A rocket-boosted rotorcraft drone

Abstract

The utility model provides a rocket boost's rotor unmanned plane, including the detachable connection of upper and lower rotor unmanned plane and rocket boost device, rotor unmanned plane includes cylindrical machine body, bullet and a plurality of wings, and the middle part of wing is connected on the machine body through the hinge mode, the inside setting of machine body elevating gear, elevating gear hinge wing upper end, and the lower end of wing sets up propeller, rocket boost device, lower end sets up booster, and the upper end sets up and holds the groove, holds the groove and sets up remote control plug bolt device, the fixed ring of machine body bottom corresponding remote control plug bolt device position setting, the utility model has the advantages of: through the rocket boost device has provided the strong initial thrust and high -speed flight ability, makes unmanned plane to be able to quickly, long -distance reach target area, has overcome the fatal weak point of traditional multi rotor unmanned plane slow speed, short voyage.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a rocket-assisted rotary-wing UAV. Background Technology

[0002] Rotary-wing unmanned aerial vehicles (UAVs), especially multi-rotor types, are playing an increasingly important role in modern civilian and military fields due to their core capabilities of vertical takeoff and landing and hovering. They are no longer dependent on runways, enabling them to take off and land flexibly in complex terrain, urban environments, and even the confined space of ship decks, exhibiting excellent low-speed maneuverability and flight stability. These characteristics give them irreplaceable advantages in diverse missions such as aerial photography, geographic mapping, infrastructure inspection, precision agriculture spraying, logistics delivery, security monitoring, and disaster emergency reconnaissance, making them a key force driving the development of the low-altitude economy.

[0003] However, traditional rotary-wing UAVs, especially the widely used electric multi-rotor platforms, have always faced two significant inherent performance bottlenecks: slow flight speed and short effective range. Their cruising speed is typically limited to a low level, and the continuous operational time of a single flight is mostly confined to the range of 20-45 minutes, significantly affected by battery capacity and flight conditions. The root cause of this limitation lies primarily in their low aerodynamic efficiency: while generating lift, the rotor also produces enormous induced drag and shape drag. When attempting high-speed forward flight, drag increases dramatically, leading to a surge in energy consumption. Simultaneously, the limited energy density of their power sources, coupled with the UAV's inherently limited payload capacity, severely restricts their ability to carry more energy. These characteristics of low speed and short range fundamentally limit the boundaries of their operational capabilities. Because of the short range of UAVs, operators on the battlefield need to infiltrate near targets, thus introducing significant risks.

[0004] The limitations of rotary-wing drones in terms of speed and range lead to a series of significant adverse effects in practical applications. Operational efficiency is severely constrained; when performing long-distance patrols or large-scale monitoring missions, frequent returns to the take-off and landing points for battery replacements or multiple deployments are required, significantly extending mission cycles and increasing manpower and time costs. In scenarios with high timeliness requirements, such as disaster emergency response, rapid reconnaissance of sudden events, or emergency medical supply delivery, slow flight speeds may result in missed critical intervention windows or delayed intelligence gathering. Limited single-flight distance severely compresses the effective operating radius of drones, making it difficult to detect, monitor, or operate target areas far from control stations or take-off and landing points, especially in the absence of mid-course resupply points. To overcome range limitations and cover larger areas, it is often necessary to deploy more drones or build a dense ground relay network, which not only significantly increases the overall complexity of the system but also substantially drives up the total cost of acquisition and operation. Utility Model Content

[0005] To address the current problems of slow flight speed and short effective range of rotary-wing drones; This utility model provides a rocket-assisted rotary-wing drone, including a rotary-wing drone and a rocket booster device that can be detachably connected. The rotary-wing drone includes a cylindrical fuselage, a warhead mounted on the top of the fuselage to reduce wind resistance, and multiple wings evenly distributed around the side walls of the fuselage. The wings are connected to the fuselage by a hinge in the middle. A lifting device is installed inside the fuselage, which is hinged to the upper end of the wing. A propeller is installed at the lower end of the wing. The lifting device drives the wing to unfold from a drooping state to a horizontal state. The rocket booster has a booster at the lower end and a receiving groove at the upper end. A remote control plug device is installed in the receiving groove. A fixing ring is installed at the bottom of the body corresponding to the position of the remote control plug device. The remote control plug extends out and is inserted into the fixing ring to lock the rotor drone and the rocket booster.

