Scissor-wing drone

Abstract

The present invention discloses a scissor-wing UAV, which belongs to the field of aircraft design technology. The UAV mainly includes a fuselage main body and a left front wing, a left rear wing, a right front wing and a right rear wing. Tiltable ducted fans are respectively arranged on the wings. The left front wing and the left rear wing as well as the right front wing and the right rear wing can be closed or unfolded. The UAV adopts only one set of power system and can have the operational advantages of both fixed-wing and rotary-wing UAVs. The UAV utilizes a wing structure that can be separated like a "scissors" and cooperates with a tiltable power system. The UAV can take off and land vertically by unfolding the wings during take-off and landing phases and fly at high speed by closing the wings during navigation phase. By switching between fixed wings and rotary wings and using corresponding wing forms in specific phases, the UAV's nuclear carrying capacity, endurance and flexibility are comprehensively improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a scissor-wing UAV. Background Art

[0002] With the gradual opening of low-altitude airspace and the continuous innovation of technology, the low-altitude economy has developed rapidly in recent years and the market scale has continued to expand. Under this development trend, the drone industry, as the leading industry of the low-altitude economy, has become particularly prominent.

[0003] At present, the application scope of drones in various fields continues to expand, and they have been widely used in logistics and transportation, disaster relief, street scene photography, environmental protection testing, power inspection, traffic monitoring, and agricultural plant protection. For example, in the field of logistics and transportation, they are involved in many scenarios such as urban terminal distribution, remote area transportation, and special material transportation. E-commerce and logistics giants are actively deploying, and instant retail companies are also deeply involved. The development of technologies such as flight control, remote sensing communication, and automatic driving and obstacle avoidance has strongly promoted their application. The market size has grown rapidly, policy support has continued to increase, and infrastructure such as take-off and landing points and route planning, and integrated management platform construction has been gradually improved. The overall situation is booming and has huge potential.

[0004] Existing drones typically come in fixed-wing or rotary-wing configurations. Fixed-wing drones are unable to take off and land vertically, requiring a runway of a certain length for takeoff and landing. This places high demands on the landing and takeoff areas, limiting their use in areas with complex terrain or limited space. Furthermore, they are unable to hover and have poor flexibility, making takeoff and landing operations difficult. Rotary-wing drones, on the other hand, have relatively slow flight speeds and limited endurance, resulting in lower efficiency over long distances, potentially impacting timeliness. Summary of the Invention

[0005] In view of the above shortcomings, the present invention provides a scissor-wing UAV to solve the problem that existing UAVs are difficult to have the characteristics of large payload, long endurance and high flexibility.

[0006] In order to achieve the above object, the present invention adopts the following technical solutions:

[0007] A scissor-wing drone, comprising:

[0008] fuselage body;

[0009] a left front wing, a left rear wing, a right front wing, and a right rear wing, wherein the left front wing and the left rear wing are located on the left side of the fuselage main body, and the right front wing and the right rear wing are located on the right side of the fuselage main body, and one end of the left front wing, the left rear wing, the right front wing, and the right rear wing are respectively rotatably connected to the fuselage main body;

[0010] a wing opening and closing drive mechanism, disposed on the fuselage body, for driving the left front wing and the left rear wing to rotate so as to fit together front and back to form a left fixed wing, and for driving the right front wing and the right rear wing to rotate so as to fit together front and back to form a right fixed wing; or for driving the left front wing and the left rear wing to rotate so as to spread out front and back to each other, and for driving the right front wing and the right rear wing to rotate so as to spread out front and back to each other;

[0011] Ducted fans are respectively arranged on the left front wing, the left rear wing, the right front wing and the right rear wing;

[0012] A fan steering drive mechanism is provided on the left front wing, the left rear wing, the right front wing and the right rear wing to drive the ducted fan to switch between a front-to-back facing state and a vertical state.

[0013] Furthermore, the ducted fan is respectively mounted on the left front wing, the left rear wing, the right front wing or the right rear wing through a fan bracket, and the ducted fan is rotatably connected to the fan bracket;

[0014] The fan steering drive mechanism is a first electric push rod, one end of which is rotationally connected to the left front wing, left rear wing, right front wing or right rear wing, and the other end is rotationally connected to the ducted fan.

[0015] Furthermore, the fan bracket extends obliquely downward from the bottom surface of the left front wing, left rear wing, right front wing or right rear wing, the ducted fan is installed at the end of the fan bracket and when the ducted fan is converted to a vertical state, the left front wing, left rear wing, right front wing or right rear wing does not block the ducted fan in the vertical direction.

[0016] Furthermore, a receiving groove is provided on the rear side surfaces of the left front wing and the right front wing. When the left front wing and the left rear wing are fitted front and back, the front side surface of the left rear wing is fitted into the receiving groove of the left front wing; and when the right front wing and the right rear wing are fitted front and back, the front side surface of the right rear wing is fitted into the receiving groove of the right front wing.

[0017] Furthermore, the bottom of the accommodating groove is arc-shaped, and the front side surfaces of the left rear wing and the right rear wing are corresponding arc surfaces.

[0018] Furthermore, the wing opening and closing drive mechanism includes a wing opening and closing unit, and there are two wing opening and closing units, which are relatively arranged on the left and right sides of the top of the fuselage main body and correspond to the left front wing and left rear wing on the left side and the right front wing and right rear wing on the right side respectively. The wing opening and closing unit includes a second electric push rod, a wing connecting joint and a wing rotating top rod, the second electric push rod is fixedly installed on the fuselage main body and extends correspondingly toward the side, the end of the telescopic rod of the second electric push rod is connected to the end of the wing connecting joint, and there are two wing rotating top rods, one end of the two wing rotating top rods is respectively and one-to-one connected to the two ends of the wing connecting joint, and the other end is respectively and one-to-one connected to the left front wing, left rear wing, right front wing or right rear wing on the same side.

[0019] Furthermore, the two ends of the wing connecting joint are chamfered at the parts away from the second electric push rod, and are at right angles at the parts close to the second electric push rod, so that when the telescopic rod of the second electric push rod is retracted, the wing rotating push rods at both ends of the wing connecting joint rotate close to each other, thereby driving the left front wing and the left rear wing on the same side to rotate and fit together front and back to form the left fixed wing, and driving the right front wing and the right rear wing to rotate and fit together front and back to form the right fixed wing, and when the telescopic rod of the second electric push rod is extended, the wing rotating push rods at both ends of the wing connecting joint rotate and unfold, thereby driving the left front wing and the left rear wing on the same side to rotate and unfold forward and backward, and driving the right front wing and the right rear wing to rotate and unfold forward and backward, and when the wing rotating push rods at both ends of the wing connecting joint rotate and unfold to a certain angle, the end surface of the wing rotating push rod abuts against the end surface of the wing connecting joint, so that the wing rotating push rods can no longer continue to unfold.

