Novel multipurpose unmanned aerial vehicle

Abstract

The novel multipurpose unmanned aerial vehicle comprises a fixed-wing aircraft body and a multifunctional task cabin, the aircraft body adopts a single-wing aerodynamic layout in a double-vertical-tail tail pipe, and a groove position with the center located at the gravity center is reserved in the bottom of a fuselage and used for containing the separable multifunctional task cabin. The main purpose is that the aircraft is combined with the task cabin, the task cabin is thrown to a designated place by utilizing the characteristic that the fixed wing is long in voyage, various tasks can be completed in a complex environment, an aircraft body is provided with a three-vector power system and has the vertical take-off and landing capacity, the aircraft body can take off and land on water, and the task cabin can be thrown to a designated water area and release a signal buoy. The aircraft dives below the water surface for exploration, is connected with the floating ticket through a communication cable, the buoy is connected with the control center in real time so as to control the task cabin, the buoy can be recycled and floats above the water surface to be in butt joint with the aircraft body after a task is finished, and the aircraft can be conveniently used for detecting the bottoms of water areas such as shallow sea areas and reservoirs.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle applications, and in particular to the structure, functions and application scenarios of a novel multi-purpose unmanned aerial vehicle. Background Art

[0002] In the field of drones, the most widely used types are multi-rotor drones and vertical take-off and landing drones. At present, the technology of multi-rotor drones is very mature, and the flight safety is very reliable. Its advantage is that it can take off and land vertically stably, and can carry various equipment to complete various tasks. Since the flight principle relies on the motor driving force to directly overcome gravity, its endurance and range are very short, and its load capacity is also small. The emergence of vertical take-off and landing fixed-wing drones makes up for its short range. Its function is to carry various equipment in the air to complete mapping, reconnaissance and other tasks.

[0003] The existing vertical take-off and landing UAVs still have the following deficiencies when in use. The specific problems are as follows:

[0004] 1. Existing vertical take-off and landing drones are generally large in size. When flying in a small space, they are prone to ground effect and eddy currents that affect flight stability. Therefore, they are not suitable for operations in small spaces and complex terrains.

[0005] 2. The general structure of existing vertical take-off and landing UAVs is to add four rotors on the basis of fixed-wing aircraft, which is equivalent to the combination of a quadcopter and a fixed-wing UAV. Multiple power systems make the fuselage very heavy, and the energy consumption for take-off and landing is huge, which seriously affects the endurance.

[0006] 3. Existing vertical take-off and landing drones do not have amphibious operation capabilities

[0007] 4. Existing unmanned detection equipment does not yet have the ability to conduct remote diving operations Summary of the invention

[0008] (1) Technical issues to be solved

[0009] In view of the shortcomings of the prior art, the present invention provides a new type of multi-purpose UAV structure, functions and application scenarios, which solves the problem that most existing UAVs do not have the ability to operate in complex scenarios and amphibious operations, and breaks through the remote control diving detection function, thereby making the application field of UAVs more extensive.

[0010] (2) Technical solution

[0011] In order to achieve the above purpose, the technical solution adopted by the present invention is: a new type of multi-purpose UAV, including an aircraft body and a multi-functional mission cabin. The structure of the aircraft body is based on the existing tilt-rotor vertical take-off and landing aircraft structure, with the power system improved and the floating landing gear and the multi-functional mission cabin separation and docking device installed. It is characterized by long range, large load capacity, and vertical take-off and landing function. The multi-functional mission cabin has a streamlined shell as the main body, equipped with a retractable vector ducted main power device, a vector underwater propulsion device, a sealed cabin for controlling diving and surfacing, an automatically retractable quadcopter power device, an underwater communication device, and various detection equipment. It has air, land, surface, and underwater detection capabilities and can fly at low altitude for a short time. The combination of the functions of the two can realize all-weather long-distance and complex environment operations.

