KR-20260062889-A - An unmanned aerial system consisting of a rotary wing aircraft and a fixed wing aircraft for carrying and dropping the rotary wing aircraft

Abstract

An unmanned flight system and a method of operation thereof are disclosed, wherein a rotary-wing flight device is detachably coupled to a fixed-wing flight device, and the rotary-wing flight device is controlled to stably detach and drop the rotary-wing flight device during flight and to fly independently. An unmanned flight system according to one embodiment includes a fixed-wing flight device comprising a wing, a fuselage, and a tail wing; and one or more rotary-wing flight devices detachably coupled to the lower end of the wing of the fixed-wing flight device. The fixed-wing flight device may include a vertical take-off and landing unit comprising a plurality of vertical take-off and landing modules comprising a motor and a propeller for vertical take-off and landing, a horizontal thrust unit comprising a thrust module comprising a motor and a propeller for horizontal thrust, a coupling unit comprising a coupling module for detachably coupling one or more rotary-wing flight devices, and a fixed-wing control unit controlling the vertical take-off and landing unit, the horizontal thrust unit, and the coupling unit.

Inventors

• 김형준
• 조진희
• 전영조

Assignees

• 주식회사 아쎄따

Dates

Publication Date

20260507

Application Date

20251029

Priority Date

20241029

Claims (20)

1. A fixed-wing aircraft comprising wings, a fuselage, and a tail wing; and It includes one or more rotary-wing aircraft detachably coupled to the lower wing of the above-mentioned fixed-wing aircraft, and The above fixed-wing flight device A vertical take-off and landing unit comprising a plurality of vertical take-off and landing modules including motors and propellers for vertical take-off and landing, A horizontal thrust unit comprising a thrust module including a motor and a propeller for horizontal thrust, A coupling part including a coupling module for separably coupling one or more rotary-wing flight devices and An unmanned flight system comprising a fixed-wing control unit that controls the vertical take-off and landing unit, the horizontal thrust unit, and the coupling unit.
2. In Article 1, The above vertical take-off and landing unit It includes two supports provided at predetermined positions on both sides of the wing in a direction parallel to the fuselage, The above plurality of vertical take-off and landing modules are provided at each end of the two supports, in an unmanned flight system.
3. In Article 2, The above connecting part An unmanned flight system provided at the bottom of the combined position of the above wing and the two supports.
4. In Article 2, The above combination module is A jig for fixing the above rotary-wing flight device and An unmanned flight system comprising a servo motor that drives the jig to combine and separate the rotary-wing flight device.
5. In Article 4, The above rotary-wing flight device A fixing part fixed to the above coupling module; A rotary wing drive unit comprising a plurality of drive modules including a motor and a propeller; and An unmanned flight system comprising a rotary wing control unit that controls the rotary wing drive unit.
6. In Article 5, The above fixed part An unmanned flight system provided on the rear side of the above rotary-wing flight device.
7. In Article 6, The above fixed part The above rotary-wing airfield device and the first fixing device for fixing explosives and An unmanned flight system comprising a second fixer for fixing the explosive and the coupling module.
8. In Article 5, The above rotary wing control unit An unmanned flight system in which the above-mentioned coupling part controls the rotary wing drive part to start driving within a predetermined time after separating the above-mentioned fixing part.
9. In Article 8, The above rotary wing control unit An unmanned flight system that controls the drive unit to change backflight to normal flight within a first and second time point after the drive unit is driven.
10. A vertical take-off and landing unit comprising a plurality of vertical take-off and landing modules, each comprising a motor and a propeller for vertical take-off and landing; A horizontal thrust unit comprising a thrust module including a motor and a propeller for horizontal thrust; A coupling part including a coupling module for detachably coupling one or more rotary-wing flight devices; and A fixed-wing flight device comprising a fixed-wing control unit that controls the vertical take-off and landing unit, the horizontal thrust unit, and the coupling unit.
11. In Article 10, The above vertical take-off and landing unit It includes two supports provided at predetermined positions on both sides of the wing in a direction parallel to the fuselage, The above plurality of vertical take-off and landing modules are fixed-wing flight devices equipped at the ends of each of the two supports.
12. In Article 11, The above connecting part A fixed-wing flight device provided at the bottom of the combined position of the wing and the two supports.
13. In Article 11, The above combination module is A jig for fixing the above rotary-wing flight device and A fixed-wing aircraft comprising a servo motor that drives the jig to combine and separate the rotary-wing aircraft.
14. In Article 11, The above fixed-wing control unit A fixed-wing flight device that controls at least one of the plurality of vertical take-off and landing modules for flight attitude control when separating the rotary-wing flight device by controlling the above coupling part.
15. In Article 11, The above fixed-wing control unit A fixed-wing flight device that controls a plurality of vertical take-off and landing modules based on horizontal thrust to maintain flight altitude.
16. In Article 11, The above fixed-wing control unit It communicates with the rotary wing control unit equipped in the above rotary wing flight device, and A fixed-wing flight device that transmits separation notification information to the rotary-wing control unit when the rotary-wing flight device is separated by controlling the coupling unit above.
17. A fixed part fixed to the coupling module of a fixed-wing airfield; A rotary wing drive unit comprising a plurality of drive modules including a motor and a propeller; and A rotary-wing flight device comprising a rotary-wing control unit that controls the rotary-wing drive unit.
18. In Article 17, The above fixed part A rotary-wing aircraft provided on the rear surface of the above-mentioned rotary-wing aircraft.
19. In Article 18, The above fixed part The above rotary-wing airfield device and the first fixing device for fixing explosives and A rotary-wing flight device comprising a second fixing device for fixing the explosive and the coupling module.
20. In Article 17, The above rotary wing control unit A rotary-wing flight device in which the coupling module of the above fixed-wing flight device controls the rotary-wing drive unit to start driving within a predetermined time after separating the above fixed part.

