of the auxiliary wing 6; When the power is insufficient, the UAV returns home through a program, and the disassembled battery 9 can be removed for replacement. The battery contact 901 can be used to contact the electrode ring 10 to provide power, which is more convenient than charging. The disassembled battery 9 also serves as a counterweight to maintain the balance of the UAV, and also as a fault-tolerant structure. If the disassembled battery 9 is not installed, it cannot provide power, so installing the disassembled battery 9 will inevitably provide a counterweight.

Claims

1. A rotorless drone structure, characterized in that: include: A main body (1), the top of the main body (1) is provided with four groups of air inlet channels (101) penetrating vertically, the bottom inner side of the air inlet channel (101) is a bucket-shaped structure, and the bottom outer side of the air inlet channel (101) is fixedly provided with a motor compartment (103); the upper outer side of the motor compartment (103) is provided with a branch, and the outer side of the branch is provided with an air outlet elbow (7) rotatably arranged in cooperation with a light bearing, and the air outlet elbow (7) is bent downward by a quarter of a turn; two groups of A limit guide rod, a deflector (2) is slidably arranged on the top of the main body (1) in cooperation with two sets of limit guide rods; side auxiliary wing frames (5) are slidably arranged on the upper middle of both sides of the main body (1), auxiliary wings (6) are hingedly arranged on the outside of the side auxiliary wing frames (5), and flange structures for limiting are integrally arranged on the outside of the auxiliary wings (6); a disassembly battery (9) is fixedly installed in the middle of the bottom of the main body (1) through a threaded connection; and four sets of level sensors are also arranged on the two side ends of the main body (1).

2. A rotorless drone structure as claimed in claim 1, characterized in that: A lift rotating frame (102) for holding the lift is fixedly arranged above the interior of the air inlet passage (101), and both sides of the rotating frame (102) are provided with a double inclined surface structure above the interior; a lift motor is fixedly arranged inside the motor compartment (103), and lift blades (104) are fixedly arranged outside the rotor end of the lift motor, and the rotor end of the lift motor is rotatably arranged in the rotating frame (102).

3. A rotorless drone structure as claimed in claim 1, characterized in that: The air deflector (2) is formed by integrating four groups of cylindrical structures that fit and slide with the air inlet passage (101); after the side auxiliary wing frame (5) is extended, the air deflector (2) can naturally fall into the air inlet passage (101); and the bottom edge of the air deflector (2) is arranged as an inclined structure with high sides and low middle.

4. A rotorless drone structure as claimed in claim 1, characterized in that: An internal control motor (3) is fixedly arranged at the middle upper part of the deflector (2); two grooves are opened at both sides of the middle of the main body (1), and control screws (4) are rotatably arranged in the grooves, and the internal control motor (3) and the two sets of control screws (4) are arranged to be connected by bevel gear transmission; a convex piece is arranged at the lower part of one end of the side auxiliary wing frame (5) located in the main body (1) and is threadedly connected to the control screw (4), thereby forming a threaded transmission.

5. A rotorless drone structure as claimed in claim 1, characterized in that: A control micro-electric cylinder (501) is fixedly arranged in the middle of the outside of the side auxiliary wing frame (5), the control micro-electric cylinder (501) is installed in a horizontal direction, and a control shaft rod (502) is fixedly arranged outside the telescopic end of the control micro-electric cylinder (501).

6. A rotorless drone structure as claimed in claim 5, characterized in that: A groove is provided at the middle upper part of one side of the auxiliary wing (6) close to the side auxiliary wing frame (5), and a control inclined groove (601) is provided on the inner wall of the groove. The control shaft rod (502) is fitted and slidably connected in one of the control inclined grooves (601).

7. A rotorless drone structure as claimed in claim 1, characterized in that: The mounting end of the outlet bend pipe (7) is integrally provided with an outer ring cover (701), and the edge of the portion of the outlet bend pipe (7) located inside the outer ring cover (701) is integrally provided with a gear ring structure; a micro servo motor (8) is fixedly provided on the outside of the branch of the motor compartment (103), and a gear is fixedly provided on the shaft end of the micro servo motor (8) to mesh with the gear ring outside the outlet bend pipe (7); and a protective shell is also provided on the outside of the micro servo motor (8).

8. A rotorless drone structure as claimed in claim 1, characterized in that: Two rows of battery contacts (901) are fixedly arranged at the middle of the top of the detachable battery (9), and two groups of electrode rings (10) are fixedly arranged at the bottom of the main body (1), and each row of battery contacts (901) can fit with a group of electrode rings (10).

9. A rotorless drone structure as claimed in claim 7, characterized in that: The main body (1) and the auxiliary wing (6) are made of low-weight carbon fiber material, and the motor compartment (103) and the air outlet elbow (7) are made of low-weight propylene polymer plastic material.

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