[0012] As a preferred embodiment of a novel multi-purpose UAV of the present invention, the aircraft body includes a fixed-wing aircraft with a single-wing aerodynamic layout in a double vertical tail tail tube, and the tail tube extends forward for a certain distance and is equipped with a vector tilt-rotor power at the front end, wherein the vector tilt-rotor power is a power motor fixed to a concave bracket, and the steering gear shaft is connected to the concave bracket to control the tilt angle of the motor. A tiltable electric ducted power is installed at the tail of the aircraft fuselage, wherein the electric ducted power is a ducted propeller fixed to the shaft of the steering gear through a ducted fixed bracket, and the tilt of the ducted propeller is controlled by the steering gear to provide horizontal and vertical thrust. A portion of the bottom of the fuselage is hollowed out to leave a position for placing a multifunctional mission cabin, and a separation docking device is installed at the position where the mission cabin is placed. A pontoon landing gear is installed below the tail tube on the wing, and the pontoon material is EPO foam, and landing gear wheels are installed at the bottom of the pontoon. The top of the pontoon is fixedly connected to the lower surface of the aircraft wing through a fixed bracket, so that the aircraft has the ability to take off and land on water and land.

[0013] As a preferred embodiment of a new type of multi-purpose UAV of the present invention, the retractable vector ducted main power device includes an electric ducted propeller, a hydraulic telescopic rod, a worm gear, and a steering servo. The nozzle housing of the electric ducted propeller is fixed to the central axis in the main support rod. A steering servo is fixed on the main support rod, and the central axis in the main support rod is connected by a pull rod to control the tilt of the ducted propeller, providing multi-angle thrust to control the forward, backward and steering of the mission cabin. The main support rod is hinged to one end of the hydraulic telescopic rod, and the other end of the hydraulic telescopic rod is hinged to the slide groove of the worm gear. When the hydraulic telescopic rod contracts and the worm gear slide groove moves backward, the entire ducted power device is retracted into the cabin. When the hydraulic telescopic rod is extended and the worm gear slide groove moves forward, the entire ducted power device is unfolded outside the cabin.

[0014] As a preferred embodiment of a new type of multi-purpose UAV of the present invention, the underwater propulsion device includes an underwater propeller and a steering servo. The underwater propeller is installed on both sides of the tail of the mission cabin. The underwater propeller is directly fixed to the servo rocker arm. The tilting of the servo rocker arm directly drives the tilting of the underwater propeller, so that the mission cabin can provide underwater power and steering force when it is in a diving state.

[0015] As a preferred embodiment of a new type of multi-purpose UAV of the present invention, the drainage cabin for controlling diving and floating includes a sealed cabin and a water pump. The water pump is installed in the sealed cabin. When the water pump is turned to fill water into the sealed cabin, water enters the sealed cabin, increasing the total mass of the mission cabin. When the gravity of the mission cabin is greater than the buoyancy, it starts to dive. When it dives to a specified depth, the water pump reverses to discharge a certain amount of water so that the gravity of the mission cabin is equal to the buoyancy. When the mission cabin is about to float to the water surface, the water pump reverses to empty the water in the sealed cabin and floats.

[0016] As a preferred embodiment of a new type of multi-purpose UAV of the present invention, the foldable four-axis power system includes a long screw, a screw-driven motor, and four motor arms. The middle of the motor arm is hinged to one end of a pull rod, and the other end of the pull rod is hinged to a threaded buckle on the long screw. When the motor drives the threaded rod to rotate, the threaded buckle moves to cause the four arms to unfold to a flight state. The entire device is installed at the bottom of the mission cabin and becomes a conventional four-axis UAV after unfolding.

[0017] As a preferred mode of a new type of multi-purpose UAV of the present invention, the underwater communication device includes a communication cable composed of a remote control receiver antenna, an open source flight control data transmission antenna, an image transmission antenna, and a GPS connection line, a cable reel, a 360-degree steering gear, and a float. The end of the communication cable is the high-frequency head of all antennas, which is fixed to the top of the float. The cable is wound on the cable reel. The side of the cable reel is fixed to the 360-degree steering gear rocker arm, so that the steering gear controls the cable reel to rotate and release and recycle the cable. When the mission cabin dives below the water surface, the cable reel automatically rotates to release the cable, so that the float will always float above the water surface and maintain a real-time connection with the signal transmitting end.