[0020] Furthermore, a storage compartment is provided at the bottom of the fuselage body, the bottom of the storage compartment downwardly penetrates the bottom surface of the fuselage body to form a storage compartment exit, and doors are rotatably provided on both sides of the storage compartment exit, and when the doors on both sides are rotated and closed, the storage compartment exit can be sealed;

[0021] A third electric push rod is also provided on both sides of the bottom of the fuselage body, and a door push rod is provided at the bottom of the doors on both sides. One end of the door push rod is rotatably connected to the door located on the same side, and the other end is rotatably connected to the telescopic rod of the third electric push rod located on the same side.

[0022] Furthermore, push-pull electromagnets are respectively provided at the front and rear ends of the storage compartment, and a door lock is provided at the end of the telescopic rod of the push-pull electromagnet. C-shaped locking rings are respectively provided on the doors on both sides, and when the doors on both sides are rotated closed and the storage compartment exit is sealed, the C-shaped locking rings of the doors on both sides can form a ring structure for inserting the door lock.

[0023] Furthermore, protrusions are respectively provided on the front and rear sides of the storage compartment, so that when the door lock is inserted into the annular structure formed by the C-shaped locking ring, the bottom of the door lock abuts against the top of the protrusion.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] The present invention provides a scissor-wing UAV, which adopts only one power system and can have the operational advantages of both fixed-wing and rotary-wing UAVs. It utilizes a wing structure that can be separated like a "scissors" and cooperates with a tiltable power system. The wings are unfolded during takeoff and landing to achieve vertical takeoff and landing, and the wings are closed during navigation to fly at high speed. By switching between fixed wings and rotary wings and using corresponding wing forms in specific stages, the nuclear load capacity, endurance and flexibility are comprehensively improved. In particular, the improvement is obvious in the field of logistics and transportation, which can significantly improve logistics and transportation efficiency and transportation range, reduce transit and delays, and bring more efficient and extensive solutions to logistics distribution.

[0026] The scissor-wing drone of the present invention innovatively combines the characteristics of fixed-wing and rotary-wing drones. It uses rotary-wing mode for vertical takeoff and landing and hovering during takeoff and landing, accurately adapting to complex terrain and confined spaces. It switches to fixed-wing mode during the cruising phase, using high speed and long endurance to expand the flight range, improve flight efficiency, significantly reduce transit delays, and comprehensively enhance the adaptability and flexibility of drone applications.

[0027] The wings of the present invention adopt a structural design that can be expanded or merged like "scissors". At the same time, when each wing is expanded to the maximum angle, the design is physically limited to a "dead point" position, which can greatly enhance the stability in the rotor mode.

[0028] After the wings of the present invention are separated, the cross-sectional configuration of the front and rear wings can still retain some upper and lower pressure differences, which is used to provide lift for the drone, making the drone more stable and reliable when switching from fixed-wing mode to rotor mode during the landing phase.

[0029] The present invention uses a tiltable power system structure to provide lift for the rotor mode in a vertical state and thrust for the fixed-wing mode in a horizontal state, thereby realizing the vertical take-off and landing function of the UAV and ensuring high speed performance with low power consumption.

[0030] The present invention can ensure that the air inlet of the ducted fan will not be blocked by the wing when the ducted fan is tilted to a vertical state, thereby causing power failure by installing the ducted fan on a wing bracket extending obliquely downward at the end.

[0031] The present invention has an idea and concept of "trapezoidal" distribution of ducted fans in rotor mode. After switching to fixed-wing mode, the relative position distance between the front and rear power units on the same side of the wing is minimized, making the overall design of the UAV more compact and reasonable.

[0032] The present invention utilizes an electric push rod to realize the structure of the cabin door opening and closing, which can effectively prevent the cabin door from shaking and getting stuck when opening and closing. Its smooth movement characteristics are conducive to extending the service life of the cabin door and connecting components, and reducing the vibration impact on internal sensitive equipment.

[0033] The present invention utilizes a push-pull electromagnet to lock the hatch structure, which has a quick response, efficient locking, and the ability to flexibly adjust the locking force. It has a simple and compact structure and strong operational reliability. It can effectively prevent materials from accidentally falling and is extremely convenient in terms of automated control. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for describing the embodiments.

[0035] Figure 1 This is a schematic diagram of the structure of the scissor-wing UAV of the present invention in fixed-wing mode;

[0036] Figure 2 This is a schematic diagram of the structure of the scissor-wing UAV of the present invention in rotor mode;

[0037] Figure 3 It is a structural schematic diagram of the fuselage main body in the present invention;

[0038] Figure 4 It is a schematic structural diagram of the frame of the fuselage main body and its upper parts in the present invention;

[0039] Figure 5 It is a schematic structural diagram of the frame of the fuselage main body and its upper parts in the present invention;

[0040] Figure 6 Schematic diagram of the structure of the fuselage bottom plate and its upper parts in the present invention (with the door closed);

[0041] Figure 7 for Figure 6 A magnified schematic diagram of point A in the middle;

[0042] Figure 8 Schematic diagram of the structure of the fuselage bottom plate and its upper parts in the present invention (with the door open);

[0043] Figure 9 It is a schematic diagram of the structure of the fuselage main body skeleton and each wing when unfolded in the present invention;

[0044] Figure 10 This is a schematic diagram of the structure of the fuselage main body skeleton and each wing (excluding the outer shell) when unfolded in the present invention;

[0045] Figure 11 Schematic diagram of the structure of the ducted fan when it is installed on the fan bracket in the present invention (the ducted fan is in a vertical state);

[0046] Figure 12 Schematic diagram of the positions of the two ducted fans when the two wings are combined in the present invention (the ducted fans are in a horizontal state).

[0047] The markings shown in the figure are: 10-fuselage body; 11-left front wing; 12-left rear wing; 13-right front wing; 14-right rear wing; 15-storage tank; 16-storage compartment; 17-storage compartment exit; 18-door; 19-power compartment; 111-fuselage; 112-nose; 113-tail; 117-top cover; 118-partition; 119-nose; 120-flight control panel; 121-vertical stabilizer; 122-rudder; 123-horizontal stabilizer; 124-elevator; 125-wing support frame; 126-vertical Partition; 127-wing bone; 129-aileron; 130-top panel; 20-ducted fan; 21-fan bracket; 22-fan steering drive mechanism; 23-ducted rotation joint; 24-push rod rotation joint; 25-fixed support rod; 31-second electric push rod; 32-wing connection joint; 33-wing rotation push rod; 41-third electric push rod; 42-cabin door push rod; 43-push-pull electromagnet; 44-cabin door lock; 45-C-type locking ring; 46-protrusion; 47-fuselage bottom plate; 48-landing gear; 50-panoramic camera. DETAILED DESCRIPTION

[0048] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts shall fall within the scope of protection of the present invention.

