Modular drones

Abstract

The present invention relates to the field of aircraft technology, and in particular to a modular unmanned aerial vehicle (UAV), comprising a front fuselage, a rotating base, a blade module, a rear fuselage, and a wing module. The rear fuselage is connected to the front fuselage in an axial direction, and the UAV can form an axial structure through the front fuselage and the rear fuselage. The rotating base is sleeved on the front fuselage and is rotatably connected to the front fuselage. The blade module is arranged in a circumferential direction of the rotating base and is retracted to the rotating base. The wing module is connected to the rear fuselage and is retracted to the rear fuselage. The blade module and the wing module are respectively retracted to the rotating base and the rear fuselage, so that the UAV actually forms a static rod-shaped structure, which is convenient for filling into tubular objects such as rocket launchers or artillery, thereby enabling the UAV to effectively cooperate with the battlefield launch and delivery of rocket launchers, artillery, and fighter aircraft, so that the UAV can reach a preset battle position in real time.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a modular unmanned aerial vehicle. Background Art

[0002] High-tech, accurate, and information-based battlefield reconnaissance, intelligent remote command, and precision destruction have become the key factors in determining victory or defeat. Due to their advantages in concealment, environmental adaptability, and controllability, drones are poised to replace manned aircraft as the primary combat platform in future wars.

[0003] Current military fixed-wing drones and loitering munitions generally utilize an integrated fixed fuselage and rigid wings. Consequently, their overall dimensions, particularly the lateral footprint of their wingspan, are generally large, making them difficult to shrink and fit into tubular objects like rocket launchers or artillery, enabling high-speed, instantaneous launch. They are also not suitable for mid-air suspension or clustered delivery from fighter aircraft. Furthermore, these models have limited functionality and generally lack versatility. Summary of the Invention

[0004] In view of this, it is necessary to provide a modular UAV to solve the technical problems in the prior art that UAVs are difficult to adapt to high-speed arrow shooting and artillery shooting and to be dropped from fighter jets in the air or in clusters.

[0005] To achieve the above technical objectives, the technical solution of the present invention provides a modular drone, comprising:

[0006] front fuselage;

[0007] A rotating base, sleeved on the front fuselage and rotatably connected to the front fuselage;

[0008] a blade module, arranged in the circumferential direction of the rotating base, capable of being retracted from the rotating base and deployed during flight;

[0009] a rear fuselage connected to the front fuselage and extending in the axial direction of the front fuselage; and

[0010] The wing module is connected to the rear fuselage and can be retracted to the rear fuselage and can be unfolded during flight.

[0011] Furthermore, the blade module includes a plurality of blades and a plurality of elastic members, each of the blades is arranged at intervals in the circumferential direction of the rotating base and is hinged to the rotating base, each of the blades is retracted to the rotating base, one end of each of the elastic members is connected to the rotating base, and each of the elastic members is used to drive each of the blades to unfold when the drone is flying.

[0012] Furthermore, the UAV also includes a locking component, and the locking component includes a fairing or a projectile shell.

[0013] Furthermore, the front fuselage includes a guide head, a power base and a tail connecting seat, the guide head, the power base and the tail connecting seat are connected in sequence, the rotating base is mounted on the power base and can be rotated by the drive of the power base, and the rear fuselage is connected to the tail connecting seat.

[0014] Furthermore, the tail connecting seat is hinged to the power base, and the front fuselage also includes a steering drive module, which is installed on the tail connecting seat and is drivingly connected to the power base for driving the power base to rotate.

[0015] Furthermore, the steering drive module includes a plurality of traveling arms and a plurality of servos, each of the traveling arms is arranged at intervals along the circumferential direction of the tail connecting seat, one end of each of the traveling arms is hinged to the power base, and each of the servos is installed inside the tail connecting seat and is respectively connected to the other end of each of the traveling arms.

[0016] Furthermore, the wing module includes two wing bags, which are respectively connected to both sides of the rear fuselage and wrapped around the rear fuselage. The modular drone also includes an inflation source, which is connected to the two wing bags and is used to inflate the two wing bags so that the two wing bags are unfolded.

