KR-20260063482-A - A drone system including a structure in which a propulsion motor is mounted on the fuselage

KR20260063482AKR 20260063482 AKR20260063482 AKR 20260063482AKR-20260063482-A

Abstract

The present invention relates to a drone in which a motor is coupled to the rear of a fuselage and an EDF or propeller-type motor is coupled, wherein the motor is equipped with an EDF and/or a propeller. The objective of the present invention is to provide a drone in which a motor is installed at the rear of a fuselage and formed with a structure in which a propeller and/or an EDF is mounted on the motor, thereby enabling the coupling of two propulsion devices to a single motor, such as an EDF or propeller-type motor.

Inventors

황상연

Assignees

(주)한컴어썸텍

Dates

Publication Date: 20260507
Application Date: 20241030

Claims (8)

A body section forming the body of the drone, with multiple sensors and a battery built in; Main wing sections formed on both sides of the above-mentioned fuselage section to control the flight direction of the fuselage section; A motor coupled to the rear of the above-mentioned body; A propulsion device coupled to the motor and generating propulsion force by the rotational force of the motor; comprising A drone system characterized in that the motor is detachably coupled to the rear of the fuselage.
In paragraph 1, the propulsion device is, It is an EDF (Electric Ducted Fan) or propeller, A drone system characterized by the EDF or the propeller being coupled to the motor, or the EDF and the propeller being coupled simultaneously.
In paragraph 2, the above-mentioned body part is, A drone system characterized by including a guide portion formed by being recessed to a predetermined depth on the rear upper surface of the fuselage and into which the EDF is inserted.
In paragraph 2, the above drone system is, A mount portion interposed between the body portion and the motor to mitigate shock generated by the rotation of the motor; A drone system characterized by further including
In paragraph 2, the above drone system is, A flight control module that controls the flight of the above-mentioned drone; A power module that controls the on/off of the above drone and supplies power to electrical devices within the drone; A receiving module that receives a control signal transmitted from a controller; A wing control module that controls the angle of the wing portion based on a control signal received by the receiving module or data measured from the sensor; A motor control module that controls the rotational speed and rotational direction of the motor based on a control signal received by the receiving module or data measured from the sensor; A drone system characterized by further including
In paragraph 5, the above-mentioned drone system is, Power on step in which the drone is switched to flight mode by the power module above, The above motor rotation step in which the motor rotates in one direction, A takeoff phase in which thrust is generated by the above-mentioned propulsion device and the drone takes off into the air, A first altitude measurement step in which an altitude measurement sensor equipped in the above drone determines whether the height of the above drone is within a predetermined first altitude range, A turning step is performed when it is determined in the first altitude measurement step that the drone is located within the first altitude range, and in which the drone turns within the first altitude range. A flight mode selection step in which the flight mode of the above-mentioned drone is selected as an automatic flight mode or a manual flight mode, A flight stage in which the above-mentioned drone flies by means of a control signal transmitted from a controller or flies autonomously along a predetermined path, When the above flight phase is completed, a descent phase in which the drone descends, A second altitude measurement step in which the altitude measurement sensor determines whether the height of the drone is within a predetermined second altitude range, A motor stop step is performed when it is determined in the second altitude measurement step that the drone is located within the second altitude range, and in which the rotation of the motor is stopped. Motor reverse rotation step in which the above motor rotates in the opposite direction of the above one direction, A horizontal control step in which the fuselage is controlled to be horizontal with respect to the ground by the above-mentioned main wing control module, and A drone system characterized by the drone flying in a landing sequence in which the drone lands on the ground.
In paragraph 6, the motor rotation step is, When both the EDF and the propeller are coupled to the motor, during the motor rotation stage, only the EDF receives rotational force to generate thrust, and A drone system characterized in that the propeller rotates when the speed of the acceleration sensor equipped in the drone exceeds a certain value after the takeoff phase.
In paragraph 6, the above-mentioned drone system is, It further includes a variable pitch propeller coupled to the above-mentioned fuselage; and A drone system characterized by the variable pitch propeller changing in the reverse direction when the drone lands.

