A safe and stable transport drone

Abstract

The invention discloses a safe and stable transport UAV, comprising a fuselage, a rotor mechanism and a tail mechanism, wherein the fuselage comprises a bottom plate, a left side plate, a right side plate and a top cover, wherein the top cover and the bottom plate intersect at the front and rear parts of the fuselage and enclose a Clark Y-wing structure with a relative thickness of 21%; the fuselage comprises a middle fuselage and a left fuselage and a right fuselage on both sides of which are slidably connected to the middle fuselage; the rotor mechanism adopts a tilt-rotor design, comprising a rotor body, which is a pair of ducted rotors symmetrically arranged on both sides of the fuselage and related fixings and a steering gear and a tilt control rod for controlling the tilting action. The tail mechanism comprises a mounting frame arranged at the lower rear part of the fuselage and a tail body connected to the mounting frame and rotatable relative to the mounting frame. The invention has the advantages of high flight speed, long range, foldability, safety and stability, etc.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to a safe and stable transport unmanned aerial vehicle. Background Art

[0002] With the development of modern logistics and drone technology, combined with the current situation of urban expansion and busy traffic, drone transportation has attracted more and more attention from express delivery companies and ordering platforms. Drone transportation has the advantages of wide transportation range, fast delivery speed, and no restrictions on traffic conditions. However, there are the following problems in the drones currently in use: 1. The fuselage cannot be adjusted, the overall structure is large, and it occupies a large space, which is not suitable for carrying; if it is carried and stored, it needs to be disassembled before and after use; it is time-consuming and laborious; 2. The fuselage lacks aerodynamic design, the flight resistance is large, and the flight speed is slow; the lift is completely dependent on the thrust of the motor, resulting in a small horizontal component of the motor thrust and insufficient forward power; and the flight power consumption is large and the range is short; 3. There is no storage space in the fuselage, and the goods are mostly transported by lifting, which interferes with the center of gravity of the drone, reduces maneuverability, increases resistance during lifting, and has low economic benefits; 4. Traditional rotor drones lack redundant control capabilities, and the rotors are exposed, which poses a safety hazard.

[0003] Traditional rotary-wing drones have low flight time, slow speed, and great safety risks, while traditional fixed-wing drones are not suitable for urban environments due to site restrictions. Therefore, there is an urgent need for a drone design that can meet the requirements of vertical take-off and landing and has the ability to fly long distances and at high speeds. Summary of the invention

[0004] The object of the present invention is to provide a safe and stable transport UAV with compact structure, adjustable fuselage, high flight speed and long range, and capable of vertical take-off and landing.

[0005] Based on the above objectives, the present invention adopts the following technical scheme: a safe and stable transport drone, including a fuselage, a rotor mechanism and a tail mechanism, the fuselage including a bottom plate, a left plate and a right plate on both sides of the bottom plate, and a top cover connecting the tops of the left plate and the right plate, the top cover is a streamlined structure design that arches upward, the bottom plate includes a left bottom plate, a middle bottom plate and a right bottom plate, the top cover includes a front middle top cover, a rear middle top cover, a left top cover and a right top cover; the left bottom plate, the left side plate and the left top cover together constitute the left fuselage; the right bottom plate, the right side plate and the right top cover together constitute the right The fuselage; the middle bottom plate, the front middle top cover and the rear middle top cover together constitute the middle fuselage; the left fuselage, the middle fuselage and the right fuselage are hollow structures with inner chambers; the left fuselage and the right fuselage have the same structure and are symmetrically arranged on the left and right sides of the middle fuselage, the left fuselage and the right fuselage are slidably connected to the middle fuselage, and the left fuselage and the right fuselage move horizontally relative to the middle fuselage to extend / receive into the inner chamber of the middle fuselage; at least one of the front middle top cover and the rear middle top cover can rotate up and down relative to the middle bottom plate to open / close the inner chamber of the middle fuselage;

[0006] The rotor mechanism includes a rotor body, a drive unit for controlling the tilting action, and a remote control receiver for controlling the drive unit, wherein the drive unit includes a pair of servos symmetrically arranged on the left fuselage and the right fuselage, and a tilt control rod connected to the servos; the rotor body is a pair of ducted rotors symmetrically arranged on both sides of the fuselage, and the ducted rotors are connected to the tilt control rod; the ducted rotor includes a pair of ducts and a first connecting member for connecting the pair of ducts, the pair of ducts are symmetrically arranged at both ends of the first connecting member, and the duct is a hollow truncated cone structure formed by smoothly connecting two ports through an inwardly protruding arc transition surface; a support frame is provided inside the duct;

[0007] The tail mechanism comprises a mounting frame arranged at the lower rear part of the fuselage and a tail body connected to the mounting frame and rotatable relative to the mounting frame.

[0008] Preferably, the width of the middle fuselage is smaller than the sum of the widths of the left fuselage and the right fuselage, a slide rail is provided in the middle of the middle bottom plate, and a first sliding block sliding left and right along the slide rail is provided at a position corresponding to the slide rail at one end of the left bottom plate close to the middle bottom plate; a second sliding block sliding left and right along the slide rail is provided at a position corresponding to the slide rail at one end of the right bottom plate close to the middle bottom plate.