[0018] (3) Beneficial effects

[0019] In summary, the present invention has the following beneficial effects:

[0020] 1. The structural features of the new multi-purpose UAV aircraft body are based on a fixed-wing aircraft with a single-wing aerodynamic layout in a double vertical tail tube. The tail tube extends forward for a certain distance and a vector motor seat and a motor are installed at the front end to form a vector power system. A tiltable electric ducted power is installed at the tail of the aircraft fuselage. The vector power system can change the motor angle and tilt the rotor to switch between horizontal and vertical power. Only three sets of power can achieve vertical take-off and landing. The existing common vertical take-off and landing UAVs are usually based on fixed-wing aircraft directly equipped with a set of quadcopter power systems. The various power systems make their take-off and landing energy consumption high, and the aircraft is heavy. The structure of this three-axis vector aircraft perfectly solves this problem, and the flight reliability is also high with the open source flight control. Waypoint tasks can be written to enable it to complete tasks automatically.

[0021] 2. The structure of the underwater communication device controls the release and recovery of the communication cable through the float and the reel, so that the antenna of the diving mission cabin can always float above the water surface, solving the problem that electromagnetic wave signals cannot propagate across media, and enabling the mission cabin to maintain real-time contact with the control end underwater.

[0022] 3. The structure of the foldable four-axis power system is composed of a long screw, a screw-driven motor, and four motor arms. The middle of the motor arm is hinged to one end of the pull rod, and the other end of the pull rod is hinged to the threaded buckle on the long screw. When the motor drives the threaded rod to rotate, the threaded buckle moves to cause the four arms to unfold to the flight state. The entire device is installed on the bottom of the mission cabin and becomes a conventional four-axis drone after unfolding. When the mission cabin encounters a huge obstacle and cannot pass through it when operating in the designated area, the mission cabin automatically unfolds its arms and becomes a four-axis drone to fly over the obstacle. Or when the mission cabin's posture is overturned due to external factors, the arms can be unfolded and the motor on one side can be controlled to reverse to correct it, so that the mission cabin has the ability to operate in various complex terrains.

[0023] 4. The structure of the underwater thruster is that the underwater thrusters are installed on both sides of the tail of the mission module. The underwater thrusters are directly fixed to the servo rocker arm. The tilting of the servo rocker arm directly drives the tilting of the underwater thruster, so that the mission module can provide underwater power and steering force when it is in a diving state, so that the mission module can remain stable in a diving state. The two vector-tilting underwater thrusters make the mission module have good controllability underwater.

[0024] 5. Brand-new UAV operation process and application field. This new multi-purpose fixed-wing UAV has all the advantages and characteristics of vertical take-off and landing fixed-wing. At the same time, its detachable multi-functional mission cabin can be deployed in complex environments for mapping or reconnaissance tasks. After the mission is completed, it can move to a relatively open area to dock with the aircraft body for recovery and return. It also has amphibious operation capabilities. The aircraft body can take off and land on water. The multi-functional mission cabin can be deployed to designated waters, release signal floats, dive below the water surface for exploration, and connect to the float through communication cables. The float is connected to the control center in real time to control the multi-functional mission cabin. After the mission is completed, the float can be recovered and floated above the water surface to dock with the aircraft body. It can be conveniently used to detect the bottom of shallow sea areas, reservoirs and other waters. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 : The three-dimensional structure diagram of the aircraft body, of which 1A is a three-dimensional diagram and 1B is an exploded diagram

[0026] Figure 2 : Three-dimensional structure diagram of vector tilt-rotor power unit

[0027] Figure 3 :Three-dimensional structure diagram of vector tilt-ducted power unit