[0006] As a preferred embodiment, the lifting device includes a first motor that is vertically fixedly installed. The output shaft of the first motor is fixedly connected to a lead screw. The outer side of the lead screw is threadedly connected to a lifting plate. The lifting plate is hinged with multiple connecting parts. The outer ends of the connecting parts are hinged to the upper end of the wing. The first motor drives the lead screw to rotate, causing the lifting plate to descend and pulling the wing to a horizontal state through the lever principle.

[0007] As a preferred embodiment, the remote-controlled plug device includes a pair of racks arranged opposite each other with their tooth surfaces facing inward. A gear meshes between the two racks, and the gear is sleeved and fixed on the output shaft of a vertically arranged second motor. The side wall of the receiving groove has an extension hole corresponding to the position of the rack. The second motor drives the gear to move the racks horizontally in opposite directions synchronously, so that they extend out of the extension hole and are inserted into the fixing ring.

[0008] As a preferred embodiment, the first motor integrates a satellite communication module, which can receive remote control commands to start or stop operation.

[0009] As a preferred embodiment, the second motor integrates a satellite communication module, which can receive remote control commands to start or stop operation, thereby controlling the extension or retraction of the plug.

[0010] As a preferred embodiment, a stop is fixedly provided at the bottom end of the lead screw to limit the lower limit of the travel of the lifting plate and prevent it from accidentally falling off the lead screw.

[0011] As a preferred embodiment, the number of wings is three to six; each propeller is driven by an independent third motor; the third motor integrates a satellite communication module, which can receive remote control commands to control the operation of the propeller.

[0012] As a preferred embodiment, the fuselage has an opening at the position corresponding to the wing, and a pin is fixedly installed in the opening. The wing has a through hole in the middle, and the pin passes through the through hole, allowing the wing to rotate around the pin.

[0013] As a preferred embodiment, the tail section of the aircraft is provided with multiple tail skirts.

[0014] The beneficial effects of this utility model are as follows: 1. This invention provides powerful initial thrust and high-speed flight capability through a rocket booster device, enabling the UAV to quickly and over long distances reach the target area, overcoming the fatal weaknesses of traditional multi-rotor UAVs, such as slow speed and short range. Upon reaching the target area, the rotorcraft separates and deploys its wings, utilizing its multi-wing system to achieve vertical takeoff and landing, precise hovering, low-speed maneuvering, and precision operations. This invention can be widely applied in battlefield rescue and medical care; for example, it can deliver antivenom over long distances to someone bitten by a snake outdoors, and it can also significantly increase the operator's operating distance, effectively protecting the operator.

[0015] 2. The lifting device of this utility model utilizes the lever principle. Driven by a single central motor, the lead screw rotates, causing the lifting plate to descend. This synchronously, stably, and reliably pulls all the wings precisely from a drooping, compact state to a horizontal, deployed working state. The structure is relatively simple, with high transmission efficiency and good consistency of action. The stop at the bottom of the lead screw acts as a mechanical limit, effectively preventing excessive descent of the lifting plate that could lead to mechanism failure or jamming, ensuring the safety and reliability of the deployment operation.

[0016] 3. This utility model integrates a second motor for satellite communication into the remote-controlled plug device, enabling ground operators to remotely issue commands from any location and time globally to precisely control the plug retraction, achieving safe, reliable, and on-demand separation of the rotorcraft UAV from the rocket booster. It can also be used in conjunction with my previously developed marine rocket recovery device (patent number: CN201610142291.7), significantly reducing the device's operating costs. Attached Figure Description

[0017] To make the content of this utility model easier to understand, the present utility model will be further described in detail below with reference to specific embodiments and accompanying drawings, wherein... Figure 1 This is a schematic diagram of the structure of this utility model; Figure 2 This is a schematic diagram of the structure of the present invention in its unfolded state; Figure 3 for Figure 1 A partial schematic diagram of point A in the middle; Figure 4This is a schematic diagram of the remote-controlled plug device of this utility model; Figure 5 This is a schematic diagram of the structure of this utility model after it is divided into parts.