[0009] Preferably, the front middle top cover is rotatably connected to the front end of the middle bottom plate by a first pin shaft; a pair of downward first connecting rods are provided at the front end of the front middle top cover, a first pin hole is provided on the first connecting rod, a first groove for accommodating the pair of first connecting rods is provided at a corresponding position on the middle bottom plate, a first positioning column is provided in the middle of the first groove, the first positioning column is a "U"-shaped structure, the pair of first connecting rods are located in the "U"-shaped opening of the first positioning column, a first through hole is provided on the first positioning column, the first pin shaft passes through the first pin hole and the first through hole to rotatably connect the front middle top cover and the middle bottom plate; a first compression spring is sleeved on the first pin shaft, one end of the first compression spring is fixedly connected to the front middle top cover, and the other end of the first compression spring is fixedly connected to the middle bottom plate, and the first compression spring is sleeved on the first pin shaft located between the pair of first connecting rods;

[0010] The rear middle top cover is rotatably connected to the rear end of the middle bottom plate by a second pin shaft; a pair of downward second connecting rods are provided at the rear end of the rear middle top cover, and a second pin hole is provided on the second connecting rod, and a second groove for accommodating the pair of second connecting rods is provided at a corresponding position on the middle bottom plate, and a second positioning column is provided in the middle of the second groove, and the second positioning column is a "U"-shaped structure, and the pair of second connecting rods are located in the "U"-shaped opening of the second positioning column, and a second through hole is provided on the second positioning column, and the second pin shaft passes through the second pin hole and the second through hole, and the rear middle top cover is rotatably connected to the middle bottom plate, and a second compression spring is sleeved on the second pin shaft, one end of the second compression spring is fixedly connected to the rear middle top cover, and the other end of the second compression spring is fixedly connected to the middle bottom plate, and the second compression spring is sleeved on the second pin shaft located between the pair of second connecting rods.

[0011] Preferably, the support frame includes a motor seat and a plurality of support rods evenly distributed along the circumference of the motor seat, the center line of the motor seat coincides with the center line of the duct, the motor seat is provided with a motor, the motor is connected with a blade, the two ends of the support rod are respectively connected to the motor seat and the inner wall of the duct, the inner wall of the duct is evenly provided with positioning grooves along the circumference, and the length of the support rod is adjustable; the support rods include a front end support rod, an adjusting bolt, and a rear end support rod, the first end of the front end support rod is inserted into the positioning groove, the second end of the front end support rod is connected to the first end of the adjusting bolt, the second end of the adjusting bolt is connected to the first end of the rear end support rod, and the second end of the rear end support rod is connected to the motor seat.

[0012] Preferably, the inner wall of the duct is provided with a noise reduction layer made of sound-absorbing material, the first connecting member connecting the duct is a fixed plate with a resistance-reducing leakage hole, and at least one outer side of the fixed plate is provided with a second connecting member for connecting the tilt control rod; the second connecting member is a sleeve adapted to the tilt control rod structure, and the second connecting member is sleeved with the tilt control rod; the windward surfaces of the front end support rod and the rear end support rod are both arc-shaped structures, and the cross-sections of the front end support rod and the rear end support rod are both long teardrop-shaped structures.

[0013] Preferably, the tail body includes a mounting rod, which is fixed on the mounting frame and can rotate relative to the mounting frame. Tail rods are fixed to the rear parts of both ends of the mounting rod. The two tail rods are arranged in parallel. A vertical stabilizer surface is arranged on the lower surface of the rear end of each tail rod, and a horizontal stabilizer surface is arranged between the two vertical stabilizers.

[0014] Preferably, the mounting frame includes two clamping plates relatively arranged on the outer side of the lower tail of the UAV fuselage, and slots for inserting the mounting rod are arranged on the relatively inner sides of the clamping plates; a tail servo pod is arranged between the two clamping plates, and the tail servo pod is fixed in the center of the lower rear part of the fuselage, and an adjusting tooth is penetrated in the middle of the mounting rod and located in the tail servo pod, and the adjusting tooth is fixedly connected to the mounting rod and meshes with the gear of the tail servo in the tail servo pod.

[0015] Preferably, the tail boom is a carbon fiber boom; the vertical stabilizer and the horizontal stabilizer both include a carbon fiber layer, a radar transparent layer, a radar absorbing layer and a radar reflecting layer are arranged on the surface of the carbon fiber layer, and the radar absorbing layer is a polyimide film layer.

[0016] Preferably, the vertical stabilizer and the horizontal stabilizer both include a carbon fiber layer, and an infrared stealth coating is provided on the surface of the carbon fiber layer.

[0017] Preferably, the top cover and the bottom plate meet at the front and rear parts of the fuselage and form a Clark Y-wing structure with a relative thickness of 21%; the cross-sectional shape of the fuselage is a double-convex wing structure or a flat-convex wing structure.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] 1. The fuselage in the present invention is a streamlined structure, and the cross-sectional shape of the lifting body fuselage is a Clark Y-shaped airfoil with a relative thickness of 21%, which has low resistance and large lift coefficient. The lift provided can reduce the burden on the motor and reduce power consumption. In addition, the lifting body design provides sufficient internal space, which can be used to store goods in the hollow cabin. The goods will not increase the resistance of the drone during flight, and the economic benefits are high. When not transporting goods, the left fuselage and the right fuselage can be horizontally moved relative to the middle fuselage and stored in the middle fuselage, making the drone structure compact, reducing the size of the drone, and easy to carry.