[0049] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they cannot be understood as limiting the present invention.

[0050] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be internal communication between two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances. In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0051] The purpose of the present invention is to provide a drone that uses only one power system and has the operational advantages of both fixed-wing and rotary-wing drones, achieving a large payload, strong endurance, and high flexibility. It mainly utilizes a wing structure that can be separated like a "scissors" and cooperates with a tiltable power system. The wings are unfolded during takeoff and landing to take off and land vertically, and the wings are closed during navigation to fly at high speed. The scissor-wing drone switches between fixed wings and rotary wings and uses corresponding wing forms in specific stages to comprehensively improve the payload capacity, endurance, and flexibility. Especially in the field of logistics and transportation, the improvement is obvious, which can significantly improve the efficiency and range of logistics and transportation, reduce transit and delays, and bring more efficient and extensive solutions to logistics distribution.

[0052] Please refer to Figures 1 to 12 A preferred embodiment of the present invention provides a scissor-wing UAV, which mainly includes a body 10, wings, and a ducted fan 20.

[0053] Please continue to refer to Figures 1 to 12In an exemplary embodiment, a storage compartment 16 is provided at the bottom of the fuselage body 10, and a power supply compartment 19 is provided at the top. The fuselage body 10 includes a fuselage 111, a nose 112 located at the head of the fuselage, and a tail 113 located at the tail of the fuselage. The nose 112 is wrapped with a nose skin, the fuselage 111 is wrapped with a fuselage skin, and the tail 113 is wrapped with a tail skin. The fuselage skin, the nose skin, and the tail skin all adopt a streamlined design. At the same time, an organic top cover 117 is provided above the fuselage 111. The organic top cover 117 is used to cover the joints where the wings rotate to open and close, so as to reduce air resistance. A nose 119 is fixedly installed at the front of the nose 112. The nose 119 is used to guide airflow, reduce air resistance, and withstand some flight stress. The frames of the fuselage 111, nose 112, and tail 113 all adopt a truss-type fuselage frame design, which can effectively withstand axial loads, improve torsional rigidity to enhance structural strength and stability, and is both weight-efficient, can reduce weight, extend fatigue life, and facilitate manufacturing and maintenance. The frames of the three are fixedly connected. The fuselage main body 10 is fixedly provided with a partition 118 at a position corresponding to the middle of the fuselage 111 to form a storage compartment 16 at the bottom and a power compartment 19 at the top. The power compartment has multiple battery slots for storing batteries or other energy supply devices. It plays a role in safely protecting the power supply, optimizing the placement of the power supply to balance the overall center of gravity of the drone, shielding the electromagnetic interference generated by the power supply, and providing a suitable working environment for the power supply (such as heat dissipation and moisture resistance). During drone operation, the load at the pivot point connecting the wing to the fuselage is transferred to the fuselage frame and distributed throughout. Simultaneously, the skin, supported by the stringers, can better resist deformation caused by torsional forces during flight. The drone's overall center of gravity is controlled at the center of the fuselage frame, enhancing flight stability, optimizing maneuverability, improving powertrain efficiency, and rationalizing structural stresses. This ensures the integration of various mechanisms within the fuselage frame while ensuring strength. A flight control board 120 is also mounted on bulkhead 118. This board uses sensors to sense attitude and control motors to adjust attitude to maintain balance and stabilize flight throughout. It collaborates with the positioning module for navigation, positioning, and correction, managing various flight modes, and allocating motor power to ensure powertrain operation based on flight status and requirements. A vertical stabilizer 121 is mounted at the end of the tail 113. A rudder 122 is mounted behind this stabilizer 121 to control the drone's vertical and vertical axis yaw. Left and right deflection alters the aerodynamic forces on the vertical tail, allowing the drone to steer left or right. A horizontal stabilizer 123 is provided at the end of the tail 113, and an elevator 124 is installed at the rear position of the horizontal stabilizer 123. By controlling the up and down deflection to change the aerodynamics of the tail, the pitch motion of the UAV around the horizontal axis is controlled to achieve ascent, descent or maintain a stable altitude, and is used to reduce air resistance.

[0054] The wings primarily include a left front wing 11, a left rear wing 12, a right front wing 13, and a right rear wing 14. The left front wing 11 and the left rear wing 12 are located on the left side of the fuselage 10, while the right front wing 13 and the right rear wing 14 are located on the right side of the fuselage 10. One end of the left front wing 11, the left rear wing 12, the right front wing 13, and the right rear wing 14 are each rotatably connected to the fuselage 10. In the exemplary embodiment, four rotating shafts are mounted on the top of the fuselage 111, and the four rotating shafts are arranged in a square shape. The left front wing 11, left rear wing 12, right front wing 13, and right rear wing 14 are each equipped with a wing support frame 125, each of which is encased in a wing shell. One end of each wing support frame 125 of the left front wing 11, left rear wing 12, right front wing 13, and right rear wing 14 is connected to four rotating shafts, one for each of the four shafts, enabling the left front wing 11, left rear wing 12, right front wing 13, and right rear wing 14 to rotate about the axes of the four rotating shafts. A vertical partition 126 is fixedly mounted in the middle of the top of the fuselage, separating the four rotating shafts into two pairs on the left and right sides. A top plate 130 is mounted on top of each of the four rotating shafts to reduce the bending moment experienced by each shaft and improve structural strength. In this exemplary embodiment, the width of the left front wing 11 and right front wing 13 is smaller than that of the left rear wing 12 and right rear wing 14.

[0055] The wing opening and closing drive mechanism is provided on the fuselage body 10 to drive the left front wing 11 and the left rear wing 12 to rotate so as to fit together front and back to form a left fixed wing, and to drive the right front wing 13 and the right rear wing 14 to rotate so as to fit together front and back to form a fixed wing. Figure 1 or driving the left front wing 11 and the left rear wing 12 to rotate to unfold forward and backward relative to each other, and driving the right front wing 13 and the right rear wing 14 to rotate to unfold forward and backward relative to each other, at this time, the left front wing 11, the left rear wing 12, the right front wing 13 and the right rear wing 14 form an X-shaped structure and are converted into a rotor form, such as Figure 2 The left front wing 11 and left rear wing 12, as well as the right front wing 13 and right rear wing 14, can open and close like a pair of scissors, hence the name of the scissor-wing drone of the present invention. When deployed, the drone forms an X-shape, and when closed, it forms a straight line. The left front wing 11 and left rear wing 12, as well as the right front wing 13 and right rear wing 14 on the left and right sides are symmetrically arranged with the midline as the axis. Whether deployed or closed, they are in a bilaterally symmetrical state.