[0018] Numbering on the map: 1. Rotary-wing UAV; 11. Airframe; 12. Warhead; 13. Wing; 14. Propeller; 15. Fixing ring; 16. Pin; 2. Rocket booster; 21. Booster; 22. Tail skirt; 3. Lifting device; 31. First motor; 32. Lead screw; 33. Lifting plate; 34. Connector; 35. Stop; 4. Remote control plug device; 41. Rack; 42. Gear; 43. Second motor. Detailed Implementation

[0019] To illustrate the features of this utility model, the following description, in conjunction with the accompanying drawings and embodiments, will further explain this utility model.

[0020] Example: Please refer to the following: Figures 1 to 5 This embodiment provides a rocket-assisted rotary-wing unmanned aerial vehicle (UAV). The UAV mainly consists of two parts: a rotary-wing UAV 1 and a rocket booster 2. The two parts are detachably connected via a specific locking mechanism.

[0021] The core component of the rotary-wing UAV 1 is a cylindrical fuselage 11. A streamlined warhead 12 is fixedly mounted at the top of the fuselage 11 to significantly reduce air resistance during high-speed flight. Four wings 13 are evenly distributed along the circumference of the sidewalls of the fuselage 11. The middle of each wing 13 is connected to the fuselage 11 by a hinge. Specifically, mounting holes are provided on the sidewalls of the fuselage 11 corresponding to the positions of each wing 13, and horizontal pins 16 are fixedly mounted in the holes. A through hole is provided in the middle of the wing 13, which fits onto the pin 16, allowing the wing 13 to rotate around the pin 16. Multiple tail skirts 22 are usually installed on the outer tail of the fuselage 11 to enhance flight stability.

[0022] Each wing 13 is fitted with a propeller 14 at its lower end. Each propeller 14 is driven by an independent third motor with an integrated satellite communication module, which can receive remote commands to control its operation. The upper ends of the wings 13 are hinged together via connectors 34.

[0023] A lifting device 3 is fixedly installed in the center of the fuselage 11. The lifting device 3 includes a vertically fixed first motor 31. The output shaft of the first motor 31 faces downward and is fixedly connected to a vertical lead screw 32. A stop block 35 is fixedly installed at the bottom end of the lead screw 32. A lifting plate 33 is threadedly connected to the lead screw 32. The lifting plate 33 is located in the upper middle part of the lead screw 32 and is hinged to the upper end of each wing 13 through the aforementioned connecting piece 34. The first motor 31 also integrates a satellite communication module, which can receive remote commands to start or stop operation. When the first motor 31 drives the lead screw 32 to rotate, the lifting plate 33 moves downward along the lead screw 32. Since the middle part of the wing 13 is hinged to the pin 16, the downward movement of the lifting plate 33 pulls the upper end of the wing 13 through the connecting piece 34. Using the lever principle, the wing 13 is gradually unfolded from a drooping state close to the side wall of the fuselage 11 to a horizontal working state. The function of the stop block 35 is to limit the downward position of the lifting plate 33 and prevent it from accidentally falling off the lead screw 32.

[0024] The lower end of the rocket booster 2 is equipped with a booster 21 that provides the main lift thrust. Its upper end has an upward-opening receiving slot. A remote-controlled insertion device 4 is installed within this slot. The remote-controlled insertion device 4 includes a pair of opposing racks 41 with their teeth facing inwards. A gear 42 meshes between the two racks 41. The gear 42 is fitted onto and fixed to the output shaft of a vertically mounted second motor 43. An extension hole is provided on the side wall of the receiving slot at a position corresponding to the racks 41. The second motor 43 also integrates a satellite communication module, capable of receiving remote commands to start or stop operation. When the second motor 43 drives the gear 42 to rotate, it causes the two meshing racks 41 to move synchronously horizontally towards each other along a straight track.

[0025] A retaining ring 15 is fixedly installed at the center of the bottom of the body 11. When the bottom of the body 11 of the rotary-wing UAV 1 aligns with the receiving slot at the upper end of the rocket booster 2, the retaining ring 15 is positioned directly opposite the remote control plug device 4 inside the receiving slot. In the docked and locked state, the second motor 43 drives the gear 42 to rotate, causing the two racks 41 to extend horizontally outward synchronously, pass through the extension holes on the side wall of the receiving slot, and insert into the retaining ring 15 at the bottom of the body 11, thereby firmly locking the rotary-wing UAV 1 and the rocket booster 2 together. When unlocking, the second motor 43 rotates in the opposite direction, driving the racks 41 to retract synchronously into the receiving slot, releasing the lock on the retaining ring 15, and separating the two parts.