[0020] 2. The rotor in the present invention adopts a tilt-rotor design. When the drone takes off, a pair of ducted rotors are horizontal relative to the ground, and the thrust direction is vertically downward, pushing the drone to rise vertically. At this time, the steering and movement of the drone can be controlled by the remote control receiver to control the action of the servo. The servo drives the ducted rotor to rotate through the tilt control lever, adjusts the inclination angle of the ducted rotor, and provides a horizontal component for steering. This steering method is more efficient than the traditional drone steering method of adjusting the motor speed, and can always keep the fuselage horizontal, which is conducive to the transportation of goods. When the drone rises to the cruising altitude, the servo drives the ducted rotor to rotate to a vertical state relative to the ground. At this time, the thrust direction is backward to achieve a higher speed. The gravity of the fuselage is offset by the lift provided by the fuselage. When the drone turns, a pair of ducted rotors can be relatively tilted according to the turning angle and turning direction, and the servo drives the corresponding ducted rotors to rotate to a suitable angle to provide a steering torque. At the same time, the thrust size can be adjusted to achieve vector steering through the thrust difference. When the drone is flying, the overall stability is good.

[0021] 3. The duct in the ducted rotor is a hollow truncated cone structure formed by smoothly connecting two ports through an inwardly protruding arc transition surface. During the flight of the drone, the windward side of the duct is an expanded structure and the leeward side is a contracted structure. This structural design can comb the airflow, reduce the vortex interference between the rotors, and thus improve the aerodynamic efficiency of the rotors; it plays a role in diverting the wind, which in disguise increases the density of the airflow passing through the blades and increases the thrust. Secondly, the inner wall of the duct is provided with a noise reduction layer made of sound-absorbing material, which plays a role in blocking sound waves to a certain extent, reducing noise pollution, and is suitable for urban environments. At the same time, the design of the duct in the present invention solves the problem that the exposed propellers of the existing drones are entangled with branches and wires or break due to collision with obstacles during flight, and fall from a height to injure people. A support frame is provided in the duct in the present invention, which can improve the strength of the duct structure, thereby contributing to safe and stable flight. The length of the support rod in the present invention is adjustable. By adjusting the length of the support rod, it is convenient to quickly install the duct and the support frame in place, or to conveniently remove the support frame from the duct for replacement, maintenance and cleaning. At the same time, the support rod is designed as a length-adjustable structure so that the support frame can be applied to ducts of different apertures. The cross-section of the support rod in the present invention is a long teardrop-shaped structure, so that the support rod plays the role of supporting and fixing the duct, and reduces the air resistance acting on the support rod.

[0022] In addition, the duct in the present invention can also control the posture of the fuselage in an emergency (such as a loss of power in the air). When a motor of an ordinary quadcopter loses power, it will be completely out of control, fall to the ground, damage the drone, and may threaten the safety of property or personnel on the ground. Even if all motors lose power, the present invention can still change the direction of the airflow passing through the duct by changing the inclination angle of the duct, thereby obtaining a reaction force to control the drone to avoid people or objects on the ground, and also protect the safety of the drone itself and the cargo. In normal cruising flight, the flight posture of the drone can also be controlled in this way.

[0023] 4. The duct fixing plate in the present invention is provided with a resistance reducing leakage hole, which is a pair of heart-shaped through holes mirror-imaged on both inner sides of the fixing plate. During the flight of the UAV, part of the airflow passes through the resistance reducing leakage hole. The resistance reducing leakage hole can reduce the resistance of the airflow during the flight of the UAV and reduce the weight of the fixing plate, saving materials and reducing the overall weight of the UAV. On the other hand, the heart-shaped resistance reducing leakage hole increases the overall beauty of the UAV and has a good visual effect.

[0024] 5. The tail wing of the drone of the present invention is mainly designed for stable flight during cruising. It is a structure that can be automatically folded and unfolded, which is easy to carry and saves space. At the same time, it retains the function of controlling the flight attitude as an elevator, and can be rotated up and down to adjust the elevation angle of the drone during cruising. The tail wing is made of carbon fiber material, which is light in weight and strong in strength. It is not easy to deform when subjected to impact or pressure, and the maintenance and replacement rate of the tail wing is reduced. In addition, in order to avoid the drone being monitored when used in a concealed manner, the tail wing can also be attached with a stealth coating, which has anti-radar and anti-infrared functions, and can achieve a stealth effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 This is a schematic diagram of the structure of Embodiment 1 of the present invention;

[0026] Figure 2 It is a structural schematic diagram of the UAV fuselage in the first embodiment;

[0027] Figure 3 for Figure 2 Enlarged view of species A;

[0028] Figure 4 for Figure 2 A schematic diagram of a structure in which the left fuselage and the right fuselage are stored in the middle fuselage;

[0029] Figure 5 It is a schematic diagram of the structure in which the left bottom plate and the right bottom plate are connected to the middle bottom plate in the first embodiment;

[0030] Figure 6 is a schematic diagram of the structure of the ducted rotor in Example 1;

[0031] Figure 7 is a schematic structural diagram of the tail wing body in the first embodiment;

[0032] Figure 8 It is a structural schematic diagram of the front end support rod in the first embodiment;

[0033] Fig. 9 It is a schematic diagram of the structure of the fuselage in the second embodiment.