[0017] Furthermore, the modular UAV also includes an antenna, which is hinged to the rear fuselage and can compress the two wing bags in a rolled-up state by rotating around the rear fuselage.

[0018] Furthermore, a limiting slot is provided at one end of the rear fuselage away from the front fuselage, and the limiting slot extends along the axial direction of the rear fuselage. The antenna is hinged to the limiting slot and can be unfolded by rotating around the rear fuselage.

[0019] Furthermore, the wing bag includes a bag casing, a plastic wing sheet and a limiting tie rod. The bag casing is connected to the rear fuselage and is used to be unfolded when inflated. The plastic wing sheet is attached to the bag casing.

[0020] Compared with the prior art, the advantageous effects of the modular UAV of the present invention include: by arranging a front fuselage, a rotating base, a blade module, a rear fuselage and a wing module, the rear fuselage is connected to the axial direction of the front fuselage, and the UAV can form an axis-type structure through the front fuselage and the rear fuselage, the rotating base is sleeved on the front fuselage and is rotatably connected to the front fuselage, the blade module is arranged in the circumferential direction of the rotating base and is retracted to the rotating base, the wing module is connected to the rear fuselage and is retracted to the rear fuselage, the blade module and the wing module are respectively retracted to the rotating base and the rear fuselage, so that the UAV can be filled with rocket launchers or artillery. After the drone starts, the blade module and the wing module are unfolded, and the rotating base drives the blade module to rotate, so that the drone can maintain normal flight. Through the above structure, the drone can effectively cooperate with the rapid launch and delivery of rockets, artillery and fighter jets on the battlefield, and reach the preset combat position instantly with the help of the high speed of the loaded bomb, and then significantly increase its flight range and hovering time through the traction flight of its own power and the lift-increasing glide of the wings, so as to better perform battlefield tasks such as reconnaissance and electronic warfare, and even directly attack or detonate to destroy high-value enemy targets. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is a front view of a modular drone provided by an embodiment of the present invention;

[0022] Figure 2 is an exploded view of a modular drone provided by an embodiment of the present invention;

[0023] Figure 3 This is a schematic structural diagram of a modular UAV in flight according to an embodiment of the present invention;

[0024] Figure 4 This is a schematic structural diagram of a modular UAV rocket in a shooting state provided by an embodiment of the present invention;

[0025] Figure 5 It is a structural schematic diagram of the projection state of the modular UAV mother machine provided by an embodiment of the present invention.

[0026] Among them, the reference numerals in the figures are:

[0027] 10—front fuselage 11—guide head 12—power base

[0028] 13—Tail connector 14—Steering drive module 20—Rotating base

[0029] 30 - propeller module 31 - propeller blade 40 - rear fuselage

[0030] 41 - Limiting groove 50 - Wing module 51 - Wing bag

[0031] 60 - fairing 70 - antenna 131 - articulated ball

[0032] 141—Servo 511—Bag 512—Plastic Wing

[0033] 513—Limited Tie Bar 10a—Rocket 20a—Mother Machine

[0034] 21a—Drop chamber. DETAILED DESCRIPTION

[0035] The preferred embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings, wherein the accompanying drawings constitute a part of this application and are used together with the embodiments of the present invention to illustrate the principles of the present invention, and are not used to limit the scope of the present invention.

[0036] Most of the current drones use non-folding wings or non-deformable wings. When performing long-range battlefield reconnaissance and precision strike missions, they can only fly as fixed-wing aircraft. They have low flight speed and a single flight trajectory, weak high-speed penetration capability, and are easily detected by battlefield detection radar. The probability of being intercepted is high and the mission success rate is low. Currently, some drones are launched by catapult, but the design of foldable-wing drones and the research on catapult systems are relatively independent, and the effective combination of foldable-wing drones with drone missile-carrying systems and catapult devices has not yet been achieved.