[0056] The wing opening and closing drive mechanism includes two wing opening and closing units, which are arranged on the left and right sides of the fuselage top of the fuselage body 10, corresponding to the left front wing 11 and left rear wing 12 on the left side, and the right front wing 13 and right rear wing 14 on the right side. Each wing opening and closing unit includes a second electric push rod 31, a wing connection joint 32, and a wing rotation push rod 33. The second electric push rod 31 is fixedly mounted on the fuselage body 10 and extends toward the side. The end of the telescopic rod of the second electric push rod 31 is connected to the end of the wing connection joint 32. There are two wing rotation push rods 33, one end of each wing rotation push rod 33 is rotatably connected to the two ends of the wing connection joint 32, and the other end is rotatably connected to the left front wing 11, left rear wing 12, right front wing 13, or right rear wing 14 on the same side.

[0057] The two ends of the wing joint 32 are rounded at the part away from the second electric push rod 31, and are right angles at the part close to the second electric push rod 31. When the telescopic rod of the second electric push rod 31 is retracted, the wing rotating top rods 33 at both ends of the wing joint 32 rotate close to each other, thereby driving the left front wing 11 and the left rear wing 12 on the same side to rotate to fit each other front and back to form the left fixed wing, and driving the right front wing 13 and the right rear wing 14 to rotate to fit each other front and back to form the right fixed wing. When the telescopic rod of the second electric push rod 31 is extended, the wing rotating top rods 33 at both ends of the wing joint 32 rotate close to each other. When the wing rotating top rods 33 at both ends of the wing connecting joint 32 rotate to each other and expand, the wing rotating top rods 33 can drive the left front wing 11 and the left rear wing 12 on the same side to rotate to expand forward and backward, and drive the right front wing 13 and the right rear wing 14 to rotate to expand forward and backward. When the wing rotating top rods 33 at both ends of the wing connecting joint 32 rotate to each other and expand to a certain angle, the end surface of the wing rotating top rod 33 abuts against the end surface of the wing connecting joint 32, making it impossible for the wing rotating top rod 33 to continue to expand, that is, the mechanism is in a "dead point" position.

[0058] In an exemplary embodiment, the wing opening and closing drive mechanism comprises two wing opening and closing units, each of which comprises a second electric push rod 31. This means that the wing opening and closing drive mechanism has two power sources. The two second electric push rods 31 are mounted at the top of the fuselage frame, respectively, adjacent to either side of a vertical partition 126 in the middle, and secured by bolts. The second electric push rods 31 are electro-hydraulic push rods. When the telescopic rod of the electro-hydraulic push rod is extended, the middle vertical partition 126 offsets the reaction force of the left and right push rods, reducing the tangential load on the bolts securing the push rods and improving the safety of wing deployment. The corresponding rotating shafts of the four wing support brackets 125 are arranged in a rectangular pattern, with sufficient clearance between the front and rear mounting positions to ensure smooth telescopic movement of the electro-hydraulic push rods. A pressure self-locking mechanism is designed into the hydraulic manifold block of the electro-hydraulic push rods. When the motor stops rotating, this mechanism locks the telescopic rods in place, achieving self-locking of the push rods. When the wing rotating push rods 33 at both ends of the wing connecting joint 32 rotate to each other and unfold to a certain angle, the end surface of the wing rotating push rod 33 abuts against the end surface of the wing connecting joint 32, making it impossible for the wing rotating push rod 33 to continue to unfold. The UAV is in rotor mode, the pushing range of the second electric push rod 31 reaches the maximum value, the axes of the wing rotating push rod 33 on the same side coincide, the pressure angle on the follower is 90 degrees, and the mechanism is in a "dead point" position, which greatly improves the stability of the wing when unfolding.

[0059] During implementation, such as in the take-off or landing stage, the second electric push rod 31 is energized, and its motor rotates forward to extend the push rod, and the wing rotating push rod 33 is tilted outward through the wing connecting joints 32 on both sides. Under the action of the push rod, the wings on both sides (the left front wing 11 and the left rear wing 12, as well as the right front wing 13 and the right rear wing 14) will be spread out like "scissors", and eventually reach the "dead point" position of the mechanism, so that the wings are opened. At this time, the UAV is in rotor mode; and in the cruising stage, the second electric push rod 31 is energized, and its motor is reversed to retract the push rod, and the wing rotating push rod 33 is tilted inward through the wing connecting joints 32 on both sides. Under the action of the push rod, the wings on both sides (the left front wing 11 and the left rear wing 12, as well as the right front wing 13 and the right rear wing 14) are merged. At this time, the UAV is in fixed-wing mode.

[0060] The wing support frame 125 is reinforced with a plurality of wing ribs 127, which are distributed along the overall extension direction of the wing support frame 125. The wing ribs 127 achieve lightweight design while ensuring adequate strength. A receiving groove 15 is provided on the rear side surfaces of the left front wing 11 and the right front wing 13. When the left front wing 11 and the left rear wing 12 are aligned front and back, the front side of the left rear wing 12 fits within the receiving groove 15 of the left front wing 11. When the right front wing 13 and the right rear wing 14 are aligned front and back, the front side of the right rear wing 14 fits within the receiving groove 15 of the right front wing 13. In a preferred embodiment, the bottom of the receiving groove 15 is curved, and the front sides of the left rear wing 12 and the right rear wing 14 are corresponding curved surfaces. More specifically, in this exemplary embodiment, the accommodating groove 15 is concave in the wing shells of the left front wing 11 and the right front wing 13, and has a corresponding curved surface on the front side of the wing shells of the left rear wing 12 and the right rear wing 14. When the left front wing 11 and the left rear wing 12 are combined into fixed-wing mode, the contact surfaces of the wing shells of the left front wing 11 and the left rear wing 12 are completely aligned, with almost no gap between them, ensuring that the wings can provide sufficient lift in this fixed-wing mode. Similarly, when the right front wing 13 and the right rear wing 14 are combined into fixed-wing mode, the contact surfaces of the wing shells of the right front wing 13 and the right rear wing 14 are completely aligned, with almost no gap between them, ensuring that the wings can provide sufficient lift in this fixed-wing mode. In terms of cross-sectional structure, the cross-section of the wing shells of the left rear wing 12 and the right rear wing 14 still conforms to the principle of high flow velocity on the upper surface and low flow velocity on the lower surface, which can generate a pressure differential. Therefore, when switching from fixed-wing mode to rotary mode, the rear wing can still provide lift, improving stability during the switching process. Ailerons 129 are also installed on the left rear wing 12 and the right rear wing 14. In fixed-wing mode, the lift difference on both sides of the wings is changed by differential deflection of the trailing edge ailerons of the left rear wing 12 and the right rear wing 14, thereby controlling the rolling motion of the drone around the longitudinal axis, realizing the tilt of the drone, and assisting in completing turns and other actions.