[0034] In the figure: left fuselage 01, middle fuselage 02, right fuselage 03, bottom plate 1, left bottom plate 101, first slider 1011, middle bottom plate 102, slide rail 1021, right bottom plate 103, second slider 1031, left side plate 2, right side plate 3, top cover 4, front middle top cover 401, rear middle top cover 402, left top cover 403, right top cover 404, first pin 5, first connecting rod 6, first groove 7, first positioning Column 8, first compression spring 9, tilt control rod 10, ducted rotor 11, duct 12, first connecting piece 13, drag reduction leakage hole 14, second connecting piece 15, motor seat 16, support rod 17, front end support rod 1701, adjusting bolt 1702, rear end support rod 1703, mounting rod 18, tail rod 19, vertical stabilizer 20, horizontal stabilizer 21, clamping plate 22, tail servo pod 23, tail adjustment gear 24. DETAILED DESCRIPTION

[0035] The present invention will be further described in detail below in conjunction with the accompanying drawings. It is obvious that the described embodiments are the best embodiments of the present invention.

[0036] like Figure 1-8 As shown, a safe and stable transport drone includes a fuselage, a rotor mechanism and a tail mechanism. The fuselage includes a bottom plate 1, a left side plate 2 and a right side plate 3 on both sides of the bottom plate 1, and a top cover 4 connecting the top of the left side plate 2 and the right side plate 3. The top cover 4 is a streamlined structure design that arches upward, and the bottom plate 1 is a streamlined structure design that arches downward. The upward arching amplitude of the top cover 4 is greater than the downward arching amplitude of the bottom plate 1. The top cover 4 and the bottom plate 1 meet at the front and rear parts of the fuselage and enclose a Clark Y-shaped airfoil structure with a relative thickness of 21% (the ratio of the maximum thickness to the chord length is called the relative thickness). The cross-sectional shape of the fuselage is a double convex airfoil structure. The fuselage structural design has the advantages of low resistance and large lift coefficient. The lift provided can reduce the burden on the motor and reduce power consumption.

[0037] The bottom plate 1 includes a left bottom plate 101 , a middle bottom plate 102 and a right bottom plate 103 , and the top cover 4 includes a front middle top cover 401 , a rear middle top cover 402 , a left top cover 403 and a right top cover 404 .

[0038] like Figure 2As shown, the left bottom plate 101, the left side plate 2, and the left top cover 403 together constitute the left fuselage 01; the right bottom plate 103, the right side plate 3, and the right top cover 404 together constitute the right fuselage 03; the middle bottom plate 102, the front middle top cover 401, and the rear middle top cover 402 together constitute the middle fuselage 02. The left fuselage 01, the middle fuselage 02, and the right fuselage 03 are hollow structures with inner cabins. The left fuselage 01 and the right fuselage 03 have the same structure and are symmetrically arranged on the left and right sides of the middle fuselage 02. The left fuselage 01 and the right fuselage 03 are slidably connected to the middle fuselage 02.

[0039] like Figure 5 As shown, a slide rail 1021 is provided in the middle of the middle bottom plate 102, and a first slider 1011 is provided at a position corresponding to the slide rail 1021 at one end of the left bottom plate 101 close to the middle bottom plate 102, and slides left and right along the slide rail 1021; a second slider 1031 is provided at a position corresponding to the slide rail 1021 at one end of the right bottom plate 103 close to the middle bottom plate 102, and slides left and right along the slide rail 1021. The left fuselage 01 and the right fuselage 03 move horizontally relative to the middle fuselage 02 to extend / receive into the inner compartment of the middle fuselage 02. The width of the middle fuselage 03 is approximately equal to but slightly smaller than the sum of the widths of the left fuselage 01 and the right fuselage 02. The width of the middle fuselage 02 in the present invention is 2 cm smaller than the sum of the widths of the left fuselage 01 and the right fuselage 03, so that the left fuselage 01 and the right fuselage 03 can be stored in the middle fuselage 02 as much as possible but still remain partially exposed for easy extraction.

[0040] The front middle top cover 401 and the rear middle top cover 402 are connected to the middle bottom plate 102 by rotating up and down to open / close the inner compartment of the middle fuselage 02. When no cargo is transported, the left fuselage 01 and the right fuselage 03 are stored in the middle fuselage 02, making the drone compact and reducing the size of the drone for easy carrying. When cargo needs to be transported, the cargo is stored in the inner compartment of the middle fuselage 02, and the cargo does not increase the resistance of the drone during flight, which is economically efficient.

[0041] like Figure 3As shown, the front middle top cover 401 is rotatably connected with the front end of the middle bottom plate 102 through the first pin shaft 5; a pair of downward first connecting rods 6 are provided at the front end of the front middle top cover 401, and a first pin hole is provided on the first connecting rod 6. A first groove 7 for accommodating the pair of first connecting rods 6 is provided at a corresponding position on the middle bottom plate 102, and a first positioning column 8 is provided in the middle of the first groove 7. The first positioning column 8 is a "U"-shaped structure, and the pair of first connecting rods 6 are located in the "U"-shaped opening of the first positioning column 8. The first positioning column 8 is provided with a first through hole, and the first pin shaft 5 passes through the first pin hole and the first through hole to rotatably connect the front middle top cover 401 with the middle bottom plate 102; a first compression spring 9 is sleeved on the first pin shaft 5, one end of the first compression spring 9 is fixedly connected to the front middle top cover 401, and the other end of the first compression spring 9 is fixedly connected to the middle bottom plate 102, and the first compression spring 9 is sleeved on the first pin shaft 5 located between the pair of first connecting rods 6. So that the front middle top cover 401 is closed firmly.