[0028] Figure 4 : 3D structural diagram of pontoon landing gear

[0029] Figure 5 : Three views of the aircraft structure, 5A is the top view, 5B is the left view, and 5C is the main view

[0030] Figure 6 :Three views of the vector motor tilt-rotor power unit structure, of which 6A is the top view, 6B is the main view, and 6C is the left view

[0031] Figure 7 :Multiple views of the vector tilt duct power unit structure. 7A is the top view, 7B is the bottom view, 7C is the main view, 7D is the left view, and 7E is the rear view

[0032] Figure 8 : The three-dimensional structure diagram of the mission module, of which 8A is the front three-dimensional diagram, 8B is the rear three-dimensional diagram, and 8C is the exploded diagram

[0033] Fig. 9 : Structural diagram of underwater cross-medium communication device, where 9A is a stereogram, 9B is a left view, 9C is a top view, and 9D is a main view

[0034] Fig.10 : A three-dimensional structural diagram of a retractable tilting ducted power unit (in unfolded state), 10A is a front three-dimensional diagram, 10B is a rear three-dimensional diagram

[0035] Fig.11 :3D structure diagram of foldable four-axis machine arm device (unfolded state)

[0036] Fig.12 :Diving drainage tank device three-dimensional structure diagram

[0037] Fig.13 :3D structure diagram of underwater propulsion device

[0038] Fig.14 : A three-dimensional structural diagram of a retractable tilting ducted power unit (retracted state), wherein 14A is a front three-dimensional diagram and 14B is a rear three-dimensional diagram

[0039] Fig.15 : A three-dimensional structural diagram of a foldable four-axis machine arm device (retracted state), wherein 15A is a front three-dimensional diagram and 15B is a top three-dimensional diagram

[0040] Fig.16 : Three views of the retractable tilting ducted power unit (expanded and retracted), where 16A, 16B, and 16C are the left view, front view, and top view of the expanded state, respectively, and 16D, 16E, and 16F are the left view, front view, and top view of the retracted state, respectively

[0041] Fig.17 : Three views of the underwater propulsion device, 17A is the main view, 17B is the top view, 17C is the right view, 17D is the rear view, and 17E is the left view

[0042] Fig.18 :Three views of the foldable four-axis machine arm device (expanded and retracted), where the expanded state 18A is the top view, 18B is the right view, 18C is the main view, 18E is the left view, and the retracted state 18D is the top view and 18F is the main view

[0043] Fig.19 : A three-dimensional structural diagram of the aircraft body and the mission cabin in docking state

[0044] In the figure:

[0045] 02. Aircraft rudder; 03. Aircraft elevator; 04. Aircraft aileron; 05. Aircraft vertical tail tail pipe; 07. Carbon fiber tube extending forward from the vertical tail tail pipe; 08. Aircraft electric ducted propeller; 10. Dual-axis servo; 09. Fixed bracket; 11. Power motor; 12. Dual-axis servo; 13. Fixed bracket; 14. Propeller; 15 Cable drum; 16. Servo; 17. Float; 18. Communication cable; 19. Quadcopter drone arm; 21. Long threaded rod (half forward thread, half reverse thread); 22. Screw 1. Buckle (one forward threaded nut and one reverse threaded nut); 20. Pull rod; 23. Long screw drive motor; 24. Propeller; 25. Four-axis arm deployment structure support seat; 26. Ducted propeller; 27. Servo; 28. Ducted main support rod; 29. ​​Hydraulic telescopic rod; 32. Screw; 30. Screw drive motor; 31. Slide block; 33. Submarine sealed cabin; 34. Water pump; 35. Underwater propeller; 36. Servo; 38. Foam buoy; 39. Aircraft landing gear; 37. Fixed bracket; 40. Aircraft front landing gear DETAILED DESCRIPTION