[0061] Ducted fans 20 are respectively provided on the left front wing 11, the left rear wing 12, the right front wing 13 and the right rear wing 14. In this exemplary embodiment, a ducted fan 20 is respectively provided on the left front wing 11, the left rear wing 12, the right front wing 13 and the right rear wing 14. The ducted fan 20 is respectively installed on the left front wing 11, the left rear wing 12, the right front wing 13 or the right rear wing 14 through a fan bracket 21, and the ducted fan 20 is rotatably connected to the fan bracket 21. In this exemplary embodiment, each ducted fan 20 is connected to the corresponding wing on the left and right sides respectively through a fan bracket 21. The fan bracket 21 is provided with a ducted rotating joint 23 at one end connected to the ducted fan 20, and the rotation connection with the ducted fan 20 is achieved through the ducted rotating joint 23, that is, the ducted fan 20 can be rotated around the ducted rotating joints 23 on both sides, and the other end is fixedly connected to the wing support frame 125 of the left front wing 11, the left rear wing 12, the right front wing 13 and the right rear wing 14.

[0062] The fan steering drive mechanism 22 is provided on the left front wing 11, the left rear wing 12, the right front wing 13, and the right rear wing 14 to drive the ducted fan 20 to switch between the front-to-back state and the vertical state. In this exemplary embodiment, the fan steering drive mechanism 22 is a first electric push rod, one end of which is rotatably connected to the left front wing 11, the left rear wing 12, the right front wing 13, or the right rear wing 14, and the other end is rotatably connected to the ducted fan 20. The fan steering drive mechanism 22, which is the first electric push rod, is located below the fan bracket 21. Its telescopic rod is connected to the ducted fan 20 via a push rod rotation joint 24. The tilt angle of the ducted fan 20 is changed by extending and shortening the telescopic rod of the fan steering drive mechanism 22, thereby achieving the conversion of the ducted fan 20 between the front-to-back state and the vertical state. It is understood that the tilt angle of the ducted fan 20 can be between the front-to-back state and the vertical state. The ducted fans 20 are distributed in a staggered and symmetrical manner as a whole. In the rotor mode, they are in a vertical state with vertical thrust. In the fixed-wing mode, they are in a front-to-back state with horizontal thrust, which is used to provide power for the drone during flight.

[0063] Five connecting rods 25 are installed between the fan brackets 21 of the left front wing 11 and the right front wing 13, respectively, while four connecting rods 25 are installed between the fan brackets 21 of the left rear wing 12 and the right rear wing 14, respectively, to reinforce the fan brackets 21 and ensure the lateral stability of the ducted fan 20 during the tilting process. The fan brackets 21 of the left front wing 11 and the fan brackets 21 of the left rear wing 12 are staggered, with errors in the front-to-back direction and the left-to-right direction, and ensure that the fan brackets 21 of the left front wing 11 and the left rear wing 12 do not interfere with each other and the relative distance is minimized when the left front wing 11 and the left rear wing 12 are closed. Similarly, the fan brackets 21 of the right front wing 13 and the fan brackets 21 of the right rear wing 14 are staggered, with errors in the front-to-back direction and the left-to-right direction, and ensure that the fan brackets 21 of the right front wing 13 and the right rear wing 14 do not interfere with each other and the relative distance is minimized when the left front wing 11 and the left rear wing 12 are closed. After the left rear wing 11, the right front wing 13, and the right rear wing 14 are deployed, the fan brackets 21 on the left front wing 11, the left rear wing 12, the right front wing 13, and the right rear wing 14 are evenly distributed in an isosceles trapezoidal shape. At this point, the ducted fans 20 on the left front wing 11, the left rear wing 12, the right front wing 13, and the right rear wing 14 are also evenly distributed in an isosceles trapezoidal shape. The distance between the ducted fans 20 on the left front wing 11 and the right front wing 13 is smaller than the distance between the ducted fans 20 on the left rear wing 12 and the right rear wing 14. The first electric push rod internally comprises a nut and a screw. When the motor drives the screw to rotate, the nut moves axially along the screw, converting the motor's rotational motion into linear motion, enabling the push rod to extend and retract, and ensuring self-locking at each position.

[0064] The fan bracket 21 extends diagonally downward, specifically diagonally forward, from the underside of the left front wing 11, left rear wing 12, right front wing 13, or right rear wing 14. The ducted fan 20 is mounted at the end of the fan bracket 21. When the ducted fan 20 is tilted to the vertical position, the left front wing 11, left rear wing 12, right front wing 13, or right rear wing 14 do not obstruct the ducted fan 20 vertically. The fan bracket 21 extends diagonally downward rather than vertically to ensure that when the ducted fan 20 is tilted to the vertical position, the air intake is not blocked by the wing on the fan's rotation axis, thereby rendering the fan power ineffective. Furthermore, a diagonal brace is attached to the fan bracket 21 to increase rigidity and strength, further ensuring the stability of the fan bracket 21 and the ducted fan 20 mounted thereon.

[0065] During implementation, at the take-off stage, after the wings (left front wing 11 and left rear wing 12, as well as right front wing 13 and right rear wing 14) are fully unfolded, the UAV is in rotor mode. At this time, the motors of the fan steering drive mechanism 22 corresponding to the electric push rods of each ducted fan 20 are energized at the same time, and the motors will drive the screw to rotate. Through the cooperation of the nut and the screw, the nut converts the rotational motion of the motor into linear motion, so that its telescopic rod extends. Since the two ends of the electric push rod are rotatably connected, and the ducted fan 20 is fixed at the end by the bracket and can rotate around the axis, the extension of the telescopic rod of the electric push rod will cause the ducted fan 20 to tilt upward around the axis, and the ducted fan 20 is in a vertical state. At this time, Figure 2 As shown, the ducted fan 20 is then started. When the blades of the ducted fan 20 reach a specified rotational speed, sufficient lift is provided, allowing the drone to lift off the ground. Similarly, during the cruise phase, the two wings (the left front wing 11 and the left rear wing 12, as well as the right front wing 13 and the right rear wing 14) are combined, and the ducted fan 20 is brought into a horizontal state (front and back facing) by contracting the telescopic rod of the fan steering drive mechanism 22 of the electric push rod. At this time, the blades of the ducted fan 20 reach a specified rotational speed to allow the drone to reach a certain speed. The pressure difference between the upper and lower surfaces of the wing can provide upward force. The ducted fan only needs to overcome the aerodynamic force at this time to maintain high-speed flight, achieving high speed with low power consumption. During the landing phase, the wings on both sides (the left front wing 11 and the left rear wing 12, as well as the right front wing 13 and the right rear wing 14) are unfolded, and the ducted fans 20 are placed in a vertical state through the telescopic rod of the electric push rod. By slowly reducing the speed of the blades of the ducted fan 20, the upward lift is reduced, thereby slowly lowering the altitude and achieving a soft landing of the drone.