[0037] An embodiment of the present invention provides a modular drone. Through structural design, the drone can be loaded into a tubular device such as a rocket launcher or artillery before takeoff, and the drone can then be launched at high speed by arrows or artillery using the rocket launcher or artillery, thereby solving the technical problems in the prior art that drones are difficult to adapt to high-speed arrow and artillery launch equipment and are difficult to be suspended or clustered for delivery from fighter jets in the air.

[0038] In order to achieve the above technical objectives, Figure 1-5 As shown, the modular UAV provided by the embodiment of the present invention includes a front fuselage 10, a rotating base 20, a blade module 30, a rear fuselage 40 and a wing module 50. The rotating base 20 is mounted on the front fuselage 10 and is rotatably connected to the front fuselage 10; the blade module 30 is arranged in the circumferential direction of the rotating base 20 and can be retracted to the rotating base 20, and the blade module 30 can be unfolded during flight; the rear fuselage 40 is connected to the front fuselage 10 and extends in the axial direction of the front fuselage 10; the wing module 50 is connected to the rear fuselage 40 and can be retracted to the rear fuselage 40, and the wing module 50 can also be unfolded during flight.

[0039] Specifically, by setting the front fuselage 10, the rotating base 20, the blade module 30, the rear fuselage 40 and the wing module 50, the rear fuselage 40 is connected to the axial direction of the front fuselage 10, and the UAV can form an axial structure through the front fuselage 10 and the rear fuselage 40, the rotating base 20 is sleeved on the front fuselage 10 and is rotatably connected to the front fuselage 10, the blade module 30 is set in the circumferential direction of the rotating base 20 and retracted to the rotating base 20, the wing module 50 is connected to the rear fuselage 40 and retracted to the rear fuselage 40, the blade module 30 and the wing module 50 are respectively retracted to the rotating base 20 and the rear fuselage 40, so that the UAV can be filled into a tubular object such as a rocket launcher or artillery, and then can be launched through the rocket launcher. Or artillery realizes high-speed arrow shooting and artillery shooting of the drone, accelerates the start of the drone, and enables the drone to reach the preset combat position instantly. After the drone starts, the blade module 30 and the wing module 50 are unfolded, and the rotating base 20 drives the blade module 30 to rotate. The blade module 30 provides power for the drone to fly by rotation, and the wing module 50 ensures the balance of the flight state, so that the drone maintains normal flight. Through the above structure, the drone can effectively cooperate with the battlefield launch and delivery of rocket launchers, artillery and fighter jets, and then through the traction flight of its own power and the lift-increasing glide of the wings, it can significantly increase its flight range and hovering time, so that it can better perform battlefield tasks such as reconnaissance warfare and electronic warfare, and can even directly attack or detonate to destroy high-value enemy targets.

[0040] It is understandable that the front fuselage 10 can be any axis-type structure, and the front fuselage 10 can drive the rotating base 20 to rotate by providing a driving device such as a motor connected to the rotating base 20.

[0041] In one embodiment, Figure 1-5 As shown, the front fuselage 10 includes a guide head 11, a power base 12, and a tail connecting base 13. The guide head 11, the power base 12, and the tail connecting base 13 are connected in sequence. The rotating base 20 is sleeved on the power base 12 and can be rotated by the power base 12. The rear fuselage 40 is connected to the tail connecting base 13. Specifically, the front end of the guide head 11 is a conical or curved structure, which reduces the resistance of the UAV flight and guides the flight of the UAV. The power base 12 can be connected to the rotating base 20 and drives the rotating base 20 to rotate, thereby driving the blade module 30 to rotate. The tail connecting base 13 can be connected to the rear fuselage 40. The guide head 11, the power base 12, and the tail connecting base 13 are connected in sequence to form the axial structure of the front fuselage 10.

[0042] In this embodiment, the power base 12 is the stator of the motor, and the rotating base 20 is the rotor of the motor. The power base 12 drives the rotating base 20 to rotate by applying magnetic force to the rotor.

[0043] In this embodiment, the tail connecting seat 13 can be connected to the power base 12 in a fixed connection, a rotational connection, or other forms.

[0044] In this embodiment, the guide head 11 is the front section of the fuselage 10 that provides the guiding function.