[0046] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0047] like Figure 1 , 2 , 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, the present invention provides a technical solution: a novel multi-purpose unmanned aerial vehicle structure and function and application scenario, including the structure of the aircraft body as shown Figure 1 The tilting motor structure 101 is as follows: Figure 2 The servo steering engine 12 is connected to the control motor 11 through the concave bracket 13, which can tilt 90 degrees forward and 20 degrees backward, and can provide horizontal forward and vertical upward pulling forces and oblique upward and oblique backward pulling forces. The device 101 is respectively fixed to the front end of the carbon fiber tube 07 extending forward from the tail tube of the vertical tail of the aircraft, one on each side of the left and right wings, and generates anti-torque through the tilt motor angle and motor speed difference to maintain the balance of the vertical take-off and landing mode, in which the two sets of 101 rotor power steering on the left and right wings are opposite. The tiltable ducted power structure 102 is as follows Figure 3, the servo servo 10 is connected to the ducted propeller 08 through the fixed bracket 09, and the servo can control the ducted propeller to tilt upward and backward 90 degrees, providing horizontal forward and vertical upward thrust. The ducted power 102 and the two rotor powers 101 constitute a three-axis vector power system, which can make the aircraft hover in the air. When the aircraft is in fixed-wing mode and flies horizontally, the directions of the two motors and the ducted power are both horizontal, and the thrust angle does not change to provide horizontal forward power, and the flight attitude is controlled by the rudder. The distribution of the rudder surface 05 is the aileron, 02 is the rudder, and 03 is the elevator. All of its rudder surfaces are controlled by 5 standard servos. 38 is an aircraft float, made of EPO foam, and the bottom of the float is the aircraft landing gear wheel 39, and 40 is the aircraft front landing gear, which constitutes a front three-point landing gear on land. The float is rigidly connected to the lower surface of the wing through the fixed bracket 37, which can realize taxiing takeoff and landing on land or water. The center of gravity of the aircraft is located in the center of the slot where the mission module is placed. Changing the weight of the mission module will not affect the center of gravity of the aircraft and thus affect the flight.

[0048] Mission module structure Figure 8 , Fig. 9 It is a mission module diving communication device 201. Since electromagnetic signals cannot be relayed across media, this device can keep the communication antenna always on the water surface and maintain real-time contact with the control center. This device consists of a float 17, a communication cable 18, a reel 15, and a 360-degree servo 16. One side of the reel is connected to the circular rocker arm of the servo so that it can drive the reel to rotate to control the recovery and release of the cable. One end of the cable and the GPS module are fixed on the top of the float, and the other end of the cable is connected to the mission module electronic system. The cable is composed of a receiver antenna, an open source flight control data transmission antenna, an image transmission antenna, and a GPS connecting line. When the mission module dives below the water surface, the cable reel automatically rotates to release the cable, so that the float will always float above the water surface and maintain real-time connection with the signal transmitter. The cable length is about 50 meters, which can be conveniently used to detect the bottom of shallow sea areas, reservoirs and other waters.

[0049] The power on land and water is provided by the electric duct at the tail, and the retractable tilting duct structure 202 is as shown in FIG. Fig.10 The nozzle shell of the electric ducted propeller 26 is fixed to the central axis in the main support rod 28. A steering servo 27 is fixed on the main support rod, which is connected to the central axis in the main support rod through a pull rod to control the tilt of the ducted propeller and provide multi-angle thrust to control the forward, backward and steering of the mission cabin. The main support rod is hinged to one end of the hydraulic telescopic rod 29, and the other end of the hydraulic telescopic rod is hinged to the slide block 31 of the screw 32. When the screw drive motor 30 drives the screw 32 to rotate, the slide block 31 moves forward and backward. When the hydraulic telescopic rod contracts and the worm slide block moves backward, the entire ducted power device is recovered into the cabin. When the hydraulic telescopic rod is extended and the worm slide block moves forward, the entire ducted power device is unfolded outside the cabin. Its unfolded state is as shown in FIG. Fig.10 , the recycling status is as follows Fig.14 The front of the mission cabin is a free area where different equipment can be placed according to different mission requirements.