[0066] A storage compartment 16 is provided at the bottom of the main fuselage 10. This compartment can be used to store supplies. In this case, the drone is a carrier drone. The bottom of the storage compartment 16 extends downward through the bottom surface of the main fuselage 10 to form a storage compartment exit 17. Doors 18 are pivotally mounted on either side of the storage compartment exit 17. When the doors 18 are pivoted and closed, they seal the storage compartment exit 17, allowing supplies to be placed inside. When the doors 18 are pivoted and opened, supplies can be removed from the storage compartment exit 17. A fuselage floor panel 47 is provided at the bottom of the fuselage 111, and the storage compartment exit 17 is formed on this floor panel. A third electric push rod 41 is also provided on either side of the bottom of the main fuselage 10. Door push rods 42 are provided at the bottom of each door 18. One end of the door push rod 42 is pivotally connected to the door 18 on the same side, and the other end is pivotally connected to the telescopic rod of the third electric push rod 41 on the same side.

[0067] The front and rear ends of the storage compartment 16 are respectively provided with push-pull electromagnets 43, and the ends of the telescopic rods of the push-pull electromagnets 43 are provided with hatch locks 44. The hatches 18 on both sides are respectively provided with C-shaped locking rings 45. When the hatches 18 on both sides are rotated and closed to seal the storage compartment exit 17, the C-shaped locking rings 45 of the hatches 18 on both sides can form an annular structure for inserting the hatch locks 44. When the hatch locks 44 are inserted into the annular structure formed by the C-shaped locking rings 45 on both sides, the C-shaped locking rings 45 can be limited by the hatch locks 44, and at this time the hatches 18 on both sides cannot rotate. In a preferred embodiment, the bottom side surface of the end of the hatch lock 44 where the C-shaped locking ring 45 is inserted is an inclined surface, so that when the hatch 18 is closed and the C-shaped locking ring 45 passes through the inclined surface of the hatch lock 44, the hatch lock 44 can be driven to retract until the C-shaped locking ring 45 and the hatch 18 are closed. The C-shaped locking ring 45 passes over the hatch lock 44, and under the action of the electromagnet spring, the hatch lock 44 is reset and inserted into the annular structure formed by the C-shaped locking rings 45 on both sides to achieve the closure and locking of the hatch 18.

[0068] The storage compartment 16 is provided with protrusions 46 on the front and rear sides respectively, so that when the door lock 44 is inserted into the ring structure formed by the C-shaped lock ring 45, the bottom of the door lock 44 abuts against the top of the protrusion 46, with the protrusion 46 as a fulcrum.

[0069] During operation, the telescopic rods of the push-pull electromagnets 43 are normally extended. Third electric push rods 41, mounted on vertical support plates on either side of the fuselage frame's bottom, provide the power to open and close the hatches 18. One push-pull electromagnet 43 is mounted on the front of the fuselage floor 47, aligned with the closing lines of the two hatches 18. The other push-pull electromagnet 43 is mounted on the rear of the fuselage floor 47, aligned with the closing lines of the two hatches 18. A hatch lock 44 is connected to the front of each electromagnet push rod. This lock, coupled with a C-shaped locking ring 45 inserted into the chassis door, secures the hatches 18, preventing the doors from accidentally opening and the contents from falling. Protrusions 46 are provided on the front and rear sides of the storage compartment 16. These protrusions serve as fulcrums for the hatch locks 44 when the doors 18 are closed, reliably supporting large loads and increasing the cargo capacity. A panoramic camera 50 is mounted on the front bottom of the fuselage floor 47 for real-time observation of the external environment and control of the drone's flight direction via the flight control board 120. A landing gear 48 is mounted on the bottom of the fuselage floor 47 via four landing gear clips. These support the drone's safe takeoff and landing, maintain the drone's height above the ground to avoid contact with ground obstacles, and assist in ground maneuvering. When the push-pull electromagnet 43 is energized, its telescopic rod retracts, and the door lock 44 retracts outside the annular structure formed by the C-shaped locking ring 45. Then, the third electric push rod 41 is energized, and the motor reverses, causing its telescopic rod to retract, pulling the door push rods 42 on both sides upward. Because the door 18 is restrained on one side by the shaft, the door push rods 42 pull it outward. When the sufficient rotation angle is reached, the cargo falls under the action of gravity, allowing the cargo to be released. After release, the push-pull electromagnet 43 is de-energized, and its telescopic rod is in its extended state. The third electric push rod 41 is energized, causing the motor to rotate forward, causing the cargo to be released. The telescopic rod is extended, pushing the door push rods 42 on both sides downward. Since one side of the door 18 is restricted by the rotating shaft, the door 18 is rotated inward. When the C-shaped locking ring 45 on the door 18 contacts the inclined surface of the door lock 44, the door 18 continues to rotate, causing the door lock 44 to retreat, and the spring of the push-pull electromagnet 43 is stretched until the doors 18 on both sides are horizontally closed. At the same time, the top of the C-shaped locking ring 45 will pass over the door lock 44. Under the action of the electromagnet spring, the door lock 44 is reset and placed in the ring structure formed by the C-shaped locking ring 45, thereby achieving the closure and locking of the door 18.

[0070] The following is a more specific implementation example, which details the logistics transportation tasks of the drone of the present invention through the specific implementation of the drone preparation stage, take-off stage, cruising stage, hovering delivery stage and landing stage.

[0071] During the preparation phase, the drone is in fixed-wing mode and parked on open ground. The supplies are stably placed inside the storage compartment 16. The left and right doors 18 are closed and locked. The lithium battery in the power compartment 19 is fully charged. All components have been adjusted. The flight route is clear and the road environment is safe. The flight controller is in the operating room, the main power is turned on, and preparations for takeoff are made.