[0045] In this embodiment, the power base 12 and the tail connecting base 13 can be used to install the guidance flight control system device, power energy and air source, which is actually the middle fuselage of the UAV central control part.

[0046] In this embodiment, the rear fuselage 40 is a mission module compartment, such as a reconnaissance combat compartment, an electronic combat compartment, a high-explosive bomb compartment, and a thermobaric bomb compartment.

[0047] In one embodiment, Figure 1-5 As shown, the tail connector 13 is hingedly connected to the power base 12, and the front fuselage 10 also includes a steering drive module 14. The steering drive module 14 is mounted on the tail connector 13 and is drivingly connected to the power base 12 for driving the power base 12 to rotate. Specifically, the tail connector 13 is hingedly connected to the power base 12 so that the tail connector 13 can steer by rotating around the power base 12. When the UAV is in flight, the steering drive module 14 drives the power base 12 to rotate, thereby driving the power base 12 and the guide head to steer, thereby achieving steering control of the UAV.

[0048] In one embodiment, Figure 2 As shown, a ball groove is provided at one end of the power base 12 close to the tail connecting seat 13, and a hinge ball 131 is provided at one end of the tail connecting seat 13 close to the power base 12, and the hinge ball 131 is hinged to the ball groove.

[0049] In one embodiment, Figure 1-5 As shown, the steering drive module 14 includes several traveling arms 141 and several servos. Each traveling arm 141 is spaced apart along the circumference of the tail connector 13. One end of each traveling arm 141 is hinged to the power base 12. Each servo is installed inside the tail connector 13 and connected to the other end of each traveling arm 141. Specifically, each traveling arm 141 is connected to the power base 12, and the servo can provide a pulling force to each traveling arm 141, causing each traveling arm 141 to swing the power base 12. Each traveling arm 141 drives the power base 12 to achieve steering of the drone.

[0050] In this embodiment, Figure 1-5 As shown, there are four swimming rods 141. The two swimming rods 141 on the left and right sides are used to control the left and right steering of the drone, and the two swimming rods 141 on the upper and lower sides are used to control the up and down steering of the drone, with 360° omnidirectional vector adjustment capability.

[0051] In this embodiment, when the UAV needs to adjust according to its own seeker information or background flight control instructions, the AI ​​intelligent electronic signal device (integrated electronic control) first decomposes the information instructions into different electrical signals and distributes them to the vector maneuver instruction actuator (4 servos) to perform push and pull actions of different strokes respectively. Then, through the floating control of the flight control pull rod connection device, the specific deflection of the power base 12 is jointly adjusted by real-time vector. When the two form a certain angle, the power base 12 will produce a new swing head direction, and the propeller blades 31 of the central power base 12 will also directly generate pulling force in the new direction, thereby timely changing the flight direction or flight attitude of the entire UAV, thereby realizing the UAV's own intelligent adjustment or the rear directive flight control.

[0052] Unlike existing fixed-wing drones that use multiple flight control servos to separately control horizontal and vertical control surfaces, the drone's flight direction and attitude can only be slowly adjusted by changing the direction of the control surfaces to influence the airflow over them. The modular drone's steering flight control system provided by the present invention can rapidly and effectively adjust the direction of the front fuselage 10 (and the nose) using a coordinated force. The propeller blades 31 then directly exert force in the new direction, achieving instant control. This is a drone that directly utilizes active force to achieve vector flight control, resulting in highly responsive and maneuverable drones.

[0053] It can be understood that the blade module 30 can be deployed under the centrifugal effect of the rotation of the rotating base 20, or can be deployed by the elastic force of the auxiliary elastic member.