Description

An unmanned aerial system consisting of a rotary wing aircraft and a fixed wing aircraft for carrying and dropping the rotary wing aircraft The present invention relates to an unmanned flight system technology, specifically an unmanned flight system and a method of operation thereof, wherein a rotary-wing flight device is detachably coupled to a fixed-wing flight device, and the rotary-wing flight device is controlled to stably detach and drop the rotary-wing flight device during flight and fly independently. An Unmanned Aerial Vehicle (UAV) is an aviation system operated by remote control or autonomous flight algorithms without a pilot on board, and consists of sensors, communication modules, propulsion systems, and control systems. These UAVs are classified into various forms, such as fixed-wing, rotary-wing, and tiltrotor aircraft, each possessing different characteristics in terms of flight efficiency, flight duration, and maneuverability. Fixed-wing aircraft are advantageous for long-distance and high-speed flight, while rotary-wing aircraft are capable of vertical take-off and landing and hovering, allowing them to be operated even in confined spaces. Recently, hybrid unmanned aerial vehicles (VTOL, Vertical Take-Off and Landing) that combine these structural advantages are being actively developed. Unmanned aerial vehicles (UAVs) are utilized in various fields, including military, industrial, commercial, and disaster response sectors, and perform functions such as video reconnaissance, cargo transport, surveying, surveillance, communications relay, and rescue support depending on the mission objective. These devices recognize position and attitude through GPS, IMU, LiDAR, and vision sensors, while flight control computers maintain stable flight by controlling thrust and steering in real time. Recently, through the convergence of artificial intelligence (AI) and automatic navigation technologies, they are evolving into advanced systems capable of performing swarm flight with multiple UAVs or autonomously modifying their paths in response to environmental changes during flight. FIG. 1 is a plan view of an unmanned flight system according to one embodiment. FIG. 2 is a front view of an unmanned flight system according to one embodiment. FIG. 3 is an illustrative diagram for explaining a coupling part according to one embodiment. FIG. 4 is an illustrative diagram for explaining the separation operation of a rotary-wing flight device according to one embodiment. FIG. 5 is an exemplary diagram of a fixed-wing flight device according to one embodiment. FIG. 6 is an illustrative diagram for explaining the combination of a rotary-wing flight device according to one embodiment. Hereinafter, an embodiment of the present invention will be described in detail with reference to the attached drawings. In describing the present invention, specific descriptions of related known functions or configurations will be omitted if it is determined that such detailed descriptions may unnecessarily obscure the essence of the present invention. Furthermore, the terms described below are defined considering their functions in the present invention, and these may vary depending on the intentions or conventions of the user or operator. Therefore, their definitions should be based on the content throughout this specification. Hereinafter, embodiments of an unmanned flight system, a fixed-wing flight device, a rotary-wing flight device, and a method of operation thereof will be described in detail with reference to the drawings. FIG. 1 is a plan view of an unmanned flight system according to one embodiment. According to one embodiment, the unmanned flight system (100) may include a fixed-wing flight device (200) and a rotary-wing flight device (300). According to one embodiment, the fixed-wing aircraft (200) may include a wing (210), a fuselage (220), and a tail wing (230), a vertical take-off and landing unit (240) including a plurality of vertical take-off and landing modules including a motor and a propeller for vertical take-off and landing, a horizontal thrust unit (250) including a thrust module including a motor and a propeller for horizontal thrust, a coupling unit (270) including a coupling module for detachably coupling one or more rotary-wing aircraft (300), and a fixed-wing control unit (not shown) for controlling the vertical take-off and landing unit (240), the horizontal thrust unit (250), and the coupling unit (270). For example, the wings (210) are a primary component that generates lift during flight and may consist of left and right wing sections and an intermediate wing section positioned between them. This is intended to improve flight stability and lift efficiency, and acts as the primary lift source during horizontal flight. The fuselage (220) is connected to the lower part of the intermediate wing section to form the central structure of the aircraft and may house electronic devices, batteries, control units