[0072] During takeoff, the flight control board 120 sends a control signal, energizing the second electric push rod 31 at the wing shaft. The motor begins to rotate forward, driving its telescopic rod outward. With the help of the wing joints 32 on both sides, the linear motion of the electric push rod is converted into outward tilting motion of the wing rotating push rod 33. As the wing rotating push rod 33 continues to rotate, the force it exerts on both sides causes each wing (the left front wing 11 and the left rear wing 12, as well as the right front wing 13 and the right rear wing 14) to gradually unfold outward, slowly spreading open like "scissors" until the entire wing structure moves to the "dead point" position. The flight control board 120 sends a control signal, de-energizing the second electric push rod 31. At this time, the left front wing 11 and the left rear wing 12, as well as the right front wing 13 and the right rear wing 14 on the same side are fully opened until the wings on the same side are at 75 degrees to each other and remain stable. From this point, the flight control board 120 issues a further control signal, energizing the motor of the fan steering drive mechanism 22 for forward rotation. This drives the screw, which, through the transmission pair between the nut and the screw, converts the motor's rotational motion into linear motion. The telescopic rod extends, causing each ducted fan 20 to tilt upward about its axis to a vertical position. The flight control board 120 then issues a control signal, de-energizing the fan steering drive mechanism 22 and locking it. Subsequently, the flight control board 120 issues another control signal, energizing each ducted fan 20. When the blade speed of each ducted fan 20 reaches a preset value, sufficient lift is generated, allowing the drone to lift off and prepare for cruise.

[0073] During the cruise phase, the flight control board 120 sends a control signal, causing the motor of the fan steering drive mechanism 22 to reverse, and the telescopic rod to retract, causing each ducted fan 20 to tilt horizontally to 45 degrees. This also increases the speed of the ducted fan 20 blades, allowing the drone to maintain lift while flying forward. When a certain forward speed is reached, due to the different cross-sectional configurations of the front and rear wings, the rear wing can maintain a greater pressure differential and provide greater lift. Therefore, the flight control board 120 sends a control signal to reverse the motor of the fan steering drive mechanism 22 of the left rear wing 12 and the right rear wing 14. The telescopic rod retracts, causing the ducted fans 20 of the left rear wing 12 and the right rear wing 14 to first enter a horizontal state. Then, the motor of the second electric push rod 31 is reversed, and the wing joint 32 retracts, merging the left front wing 11 with the left rear wing 12, and the right front wing 13 with the right rear wing 14. During this process, the ducted fans 20 of the left and right front wings 11 and 13 are continuously regulated to ensure equal lift front-to-back and left-to-right, maintaining dynamic balance. After the wings merge, the flight control board 120 issues a control signal, energizing the motors of the fan steering drive mechanisms 22 of the left and right front wings 11 and 13, reversing their rotation. The telescopic rods retract, bringing the ducted fans 20 of the left and right front wings 11 and 13 into a horizontal position. The flight control board 120 then issues further control signals to adjust the rotational speed of each ducted fan 20, bringing the drone to its rated high speed. The panoramic camera 50 below the drone then observes the ground environment in real time. The flight control board 120 further adjusts the ailerons 129, rudder 122, and elevator 124 to control the drone's flight direction, directing it toward the launch site in preparation for hovering and launch.

[0074] During the hovering release phase, when the drone reaches the designated release location, the flight control board 120 sends a control signal, energizing the motors of the fan steering drive mechanisms 22 of the left front wing 11 and right front wing 13 to rotate forward. The telescopic rod extends, tilting the ducted fans 20 of the left and right front wings 11 and 13 to a vertical position. The motor of the second electric push rod 31 then energizes the motors to rotate forward, causing the telescopic rod to extend, opening the front and rear wings until they reach their "dead point" position, where they self-lock. During this process, the ducted fans 20 of the left and right front wings 11 and 13 are continuously regulated to ensure equal lift front-to-back and left-to-right, maintaining dynamic balance. After the wings are fully deployed, the flight control board 120 sends a control signal, energizing the motors of the fan steering drive mechanisms 22 of the left and right rear wings 12 and 14 to rotate forward. The telescopic rod extends, placing the ducted fans 20 of the left and right rear wings 12 and 14 in a vertical position. The flight control board 120 then issues a control signal to adjust the speed of the blades of each ducted fan 20, ensuring that the drone maintains a certain amount of lift to support it. Due to air resistance, the drone's forward speed gradually decreases. By adjusting the speed of the ducted fan 20 blades, the drone's chassis door is aligned at a certain height and aligned with the drop site. The flight control board 120 issues a control signal to energize the push-pull electromagnet 43, causing the electromagnet push rod to retract, causing the door lock 44 to retreat into the annular structure formed by the C-shaped lock ring 45. Then, the third electric push rod 41 is energized, causing the motor to reverse and retract, causing the push rods 42 on both sides of the door to rotate outward. Because one side of the door 18 is constrained by the rotating shaft, the door push rods 42 act to rotate the door 18 outward. When the rotation angle reaches a predetermined value, the cargo naturally falls due to gravity. After the drop operation is completed, the push-pull electromagnet 43 is de-energized, and its electromagnet push rods return to their initial extended state. At this point, the flight control board 120 issues a control signal, energizing the third electric push rod 41. Its motor rotates forward, extending the push rod and driving the door push rods 42 on both sides to rotate inward. This rotation forces the door 18 to close inward. When the C-shaped locking ring 45 on the door 18 contacts the inclined surface of the door lock 44, as the door 18 continues to rotate, the door lock 44 is forced back, causing the electromagnet spring to stretch until both doors 18 are horizontally closed. The top of the C-shaped locking ring 45 passes over the door lock 44. Under the restoring force of the electromagnet spring, the door lock 44 returns to its original position and retracts into the ring structure formed by the C-shaped locking ring 45, thus closing and locking the door 18. The flight control board 120 issues a control signal, regulating the speed of each ducted fan 20 to move the drone above the landing site and prepare for landing.

[0075] During the landing phase, when the drone is directly above the landing site, the flight control board 120 issues a control signal, regulating the speed of the ducted fans 20 to slowly lower the drone until the landing gear 48 touches the ground, achieving a soft landing. The flight control board 120 then sends a control signal, energizing the motor of the second electric push rod 31 to reverse, retracting the push rod and merging the front and rear wings. The drone then waits for data integration. Once integration is complete, it sends a detailed report on the mission to the control room, then disconnects the drone's power supply, completing the logistics transport mission.

[0076] This invention proposes a new type of drone that utilizes a single power system, yet combines the advantages of both fixed-wing and rotary-wing drones. It boasts a large payload, long endurance, and high flexibility, enabling it to effectively perform a variety of flight missions. By integrating the advantages of both rotary-wing and fixed-wing drones, it switches flight modes based on the flight process. During takeoff and landing, it switches to rotary-wing mode, achieving vertical takeoff and landing and hovering. During the cruise phase, it switches to fixed-wing mode, achieving long endurance and high speed. This effectively enhances payload capacity, endurance, and flexibility, allowing it to adapt to diverse and complex terrain and environmental conditions, including urban, mountainous, and island environments, significantly expanding its coverage area.

[0077] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present invention should be included in the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be based on the scope of protection of the claims.