[0054] In one embodiment, Figure 1-5 As shown, the blade module 30 includes a plurality of blades 31 and a plurality of elastic members (not labeled in the figure). Each blade 31 is arranged at intervals in the circumferential direction of the rotating base 20 and is hinged to the rotating base 20. Each blade 31 is retracted to the rotating base 20, and one end of each elastic member is connected to the rotating base 20. Each elastic member is used to drive each blade 31 to deploy when the drone is in flight. Specifically, the blade module 30 is provided with blades 31 and elastic members. When the drone is in flight, each blade 31 deploys under the elastic force of the elastic member, thereby providing power for the drone's flight. The elastic member not only provides power for the deployment of the blades 31, but also adaptively adjusts the angle of the blades 31 according to the rotational speed of the blades 31, thereby ensuring the drone's stable flight.

[0055] In this embodiment, the elastic member is actually a deformable strip-shaped spring. One end of the spring, away from the hinge at the base of blade 31, is fixed to rotating base 20, while the other end is free. When blade 31 is flattened, the spring is compressed. When blade 31 is released, the spring spring springs upward to provide assistance. Once the blade is erected, the free end of the spring spring presses against the base of blade 31, preventing it from falling back under the force.

[0056] It is understandable that each blade 31 can be retracted to the rotating base 20 through the limiting effect of a locking ring or other structure.

[0057] In one embodiment, Figure 1 As shown, the drone also includes a locking element, which includes a fairing 60 or a projectile casing. Specifically, the drone utilizes a rocket fairing or artillery projectile casing, simplifying its structure. During the startup process, when the drone is launched or dropped into the ideal startup position—typically the highest or furthest point of the rocket or artillery trajectory—the fairing of the rocket or artillery projectile or the projectile casing automatically cracks and ejects. Subsequently, the drone's propeller blades 31, propelled by the elastic element, spring open and generate flight power as the rotating base 20 rotates.

[0058] In one embodiment, Figure 1-5 As shown, the wing module 50 includes two wing bags 51, which are connected to either side of the rear fuselage 40 and wrapped around it. The modular drone also includes an inflation source (not shown) connected to the two wing bags 51 for inflating them and deploying them. Specifically, the two wing bags 51 are retracted by being wrapped around the rear fuselage 40. During takeoff, the inflation source inflates the two wing bags 51, causing them to expand and expand. The deployed wing bags 51 provide balance and lift for the drone's flight.

[0059] In one embodiment, Figure 3 As shown, the wing bag 51 includes a bag cover 511 and a plastic winglet 512. The bag cover 511 is connected to the rear fuselage 40 and is configured to unfold when inflated. The plastic winglet 512 is attached to the bag cover 511. Specifically, the bag cover 511 has good flexibility and airtightness, and can form a wing structure through the inflated bag body. The plastic winglet 512 is a semi-rigid material with a certain degree of elasticity. The plastic winglet 512 can shape the bag cover 511 and prevent it from wrinkling when rolled up.

[0060] In this embodiment, the capsule 511 is made of glued woven fabric, which has good flexibility and airtightness; the semi-rigid plastic wing 512 is attached to the outside or inside of the capsule 511, and has a certain resilience, which helps the capsule 511 to unfold and forms the exoskeleton structure of the capsule 511. Since the capsule 511 is flexible, it unfolds slowly only by inflation. In this embodiment, by attaching the semi-rigid plastic wing 512 to the capsule 511, the unfolding speed of the wing bag 51 can be effectively accelerated, so that the UAV can quickly unfold and fly.

[0061] In this embodiment, Figure 3 As shown, a number of limiting tie bars 513 of different heights are provided between the wing pieces to strengthen the structure of the wing bag 51 and facilitate shaping of the wing bag 51 .

[0062] In this embodiment, Figure 3 As shown, the inflated wing bag 51 has a delta-wing configuration due to the shaping effect of the limiting tie rods 513. The inflated wing bag 51 has a smooth airfoil in longitudinal section, which is beneficial for flight aerodynamics and lift, while the cross section has a triangular shape with a high center and a low outside, which helps to enhance the wing load capacity.

[0063] In one embodiment, Figure 1-5 As shown, the modular drone also includes an antenna 70, which is hinged to the rear fuselage 40 and can compress the two wound wing bags 51 by rotating around the rear fuselage 40. Specifically, in addition to its communication function, the antenna 70 can also compress the two wound wing bags 51 to limit their position, ensuring that the wing bags 51 are stably wound around the rear fuselage 40. Therefore, the drone's own antenna 70 can lock the two wound wing bags 51, eliminating the need for additional locking mechanisms, thereby simplifying the drone's structure.