[0050] The bottom of the mission cabin is equipped with a quadcopter UAV power unit, the structure is as follows: Fig.11 , generally in a recovery state, the expansion and recovery of the machine arm 19 is controlled by a long screw rod 21, the threaded buckle 22 on the long screw rod 21 is hingedly connected to the connecting rod 20, the connecting rod 20 is hingedly connected to the machine arm 19, the center of the threaded rod is fixed to the fixed base 25 by a bearing, and one end is a motor 23 to drive the threaded rod to rotate. Half of the long threaded rod is a forward thread and the other half is a reverse thread. When the threaded rod rotates, the front and rear threaded buckles will move in opposite directions, and the four machine arms are driven to expand and recover through the rod. Its expansion state is as follows Fig.11 , the recycling status is as follows Fig.15 When the mission cabin encounters a large height difference in complex terrain and cannot move forward, the aircraft arms can be deployed to fly over the obstacle in a short time. The flight principle is the same as that of a quadcopter.

[0051] Mission cabin diving drainage cabin structure 204 Fig.12 The inside of the sealed cabin 33 is connected to one water outlet of the water pump 34, and the other water outlet of the water pump is connected to the outside of the mission cabin. The mission cabin needs to be counterweighted so that when the sealed cabin 33 is in a half-water state, the total mass of the mission cabin is equal to the buoyancy of the mission cabin when it is fully submerged. When the mission cabin needs to dive on the water, the water pump is turned forward to fill the sealed cabin with water to increase the total mass. The mission cabin dives. When it dives to the specified depth, the water pump is reversed to empty the water to half so that the total mass of the mission cabin is equal to the buoyancy of the mission cabin. When the mission is completed, the water pump reverses to empty the water in the sealed cabin and the mission cabin surfaces.

[0052] The underwater propeller structure 205 is as follows Fig.13 The side of the underwater thruster 35 is fixed to the rotating shaft of the steering servo 36 to control the tilt of the thruster. The device is fixed in the center of the two sides of the tail of the mission cabin. When the mission cabin is in the diving state, the two underwater thrusters control the movement posture of the mission cabin underwater through tilt and speed difference.

[0053] This new multi-purpose fixed-wing UAV test machine is made of wood frame and KT plate. In the later development, it can be made of fiberglass composite material and carbon fiber frame. The aerodynamic performance of the aircraft body is very excellent in the test flight, and the low-speed performance is very good. The aircraft body and the multi-functional mission cabin are independent units, and all functions are clearly divided and cooperate with each other without affecting each other. Both the aircraft body and the multi-functional mission cabin use open source flight control. You can complete the mission process by writing and setting waypoint tasks, without real-time human control. You only need to observe the returned flight parameters to ensure flight safety.

[0054] This specific embodiment is merely an explanation of the present invention and is not a limitation of the present invention. After reading this specification, those skilled in the art may make non-creative modifications to the present embodiment as needed. However, as long as they are within the scope of the claims of the present invention, they are protected by the patent law.

Claims

1. A new type of multi-purpose UAV, characterized by: The invention comprises an aircraft body and a mission cabin body structure arranged below the aircraft body, wherein the mission cabin body structure is provided with underwater propulsion devices (205) on both sides of the tail, a retractable tilt-ducted power device (202) is arranged above the tail of the mission cabin, an underwater cross-medium communication device (201) is arranged inside the center of the mission cabin body, a mission cabin flight mode four-axis arm deployment device (203) is arranged on the entire bottom surface of the mission cabin, and a diving drainage tank device (204) is arranged in front of the mission cabin underwater cross-medium communication device (201). The aircraft body comprises a pontoon landing gear (103) arranged below the wing, and a vector tilt-ducted power device (102) is arranged at the tail of the aircraft fuselage.