[0042] The rear middle top cover 402 is rotatably connected with the rear end of the middle bottom plate 102 through a second pin shaft; a pair of downward second connecting rods are provided at the rear end of the rear middle top cover 402, a second pin hole is provided on the second connecting rod, a second groove for accommodating the pair of second connecting rods is provided at a corresponding position on the middle bottom plate 102, a second positioning column is provided in the middle of the second groove, the second positioning column is a "U"-shaped structure, a pair of second connecting rods are located in the "U"-shaped opening of the second positioning column, a second through hole is provided on the second positioning column, the second pin shaft passes through the second pin hole and rotatably connects the rear middle top cover with the middle bottom plate 102, a second compression spring is sleeved on the second pin shaft, one end of the second compression spring is fixedly connected with the rear middle top cover 402, the other end of the second compression spring is fixedly connected with the middle bottom plate 102, and the second compression spring is sleeved on the second pin shaft located between the pair of second connecting rods, so that the rear middle top cover 402 is firmly closed.

[0043] The rotor mechanism includes a rotor body, a drive unit for controlling the rotor tilting action, and a remote control receiver for controlling the drive unit. The drive unit includes a pair of servos symmetrically arranged on both sides of the fuselage, and a tilting control rod 10 connected to the servos; the pair of servos are a left servo and a right servo respectively arranged in the left fuselage 01 and the right fuselage 03. The electronic equipment required for controlling the flight is evenly distributed in the interior of the left fuselage 01 and the right fuselage 03 in terms of weight and center of gravity.

[0044] The tilt control lever 10 includes a left tilt control lever connected to the left servo and a right tilt control lever connected to the right servo. The left tilt control lever is fixedly connected to a left adjustment tooth at one end close to the left servo, and the left adjustment tooth is meshed with the servo gear of the left servo. The right tilt control lever is fixedly connected to a right adjustment tooth at one end close to the right servo, and the right adjustment tooth is meshed with the servo gear of the right servo. The left / right servo can drive the tilt control lever 10 to rotate through the corresponding left / right adjustment tooth, and adjust the swing direction of the rotor body through the tilt control lever 10, thereby adjusting the angle of the rotor body to adjust according to the requirements of different flight angles.

[0045] like Figure 1 As shown, the rotor body is a pair of ducted rotors 11 symmetrically arranged on both sides of the fuselage, and the ducted rotors 11 are connected to the tilt control rod 10.

[0046] like Figure 6 As shown, the ducted rotor 11 includes a pair of ducts 12 and a first connector 13 for connecting the pair of ducts. The pair of ducts 12 are symmetrically arranged at both ends of the first connector 13. The duct 12 is a hollow truncated cone structure formed by smoothly connecting the two ports through an inwardly protruding arc transition surface. During the flight of the UAV, the windward side of the duct 11 is an expanded structure, and the leeward side is a contracted structure. This structural design can comb the airflow, reduce the vortex interference between the rotors, and thus improve the aerodynamic efficiency of the rotors; it has a drainage effect on the wind, which in disguise increases the density of the airflow passing through the blades and increases the thrust. At the same time, the design of the duct 12 in the present invention solves the problem that the exposed propellers of existing UAVs get entangled with branches and wires or break due to collision with obstacles during flight, and fall from a height to injure people.

[0047] In addition, the duct 12 in the present invention can also control the posture of the fuselage in an emergency (such as loss of power in the air). When a motor of an ordinary quadcopter loses power, it will be completely out of control, fall to the ground, damage the drone, and may threaten the property or personnel safety on the ground. Even if all motors lose power, the present invention can still change the inclination angle of the ducted rotor 11 and the direction of the airflow passing through it, thereby obtaining a reaction force to control the drone to avoid people or objects on the ground, and also protect the safety of the drone itself and the cargo. In normal cruising flight, the flight posture of the drone can also be controlled in this way.

[0048] The inner wall of the duct 12 is provided with a noise reduction layer made of sound absorbing material, which plays a role in blocking sound waves to a certain extent and reducing noise pollution. The first connector 13 connecting the duct 12 is a fixed plate with a resistance reduction leakage hole 14. The resistance reduction leakage hole 14 is a pair of heart-shaped through holes mirror-imaged on both inner sides of the fixed plate. During the flight of the drone, part of the airflow passes through the resistance reduction leakage hole 14. The resistance reduction leakage hole 14 can reduce the resistance of the airflow during the flight of the drone, and at the same time can reduce the weight of the fixed plate, save materials, and reduce the overall weight of the drone. On the other hand, the heart-shaped resistance reduction leakage hole 14 increases the overall beauty of the drone and has a good visual effect. The second connector 15 for connecting the tilt control rod 10 is provided on both outer sides of the fixed plate. The second connector 15 is a sleeve that is compatible with the structure of the tilt control rod 10. The second connector 15 is sleeved with the tilt control rod 10 to facilitate daily disassembly, inspection and maintenance.

[0049] The duct 12, the first connecting member 13 and the second connecting member 15 in the present invention are an integrated structure, so that the overall structural strength of the ducted rotor 11 is high and the service life is long. At the same time, one tilt control rod 10 can control two ducts 12 on one side, reducing the structural complexity of the drone.