Description

A drone system combined with an EDF or propeller-type motor {A drone system including a structure in which a propulsion motor is mounted on the fuselage} The present invention relates to a drone system coupled with an EDF or propeller-type motor, and more specifically, to a drone system coupled with an EDF or propeller-type motor in which the motor is coupled to the rear of the fuselage and the motor is equipped with an EDF and/or a propeller. Generally, drones are unmanned aerial vehicles that are being utilized in various civilian sectors beyond the military. Recently, the scope of drone applications has been gradually expanding across diverse fields, such as filming locations that are difficult for humans to access directly or realizing unmanned delivery services. Conventional drones have low reliability due to their use of components comparable to those of manned aircraft, which limits their application fields and increases the risk of crashes, thereby restricting their uses. Rotary-wing drones fly by rotating multiple propellers, but they have the problem of short flight times and significant human and material damage due to free-falling upon crashing. Therefore, fixed-wing drones capable of long-duration flight are widely used, particularly in the military sector. Drones are structured to receive user control signals wirelessly and fly by obtaining thrust from propellers driven by motors. However, drones using motors and propellers like this have the problem that the motors and propellers can frequently be damaged or broken in the event of a crash or impact during flight, and the user's hands can be injured by the rapidly rotating propellers. FIG. 1 is a perspective view of a drone system according to an embodiment of the present invention. FIG. 2 is an exploded perspective view of a drone system according to an embodiment of the present invention. FIG. 3 is an example of use of a drone system according to an embodiment of the present invention. FIG. 4 is a block diagram of a drone system according to an embodiment of the present invention. FIG. 5 is an operation sequence diagram of a drone system according to an embodiment of the present invention. Hereinafter, an embodiment of the present invention as described above will be explained in detail with reference to the drawings. FIG. 1 illustrates a perspective view of a drone system according to an embodiment of the present invention. As shown in FIG. 1, the drone (10) includes a body portion (100) forming the body of the drone and wing-shaped main wing portions (200) formed on both sides of the body portion (100). A motor (300) is formed at the rear of the body (100) to provide propulsion for the drone (10) to fly, and as the EDF (Electric Ducted Fan) and/or propeller are operated by the motor (300), the drone (10) obtains propulsion and flies. A plurality of sensors are provided inside the fuselage (100), and it is preferable to install a battery (not shown) that provides power necessary for the operation of the plurality of sensors and motors (300), and an actuator is installed to control the angle of the main wing portions (200) on both sides of the fuselage (100). Since conventional drones are formed with only one propeller connected to a single motor, multiple motors must be provided to connect multiple propellers. However, the drone of the present invention can selectively combine a propulsion device in the form of an EDF (400) or a propeller (500) with a single motor (300), and is formed so that both the EDF (400) and the propeller (500) can be mounted on the motor (300) as needed, thereby improving thrust but reducing the number of motors, which reduces the weight of the drone itself and increases the flight time of the drone. FIG. 2 illustrates an exploded perspective view of a drone system according to one embodiment of the present invention. As shown in FIG. 2, the drone (10) of the present invention is formed with a motor (300), an EDF (400) that converts the rotational force of the motor (300) into propulsion force, and/or a propeller (500) formed in a detachable form at the rear of the drone. A guide section (101) is formed at the upper rear portion of the body (100), recessed to a predetermined depth and extended for a predetermined length in the forward direction of the drone, and an EDF (400) is inserted along the guide section (101). A motor (300) is inserted into a hole formed at the rear of the body (100). At this time, when the motor (300) is mounted on the body part (100), it may be coupled to a spring-structured motor mounting structure provided at the rear of the body part (100). The motor mounting structure may be formed in such a way that when the motor (300) is mounted, the spring is compressed and then expanded to a predetermined width so that the motor (300) does not detach, and when the motor (300) is to be separated, the motor (300) is separated by re-pressing the motor (300) or restoring the spring to its original stat