2. A novel multi-purpose UAV according to claim 1, characterized in that: The mission cabin underwater cross-medium communication device (201) comprises a 360-degree steering gear (16), a cable drum (15), a communication cable (18) and a buoy (17); the rotating shaft of the 360-degree steering gear (16) is connected to the cable drum (15); one end of the communication cable (18) is connected to an electronic control device in the mission cabin, and the other end is fixed to the top of the buoy (17); the communication cable (18) is wound around the cable drum (15); the rotation of the cable drum (15) is controlled by the 360-degree steering gear (16) to realize the release and recovery of the communication cable (18).

3. A novel multi-purpose UAV according to claim 1, characterized in that: The mission cabin retractable tilting ducted power device (202) comprises an electric ducted propeller (26), a main support rod (28), a steering servo (27), a hydraulic telescopic rod (29), a screw (32), a slide block (31) and a screw drive motor (30). The nozzle shell of the electric ducted propeller (26) is fixed to the central axis in the main support rod (28), the steering servo (27) is fixed to the main support rod (28), and the central axis in the main support rod (28) is connected by a pull rod to control the ducted propulsion. The main support rod (28) is hingedly connected to one end of the hydraulic telescopic rod (29) to rotate, and the other end of the hydraulic telescopic rod (29) is hingedly connected to the slide block (31) of the screw rod (32). The screw drive motor (30) drives the screw rod (32) to rotate, so that the slide block (31) moves forward and backward. When the hydraulic telescopic rod (29) contracts and the slide block (31) moves backward, the ducted power device is recovered into the cabin. When the hydraulic telescopic rod (29) extends and the slide block (31) moves forward, the ducted power device is deployed outside the cabin.

4. A novel multi-purpose UAV according to claim 1, characterized in that: The mission cabin flight mode four-axis arm deployment device (203) comprises a long screw (21), a threaded buckle (22), a connecting rod (20), an unmanned aerial vehicle arm (19), a fixed base (25) and a motor (23). The center of the long screw (21) is fixed to the fixed base (25) by a bearing, one end of the long screw (21) is driven by the motor (23), half of the long screw (21) is a forward thread and the other half is a reverse thread, the threaded buckle (22) is hingedly connected to the connecting rod (20), and the connecting rod (20) is hingedly connected to the unmanned aerial vehicle arm (19). When the long screw (21) rotates, the front and rear threaded buckles (22) move in opposite directions, and drive the four unmanned aerial vehicle arms (19) to be deployed and recovered through the connecting rod (20).

5. A novel multi-purpose UAV according to claim 1, characterized in that: The mission cabin diving and drainage cabin device (204) comprises a sealed cabin (33) and a water pump (34); the interior of the sealed cabin (33) is connected to a water outlet of the water pump (34); the other water outlet of the water pump (34) is communicated with the exterior of the mission cabin; the amount of water in the sealed cabin (33) is controlled by the forward and reverse rotation of the water pump (34) to achieve diving and surfacing of the mission cabin.

6. A novel multi-purpose UAV according to claim 1, characterized in that: The mission cabin underwater propeller device (205) comprises an underwater propeller (35) and a steering gear (36). The side of the underwater propeller (35) is fixed to the rotating shaft of the steering gear (36). The steering gear (36) controls the tilting of the underwater propeller (35) to provide underwater power and steering force.

7. A novel multi-purpose UAV according to claim 1, characterized in that: The buoy landing gear (103) comprises a buoy (38), a landing gear wheel (39) and a fixed bracket (37); the buoy (38) is made of EPO foam, the bottom of the buoy (38) is provided with a landing gear wheel (39), and the top of the buoy (38) is fixedly connected to the lower surface of the aircraft wing via the fixed bracket (37).

8. The novel multi-purpose UAV according to claim 1 is characterized by: The vector tilt duct power (102) comprises a ducted propeller (08), a steering gear (10) and a ducted fixed bracket (09); the ducted propeller (08) is fixed to the rotating shaft of the steering gear (10) via the ducted fixed bracket (09); the tilt of the ducted propeller (08) is controlled by the steering gear (10) to provide thrust in the horizontal and vertical directions.

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