[0050] A support frame is provided inside the duct 12, and the support frame includes a motor seat 16 and four support rods 17 evenly distributed along the circumference of the motor seat 16. The center line of the motor seat 16 coincides with the center line of the duct 12. A motor is provided on the motor seat 16, and a blade (not shown in the figure) is connected to the motor. Two ends of the four support rods 17 are respectively connected to the motor seat 16 and the inner wall of the duct 12 to form a cross-shaped support frame. The cross-shaped support frame can improve the structural strength of the duct 12 and improve the overall wind resistance and stability of the duct 12, thereby contributing to safe and stable flight.

[0051] The inner wall of the duct 12 is evenly provided with positioning grooves in the circumferential direction. The length of the support rod 17 is adjustable. The support rod 17 includes a front support rod 1701, an adjusting bolt 1702, and a rear support rod 1703. The cross-sections of the front support rod 1701 and the rear support rod 1703 are long teardrop-shaped structures with the same structure, such as Figure 8 As shown in the structural schematic diagram of the front end support rod, the cross-section of the front end support rod 1701 is a long teardrop-shaped structure with a consistent structure. The long teardrop-shaped structure enables the support rod 17 to both support and fix the duct 12 and reduce the air resistance acting on the support rod 17.

[0052] The first end of the front support rod 1701 is inserted into the positioning groove, the second end of the front support rod 1701 is connected to the first end of the adjusting bolt 1702, the second end of the adjusting bolt 1702 is connected to the first end of the rear support rod 1703, and the second end of the rear support rod 1703 is connected to the motor seat 16.

[0053] The support rod 17 in the present invention is of adjustable length. By adjusting the length of the support rod 17, the duct 12 and the support frame can be quickly installed in place, or the support frame can be conveniently removed from the duct 12 for replacement, maintenance and cleaning. At the same time, the support rod 17 is designed as a length-adjustable structure so that the support frame can be suitable for ducts 12 with different apertures.

[0054] The tail mechanism comprises a mounting frame arranged at the lower rear part of the fuselage and a tail body connected to the mounting frame and capable of rotating around an X-axis relative to the mounting frame.

[0055] like Figure 7 As shown, the tail body includes a mounting rod 18, and tail rods 19 are fixed to the rear of both ends of the mounting rod 18. The two tail rods 19 are arranged in parallel, and a vertical stabilizer 20 is arranged on the lower surface of the rear end of each tail rod 19, and a horizontal stabilizer 21 is arranged between the two vertical stabilizers 20.

[0056] The mounting frame includes two clamping plates 22 arranged opposite to each other at the lower rear part of the fuselage. A slot for inserting the mounting rod 18 is arranged on the opposite inner sides of the clamping plates 22 . The mounting rod 18 is inserted into the slot and can rotate relative to the clamping plates 22 .

[0057] The lower surface of the card plate 22 is set horizontally, and the card plate 22 with a horizontal bottom can play the role of the landing gear of the drone, thereby improving the support of the fuselage and making the take-off and landing smooth. The horizontal cross-section of the card plate 22 is a long teardrop shape to reduce air resistance.

[0058] A tail servo pod 23 is arranged between the two clamping plates 22. The tail servo pod 23 is fixed at the lower center of the rear part of the fuselage. The lower surface of the tail servo pod 23 is set as an arc tangent to the lower surface of the middle fuselage 02, and the upper surface is set as an arc tangent to the upper surface of the middle fuselage 02, so as to minimize the air resistance brought by the tail servo pod 23 and bring some lift.

[0059] A tail adjusting tooth 24 is provided in the middle of the mounting rod 18 and in the tail servo pod 23. The tail adjusting tooth 24 is fixedly connected to the mounting rod 18 and meshes with the tail servo gear in the tail servo pod 23. The tail servo can drive the mounting rod 18 to rotate through the tail adjusting tooth 24, and adjust the swing direction of the tail rod 19 through the mounting rod 18, thereby adjusting the angle of the tail body to be adjusted according to the requirements of different flight angles.

[0060] Carbon fiber is a new type of fiber material with high strength and high modulus, with a carbon content of more than 95%. It is a microcrystalline graphite material obtained by stacking organic fibers such as flake graphite microcrystals along the axial direction of the fiber through carbonization and graphitization. Carbon fiber is "soft on the outside and hard on the inside", lighter than metal aluminum, but stronger than steel, and has the characteristics of corrosion resistance and high modulus. Therefore, in order to reduce the weight of the tail wing, the tail rod 19 is preferably a carbon fiber rod.

[0061] The tail body in the present invention is fixed to the rear part of the UAV fuselage through a mounting frame. On the one hand, the UAV can maintain balance when flying. On the other hand, the tail body can be rotated downward relative to the fuselage of the UAV to be folded. When the UAV needs to be stored and organized, the tail body is folded to the lower part of the middle fuselage 02 to save space. When the UAV needs to fly, the tail is unfolded while the UAV rises to the cruising altitude and the rotor is tilted. In addition, the mounting rod 18, tail rod 19, vertical stabilizer 20 and horizontal stabilizer 21 in the present invention are of an integrated design. The mounting rod 18 can be rotated relative to the mounting frame to make the tail body rotate synchronously, thereby facilitating the control of the inclination and folding of the tail body.