[0026] The above embodiments and accompanying drawings are only used to illustrate the technical solutions of this utility model and are not intended to limit this utility model. This utility model has been described in detail with reference to preferred embodiments. Those skilled in the art should understand that any changes, modifications, additions, or substitutions made by those skilled in the art within the scope of this utility model do not depart from the spirit of this utility model and should also fall within the protection scope of the claims of this utility model. Other related technical structures not disclosed in detail in this utility model are existing technologies in the art.

Claims

1. A rocket-assisted rotary-wing unmanned aerial vehicle, characterized in that: It includes a rotorcraft drone (1) that can be detached and connected vertically and a rocket booster (2); The rotary-wing unmanned aerial vehicle (1) includes a cylindrical fuselage (11), a warhead (12) set on the top of the fuselage (11) to reduce wind resistance, and multiple wings (13) evenly distributed on the side wall of the fuselage (11) in the circumferential direction. The middle part of the wings (13) is connected to the fuselage (11) by a hinge. A lifting device (3) is set inside the fuselage (11). The lifting device (3) is hinged to the upper end of the wings (13). A propeller (14) is set at the lower end of the wings (13). The lifting device drives the wings to unfold from the drooping state to the horizontal state. The rocket booster device (2) has a booster (21) at the lower end and a receiving groove at the upper end. A remote control plug device (4) is installed in the receiving groove. A fixing ring (15) is installed at the bottom of the body (11) corresponding to the position of the remote control plug device. The remote control plug extends out and is inserted into the fixing ring (15) to achieve locking between the rotary-wing UAV (1) and the rocket booster device (2).

2. The rocket-assisted rotary-wing unmanned aerial vehicle according to claim 1, characterized in that: The lifting device (3) includes a first motor (31) that is fixedly installed vertically. The output shaft of the first motor (31) is fixedly connected to a lead screw (32). The outside of the lead screw (32) is threadedly connected to a lifting plate (33). The lifting plate (33) is hinged with multiple connecting parts (34). The outer end of the connecting parts (34) is hinged to the upper end of the wing (13). The first motor (31) drives the lead screw (32) to rotate, causing the lifting plate (33) to descend. The wing (13) is pulled to a horizontal state by lever principle.

3. The rocket-assisted rotary-wing unmanned aerial vehicle according to claim 1, characterized in that: The remote control plug device (4) includes a pair of racks (41) arranged opposite each other with their tooth surfaces facing inward. A gear (42) meshes between the two racks (41). The gear (42) is sleeved and fixed on the output shaft of the vertically arranged second motor (43). The side wall of the receiving groove is provided with an extension hole corresponding to the position of the rack (41). The second motor (43) drives the gear (42) to move the rack (41) horizontally in opposite directions in sync, so that it extends out of the extension hole and is inserted into the fixing ring (15).

4. The rocket-assisted rotary-wing unmanned aerial vehicle according to claim 2, characterized in that: The first motor (31) is equipped with a satellite communication module, which can receive remote control commands to start or stop working.

5. The rocket-assisted rotary-wing unmanned aerial vehicle according to claim 3, characterized in that: The second motor (43) integrates a satellite communication module, which can receive remote control commands to start or stop working, thereby controlling the extension or retraction of the plug.

6. The rocket-assisted rotary-wing unmanned aerial vehicle according to claim 2, characterized in that: A stop (35) is fixedly provided at the bottom end of the lead screw (32) to limit the lower limit of the stroke of the lifting plate (33) and prevent it from accidentally falling off the lead screw (32).

7. The rocket-assisted rotary-wing unmanned aerial vehicle according to claim 1, characterized in that: The number of wings (13) is 3 to 6; each propeller (14) is driven by an independent third motor; the third motor integrates a satellite communication module, which can receive remote control commands to control the operation of the propeller (14).

8. The rocket-assisted rotary-wing unmanned aerial vehicle according to claim 1, characterized in that: The body (11) has an opening at the position corresponding to the wing (13), and a pin (16) is fixedly installed in the opening. The wing (13) has a through hole in the middle, and the pin (16) passes through the through hole, so that the wing (13) can rotate around the pin (16).

9. The rocket-assisted rotary-wing unmanned aerial vehicle according to claim 1, characterized in that: The tail section of the body (11) is provided with multiple tail skirts (22).

Images