[0064] In this embodiment, when the wing bag 51 of the curled and tightened flexible wing loses the restraint of the whip antenna 70, it suddenly becomes loose and is pushed by the rebound stress of the semi-rigid plastic wing sheet 512 on its surface, and the wing bag 51 is expanded by the inflation of the inflation source.

[0065] In this embodiment, the antenna 70 is limited by the outer locking frame, and the locking frame can be any locking structure such as a solenoid valve that can lock the antenna 70. The locking frame locks the antenna 70 and then presses the wing bag 51. The wing bag 51 is in a tightened state. After the drone is ejected or projected, the locking frame unlocks the antenna, causing the antenna 70 to bounce off and break away from the pressure on the wing bag 51, causing the wing bag 51 to relax. After losing the restraint of the whip antenna 70, the wing bag 51 suddenly becomes loose, and is pushed by the rebound stress of the semi-rigid plastic wing sheet 512 on its surface and the inflation source to inflate the two wing bags 51, causing the two wing bags 51 to unfold.

[0066] In one embodiment, Figure 2-3 As shown, a limit slot 41 is provided at one end of the rear fuselage 40, away from the front fuselage 10. The limit slot 41 extends along the axial direction of the rear fuselage 40. The antenna 70 is hinged to the limit slot 41 and can be deployed by rotating around the rear fuselage 40. Specifically, the limit slot 41 limits the position of the antenna 70, so that the deployed antenna 70 extends along the axial direction of the rear fuselage 40, providing overall balance for the UAV during flight.

[0067] It can be understood that the antenna 70 can be bounced open by its own elastic force, or by the elastic force of the spring clip set between the antenna 70 and the rear fuselage 40. After being bounced open, the antenna 70 can be limited by the limiting groove 41 or the elastic force of the spring clip to remain level with the rear fuselage 40.

[0068] The specific working principle of the drone provided by the embodiment of the present invention is as follows: in the early stage of take-off, the drone realizes a static rod-like structure through the curling of its inflatable wing bag 51 and the folding of its blades 31. Before starting, the drone has a wingspan with no lateral space occupied, so that the drone can be adapted to be filled into tubular objects such as rocket launchers and artillery, and achieve a high-speed start by arrow shooting, artillery shooting or aircraft projection.

[0069] like Figure 4 As shown, when the UAV is firing the rocket 10a, the stick-shaped UAV is stored in the fairing 60 and mounted on the rocket 10a. After the rocket 10a is launched to start the UAV, when the UAV is launched or dropped to the ideal starting position (generally set at the highest point or farthest point of the trajectory of the rocket or artillery ammunition), the fairing 60 of the rocket or artillery ammunition or the projectile shell of the artillery ammunition automatically cracks and ejects the shell, and the blades 31 are deployed;

[0070] like Figure 5 As shown, when the drone is being dropped from the mother machine 20a, the mother machine 20a drops the drone in the drop compartment 21a during flight. When the drone falls to a certain height, the blades 31 unfold.

[0071] After the blades 31 are unfolded, they rotate under the drive of the power base 12, generating flight power to pull the UAV into flight. At the same time, the antenna 70 pops open and swings its head to maintain a level with the rear fuselage to balance the entire machine. When the wing bag 51 of the flexible wing in curling and tightening loses the restraint of the whip antenna 70, it suddenly loosens and is pushed by the rebound stress of the semi-rigid plastic wing sheet 512 on its surface, and the wing bag 51 is expanded under the inflation of the inflation source, so as to increase the lift and glide of the UAV. The structural settings such as the wing bag 51 can also reduce the weight of the UAV, simplify the structure of the UAV, and significantly increase the flight range and hovering time of the UAV, thereby ensuring that the UAV can perform its work tasks more punctually and stably. After entering the cruise flight state, the onboard computer formulates a flight plan according to the mission requirements and the current environment of the UAV, and decomposes and allocates tasks, and respectively activates the onboard auxiliary, reconnaissance and strike modules to perform battlefield reconnaissance, target following, long-range strikes or other preset tasks and temporary tasks.