[0062] During use, when items need to be transported, the left fuselage 01 and the right fuselage 03 are pulled out of the middle fuselage 02, the inner cabin of the middle fuselage 02 is opened, the items are placed in the inner cabin, and then the inner cabin is closed, and the flight of the drone is controlled by the remote control.

[0063] When the drone takes off, the pair of ducted rotors 11 are horizontal relative to the ground, and the thrust direction is vertically downward, pushing the drone to rise vertically. At this time, the steering and movement of the drone can be controlled by the remote control receiver to control the corresponding servo action. The left / right servo drives the ducted rotor 11 to rotate through the corresponding tilt control lever, adjusts the inclination angle of the ducted rotor 11, and provides a horizontal component to push the fuselage to rotate. This steering method is more efficient than the traditional drone steering method of adjusting the motor speed, and can always keep the fuselage level, which is conducive to the transportation of goods.

[0064] When the drone rises to the cruising altitude, the drone will automatically unfold its tail wing, and the left / right servos will drive the corresponding ducted rotor 11 to rotate to a vertical state relative to the ground. At this time, the thrust direction is backward, and a higher speed can be achieved. The gravity of the fuselage is offset by the lift provided by the fuselage. When the drone turns, a pair of ducted rotors 11 can tilt relative to each other according to the turning angle and turning direction, and the left / right servos will drive the corresponding ducted rotors 11 to rotate to the appropriate angle to provide steering torque. At the same time, the thrust size can also be adjusted to achieve vector steering through the thrust difference, and the overall stability of the drone is good when flying.

[0065] Embodiment 2

[0066] The solution of the second embodiment is basically the same as that of the first embodiment, except that: Figure 8 As shown, the cross-sectional shape of the fuselage is a plano-convex wing structure, that is, the top cover 4 is convex in an arc, and the bottom plate 2 is a flat straight line except for the leading edge. This fuselage structural design is convenient for mass production.

[0067] Embodiment 3

[0068] The technical solution of Example 3 is basically the same as that of Example 1, except that the vertical stabilizer and the horizontal stabilizer both include a carbon fiber layer, and a radar transparent layer, a radar absorbing layer and a radar reflecting layer are arranged on the surface of the carbon fiber layer.

[0069] Preferably, the radar absorbing layer is a polyimide film layer.

[0070] The carbon fiber layer of the tail wing bottom layer can prevent the drone from deformation and damage when encountering strong winds and other bad weather during flight. On the other hand, its light weight can reduce the weight of the drone and make it easier to carry.

[0071] By setting up a radar transparent layer, a radar absorbing layer and a radar reflecting layer, the RCS of the drone is reduced, making the drone invisible to radar and able to perform reconnaissance or transportation operations without anyone noticing.

[0072] Embodiment 4

[0073] The technical solution of the fourth embodiment is basically the same as that of the first embodiment, except that the vertical stabilizer and the horizontal stabilizer both include a carbon fiber layer, and an infrared stealth coating is provided on the surface of the carbon fiber layer.

[0074] The bottom layer of the carbon fiber layer can, on the one hand, prevent the drone from being deformed or damaged when encountering severe weather such as strong winds during flight; on the other hand, its light weight can reduce the weight of the drone and make it easier to carry.

[0075] The design of the infrared stealth coating can make the drone invisible in the infrared, so it can carry out reconnaissance or transportation operations without anyone noticing.

[0076] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A safe and stable transport drone, comprising a fuselage, a rotor mechanism and a tail mechanism, characterized in that: The fuselage includes a bottom plate, a left side plate and a right side plate on both sides of the bottom plate, and a top cover connecting the tops of the left side plate and the right side plate, wherein the top cover is designed as a streamlined structure that arches upward, and the bottom plate is designed as a streamlined structure that arches downward, and the upward arching amplitude of the top cover is greater than the downward arching amplitude of the bottom plate; The bottom plate comprises a left bottom plate, a middle bottom plate and a right bottom plate, and the top cover comprises a front middle top cover, a rear middle top cover, a left top cover and a right top cover; the left bottom plate, the left side plate and the left top cover together constitute the left fuselage; the right bottom plate, the right side plate and the right top cover together constitute the right fuselage; the middle bottom plate, the front middle top cover and the rear middle top cover together constitute the middle fuselage; the left fuselage, the middle fuselage and the right fuselage are hollow structures with an inner cabin; the left fuselage and the right fuselage have the same structure and are symmetrically arranged on the left and right sides of the middle fuselage, and the left fuselage and the right fuselage are slidably connected to the middle fuselage, and the left fuselage and the right fuselage move horizontally relative to the middle fuselage to extend / receive into the inner cabin of the middle fuselage; at least one of the front middle top cover and the rear middle top cover can rotate up and down relative to the middle bottom plate to open / close the inner cabin of the middle fuselage; The rotor mechanism includes a rotor body, a drive unit for controlling the tilting action, and a remote control receiver for controlling the drive unit, the drive unit includes a pair of servos symmetrically arranged on the left fuselage and the right fuselage, and a tilt control rod connected to the servos; the rotor body is a pair of ducted rotors symmetrically arranged on both sides of the fuselage, and the ducted rotors are connected to the tilt control rods; the ducted rotor includes a pair of ducts and a first connecting member for connecting the pair of ducts, the pair of ducts are symmetrically arranged at both ends of the first connecting member, and the duct is a hollow frustum structure formed by smoothly connecting two ports through an inwardly protruding arc transition surface; a support frame is provided inside the duct; The tail mechanism comprises a mounting frame arranged at the lower rear part of the fuselage and a tail body connected to the mounting frame and rotatable relative to the mounting frame; The front middle top cover is rotatably connected to the front end of the middle bottom plate via a first pin shaft; the rear middle top cover is rotatably connected to the rear end of the middle bottom plate via a second pin shaft; The support frame includes a motor seat and a plurality of support rods evenly distributed along the circumference of the motor seat, the center line of the motor seat coincides with the center line of the duct, a motor is provided on the motor seat, a blade is connected to the motor, two ends of the support rod are respectively connected to the motor seat and the inner wall of the duct, the inner wall of the duct is evenly provided with positioning grooves along the circumference, and the length of the support rod is adjustable; the support rods include a front support rod, an adjusting bolt, and a rear support rod, the first end of the front support rod is inserted into the positioning groove, the second end of the front support rod is connected to the first end of the adjusting bolt, the second end of the adjusting bolt is connected to the first end of the rear support rod, and the second end of the rear support rod is connected to the motor seat; The tail body includes a mounting rod, which is fixed on the mounting frame and can rotate relative to the mounting frame. Tail rods are fixed to the rear parts of both ends of the mounting rod. The two tail rods are arranged in parallel. A vertical stabilizer is arranged on the lower surface of the rear end of each tail rod, and a horizontal stabilizer is arranged between the two vertical stabilizers.