Claims

1. A scissor-wing drone, characterized in that: Includes: fuselage body (10); A left front wing (11), a left rear wing (12), a right front wing (13) and a right rear wing (14), wherein the left front wing (11) and the left rear wing (12) are located on the left side of the fuselage main body (10), and the right front wing (13) and the right rear wing (14) are located on the right side of the fuselage main body (10), and one end of the left front wing (11), the left rear wing (12), the right front wing (13) and the right rear wing (14) are respectively rotatably connected to the fuselage main body (10); a wing opening and closing drive mechanism, which is arranged on the fuselage body (10) to drive the left front wing (11) and the left rear wing (12) to rotate so as to fit together front and back to form a left fixed wing, and to drive the right front wing (13) and the right rear wing (14) to rotate so as to fit together front and back to form a right fixed wing; or to drive the left front wing (11) and the left rear wing (12) to rotate so as to spread out front and back to each other, and to drive the right front wing (13) and the right rear wing (14) to rotate so as to spread out front and back to each other; Ducted fans (20) are respectively arranged on the left front wing (11), the left rear wing (12), the right front wing (13) and the right rear wing (14); A fan steering drive mechanism (22) is provided on the left front wing (11), the left rear wing (12), the right front wing (13) and the right rear wing (14) to drive the ducted fan (20) to switch between a front-to-back facing state and a vertical state.

2. The scissor-wing drone according to claim 1, characterized in that: The ducted fan (20) is respectively mounted on the left front wing (11), the left rear wing (12), the right front wing (13) or the right rear wing (14) via a fan bracket (21), and the ducted fan (20) is rotatably connected to the fan bracket (21); The fan steering drive mechanism (22) is a first electric push rod, one end of which is rotationally connected to the left front wing (11), the left rear wing (12), the right front wing (13) or the right rear wing (14), and the other end of which is rotationally connected to the ducted fan (20).

3. The scissor-wing drone according to claim 2, characterized in that: The fan bracket (21) extends obliquely downward from the bottom surface of the left front wing (11), the left rear wing (12), the right front wing (13) or the right rear wing (14); the ducted fan (20) is mounted at the end of the fan bracket (21); and when the ducted fan (20) is converted to a vertical state, the left front wing (11), the left rear wing (12), the right front wing (13) or the right rear wing (14) does not block the ducted fan (20) in the vertical direction.

4. The scissor-wing drone according to claim 1, characterized in that: The left front wing (11) and the right front wing (13) are provided with a receiving groove (15) on their rear side surfaces. When the left front wing (11) and the left rear wing (12) are fitted together front and back, the front side of the left rear wing (12) is fitted into the receiving groove (15) of the left front wing (11); and when the right front wing (13) and the right rear wing (14) are fitted together front and back, the front side of the right rear wing (14) is fitted into the receiving groove (15) of the right front wing (13).

5. The scissor-wing drone according to claim 4, characterized in that: The bottom of the accommodating groove (15) is arc-shaped, and the front side surfaces of the left rear wing (12) and the right rear wing (14) are corresponding arc surfaces.

6. The scissor-wing drone according to claim 1, characterized in that: The wing opening and closing drive mechanism includes a wing opening and closing unit. The wing opening and closing units are two and are relatively arranged on the left and right sides of the top of the fuselage body (10) and correspond to the left front wing (11) and the left rear wing (12) on the left side and the right front wing (13) and the right rear wing (14) on the right side. The wing opening and closing unit includes a second electric push rod (31), a wing connection joint (32) and a wing rotation top rod (33). The second electric push rod (31) is fixedly mounted on the fuselage body. The second electric push rod (31) is provided on the main body (10) and extends toward the side. The end of the telescopic rod of the second electric push rod (31) is connected to the end of the wing connection joint (32). There are two wing rotation top rods (33). One end of the two wing rotation top rods (33) is respectively and one-to-one connected to the two ends of the wing connection joint (32), and the other end is respectively and one-to-one connected to the left front wing (11), the left rear wing (12), the right front wing (13) or the right rear wing (14) on the same side.

7. The scissor-wing drone according to claim 6, characterized in that: The two ends of the wing joint (32) are rounded at the part away from the second electric push rod (31), and are right angled at the part close to the second electric push rod (31), so that when the telescopic rod of the second electric push rod (31) is retracted, the wing rotating top rods (33) at the two ends of the wing joint (32) rotate close to each other, thereby driving the left front wing (11) and the left rear wing (12) on the same side to rotate so as to fit together front and back to form the left fixed wing, and driving the right front wing (13) and the right rear wing (14) to rotate so as to fit together front and back to form the right fixed wing, and when the second electric push rod (3 When the telescopic rod 1) is extended, the wing rotating top rods (33) at both ends of the wing connecting joint (32) rotate and unfold relative to each other, thereby driving the left front wing (11) and the left rear wing (12) on the same side to rotate and unfold relative to each other, and driving the right front wing (13) and the right rear wing (14) to rotate and unfold relative to each other, and when the wing rotating top rods (33) at both ends of the wing connecting joint (32) rotate and unfold relative to each other to a certain angle, the end surface of the wing rotating top rod (33) abuts against the end surface of the wing connecting joint (32), so that the wing rotating top rod (33) can no longer be unfolded.

8. The scissor-wing drone according to claim 1, characterized in that: A storage compartment (16) is provided at the bottom of the fuselage body (10), the bottom of the storage compartment (16) passes downward through the bottom surface of the fuselage body (10) to form a storage compartment outlet (17), and doors (18) are rotatably provided on both sides of the storage compartment outlet (17), and when the doors (18) on both sides are rotated and closed, the storage compartment outlet (17) can be closed. A third electric push rod (41) is further provided on both sides of the bottom of the fuselage main body (10), and a door push rod (42) is provided at the bottom of the doors (18) on both sides. One end of the door push rod (42) is rotatably connected to the door (18) located on the same side, and the other end is rotatably connected to the telescopic rod of the third electric push rod (41) located on the same side.

9. The scissor-wing drone according to claim 8, characterized in that: The front and rear ends of the storage compartment (16) are respectively provided with push-pull electromagnets (43), the end of the telescopic rod of the push-pull electromagnet (43) is provided with a hatch lock (44), and the hatches (18) on both sides are respectively provided with C-shaped locking rings (45), and when the hatches (18) on both sides are rotated and closed to seal the storage compartment outlet (17), the C-shaped locking rings (45) of the hatches (18) on both sides can form a ring structure for inserting the hatch lock (44).

10. The scissor-wing drone according to claim 9, characterized in that: The storage compartment (16) is provided with protrusions (46) on both the front and rear sides, respectively, so that when the door lock (44) is inserted into the ring structure formed by the C-shaped lock ring (45), the bottom of the door lock (44) abuts against the top of the protrusion (46).

Images