[0072] The modular drone of this embodiment of the present invention, through its inflatable flexible wings that effectively curl and its propeller blades fold, achieves a practical static rod-like structure, with a wingspan that takes up no lateral space before launch. Combined with the flexible choice of mission module bays in the rear fuselage 40, it is particularly well-suited for insertion into tubular objects such as rocket launchers or artillery, enabling the immediacy of high-speed arrow and artillery launches on the battlefield. It is also easily suitable for overhead suspension or clustered delivery from fighter aircraft.

[0073] At the same time, the modular soft-wing UAV effectively cooperates with the battlefield launch and delivery of rocket launchers, artillery and fighter jets, and then through the traction flight of its own blades 31 and the lift-increasing gliding of the wing bags 51, it can significantly increase its flight range and hovering time, better perform battlefield tasks such as reconnaissance and electronic warfare, and can even directly attack or detonate to destroy high-value enemy targets.

[0074] The above description is only a preferred 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 any technician familiar with this technical field within the technical scope disclosed by the present invention should be covered by the scope of protection of the present invention.

Claims

1. A modular drone, characterized in that: include: front fuselage; A rotating base, sleeved on the front fuselage and rotatably connected to the front fuselage; a blade module, arranged in the circumferential direction of the rotating base, capable of being retracted from the rotating base and deployed during flight; a rear fuselage connected to the front fuselage and extending in the axial direction of the front fuselage; and a wing module connected to the rear fuselage and capable of being retracted therefrom and deployed during flight; The wing module includes two wing bags, which are respectively connected to the two sides of the rear fuselage and wrapped around the rear fuselage. The modular drone also includes an inflation source, which is connected to the two wing bags and is used to inflate the two wing bags so that the two wing bags are unfolded.

2. The modular drone according to claim 1, characterized in that: The blade module includes a plurality of blades and a plurality of elastic members. The blades are spaced apart in the circumferential direction of the rotating base and are hinged to the rotating base. The blades are retracted to the rotating base. One end of each elastic member is connected to the rotating base. The elastic members are used to drive the blades to unfold when the drone is flying.

3. The modular drone according to claim 2, characterized in that: The drone further comprises a locking element, which comprises a fairing or a projectile shell.

4. The modular drone according to any one of claims 1 to 3, characterized in that: The front fuselage includes a guide head, a power base and a tail connecting seat. The guide head, the power base and the tail connecting seat are connected in sequence. The rotating base is mounted on the power base and can be rotated by the drive of the power base. The rear fuselage is connected to the tail connecting seat.

5. The modular drone according to claim 4, characterized in that: The tail connecting seat is hinged to the power base, and the front fuselage further includes a steering drive module, which is installed on the tail connecting seat and is drivingly connected to the power base for driving the power base to rotate.

6. The modular drone according to claim 5, characterized in that: The steering drive module includes several traveling arms and several servos, and each of the traveling arms is arranged at intervals along the circumferential direction of the tail connecting seat. One end of each of the traveling arms is hinged to the power base, and each of the servos is installed inside the tail connecting seat and is respectively connected to the other end of each of the traveling arms.

7. The modular drone according to claim 1, wherein: The modular UAV further comprises an antenna, which is hinged to the rear fuselage and can compress the two wing bags in a rolled-up state by rotating around the rear fuselage.

8. The modular drone according to claim 7, characterized in that: A limiting slot is provided at one end of the rear fuselage away from the front fuselage, and the limiting slot extends along the axial direction of the rear fuselage. The antenna is hinged to the limiting slot and can be deployed by rotating around the rear fuselage.

9. The modular drone according to claim 1, wherein: The wing bag includes a bag casing, a plastic wing sheet and a limiting tie rod. The bag casing is connected to the rear fuselage and is used to be unfolded when inflated. The plastic wing sheet is attached to the bag casing.

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