2. The safe and stable transport drone according to claim 1, characterized in that: The width of the middle fuselage is smaller than the sum of the widths of the left fuselage and the right fuselage. A slide rail is provided in the middle of the middle bottom plate. A first sliding block is provided on the left bottom plate at a position corresponding to the slide rail and close to the middle bottom plate for sliding left and right along the slide rail. A second sliding block is provided on the right bottom plate at a position corresponding to the slide rail and close to the middle bottom plate for sliding left and right along the slide rail.

3. The safe and stable transport drone according to claim 2, characterized in that: A pair of downward first connecting rods are provided at the front end of the front middle top cover, a first pin hole is provided on the first connecting rod, a first groove for accommodating the pair of first connecting rods is provided at a corresponding position on the middle bottom plate, a first positioning column is provided in the middle of the first groove, the first positioning column is a "U"-shaped structure, the pair of first connecting rods are located in the "U"-shaped opening of the first positioning column, a first through hole is provided on the first positioning column, the first pin shaft passes through the first pin hole and the first through hole to rotatably connect the front middle top cover and the middle bottom plate; a first compression spring is sleeved on the first pin shaft, one end of the first compression spring is fixedly connected to the front middle top cover, and the other end of the first compression spring is fixedly connected to the middle bottom plate, and the first compression spring is sleeved on the first pin shaft located between the pair of first connecting rods; A pair of downward second connecting rods are provided at the rear end of the rear middle top cover, and a second pin hole is provided on the second connecting rod. A second groove for accommodating the pair of second connecting rods is provided at a corresponding position on the middle bottom plate, and a second positioning column is provided in the middle of the second groove. The second positioning column is a "U"-shaped structure, and the pair of second connecting rods are located in the "U"-shaped opening of the second positioning column. A second through hole is provided on the second positioning column, and the second pin shaft passes through the second pin hole and the second passage to rotatably connect the rear middle top cover and the middle bottom plate, and a second compression spring is sleeved on the second pin shaft, one end of the second compression spring is fixedly connected to the rear middle top cover, and the other end of the second compression spring is fixedly connected to the middle bottom plate, and the second compression spring is sleeved on the second pin shaft located between the pair of second connecting rods.

4. The safe and stable transport drone according to claim 3, characterized in that: The inner wall of the duct is provided with a noise reduction layer made of sound-absorbing material, and the first connecting member connecting the duct is a fixed plate with a resistance-reducing leakage hole, and at least one outer side of the fixed plate is provided with a second connecting member for connecting the tilt control rod; the second connecting member is a sleeve adapted to the tilt control rod structure, and the second connecting member is sleeved with the tilt control rod; the windward surfaces of the front support rod and the rear support rod are both arc-shaped structures, and the cross-sections of the front support rod and the rear support rod are both long teardrop-shaped structures.

5. The safe and stable transport drone according to claim 4, characterized in that: The mounting frame includes two clamping plates relatively arranged on the outer side of the lower tail of the UAV fuselage, and slots for inserting the mounting rod are arranged on the relatively inner sides of the clamping plates; a tail servo pod is arranged between the two clamping plates, and the tail servo pod is fixed at the center of the lower rear part of the fuselage, and an adjusting tooth is penetrated in the middle of the mounting rod and located in the tail servo pod, and the adjusting tooth is fixedly connected to the mounting rod and meshes with the gear of the tail servo in the tail servo pod.

6. The safe and stable transport drone according to claim 5, characterized in that: The tail rod is a carbon fiber rod; the vertical stabilizer and the horizontal stabilizer both include a carbon fiber layer, and a radar transparent layer, a radar absorbing layer and a radar reflecting layer are arranged on the surface of the carbon fiber layer, and the radar absorbing layer is a polyimide film layer.

7. The safe and stable transport drone according to claim 5, characterized in that: The vertical stabilizer and the horizontal stabilizer both include carbon fiber layers, and infrared stealth coatings are arranged on the surfaces of the carbon fiber layers.

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