KR20240124062A - Variable geometry wing typed drone - Google Patents

Abstract

The present invention relates to a variable-wing drone. A variable-wing drone according to an embodiment of the present invention includes a body formed in a form in which a width increases from a front end to a rear end, a pair of wing parts rotatably formed on both sides of the body part, a propulsion part formed at the rear end of the body part to drive a propeller, a detection part formed on the body part to detect position information and movement information, and a control part which, depending on a flight speed, flies in a delta wing mode in which the pair of wing parts are folded relative to the body part, or in a forward wing mode in which the pair of wing parts are deployed by rotating from the body part at a preset angle.

Description

Variable geometry wing typed drone

The present invention relates to a variable wing drone, and more specifically, a technology for performing a hovering flight while changing from a delta wing to a forward-swept wing is disclosed.

Unmanned drones can be broadly divided into fixed-wing unmanned drones that fly by obtaining propulsion through the rotation of the propeller and lift through fixed wings, and rotary-wing unmanned drones that fly solely using the thrust generated by the rotation of the rotor. Among fixed-wing behaviors, the variable wing refers to a wing in which the main lift-generating device of the aircraft, the wing, is not fixed but moves forward and backward and changes. Among fixed-wing types, the forward-swept wing refers to a wing in which the tip of the aircraft wing is extended ahead of the part attached to the fuselage in the direction of flight.

Fixed-wing unmanned drones cannot take off and land vertically, so they require a runway, cannot hover, and have a high risk of accidents during takeoff and landing. Rotary-wing unmanned drones have multiple propellers, so they are complicated to control, and their efficiency is low due to high battery consumption. Recently, unmanned drones have been used for military purposes. In particular, they are being developed for the purpose of destroying key military facilities in enemy territory or enemy fighter jets. The need for military unmanned drones has increased due to the recent Russia-Ukraine War.

Among the conventional technologies, Korean Patent No. 10-1663814 (announced on October 7, 2016) relates to a "tail takeoff and landing aircraft", and discloses a technology for forming a variable wing section that rotates around the body of the aircraft to function as a rotor during takeoff and landing, and is fixed to the body of the aircraft to function as a fixed wing during cruising. However, in this case, multiple propellers must be used, and the limitation of reduced efficiency due to variable main wings has not been overcome.

The technical problem to be solved by the present invention is to provide a variable wing drone that changes from a delta wing to a forward-swept wing shape depending on the flight speed in order to perform a hovering flight.

Additionally, the purpose is to provide a variable-wing drone that can variably adjust its speed depending on its flight altitude or flight mode.

Additionally, the aim is to provide a variable wing drone that can detect a target while hovering and change flight mode to quickly reach the target.

Additionally, the goal is to provide a variable-wing drone that can take off or land vertically and can be used in various spaces.

A variable wing drone according to an embodiment of the present invention comprises a body portion formed in a shape in which a width increases from a leading end to a trailing end, a pair of wing portions rotatably formed on both sides of the body portion, a propulsion portion formed at the trailing end of the body portion to drive a propeller, a detection portion formed on the body portion to detect position information and movement information, and a control portion which, depending on a flight speed, causes the pair of wing portions to fly in a delta wing mode in which they are folded relative to the body portion, or in a forward wing mode in which they are deployed by rotating the pair of wing portions at a preset angle relative to the body portion.

In addition, the body part further includes a communication part formed to communicate with an external user terminal, and the control part receives a preset flight zone from the user terminal and causes the pair of wing parts to fly in the delta wing mode until the flight zone is reached, and after reaching the flight zone, changes the pair of wing parts to the forward wing mode to perform a hovering flight, and receives target information from the user terminal and, when the target information is searched, changes the pair of wing parts to the delta wing mode to perform a steep dive flight.

In addition, the device further includes an image acquisition unit formed at the tip of the body to acquire images of the surroundings, and the control unit can change the pair of wing units to the delta wing mode to perform a steep dive flight when target information is recognized from image information acquired from the image acquisition unit.

Accordingly, the mission can be performed by controlling the flight speed by changing the shape of the delta wing to a forward-swept wing depending on the flight speed to perform a hovering flight.

Additionally, the speed can be variably adjusted depending on the flight altitude or flight mode of the variable-wing drone.

Additionally, by detecting a target while hovering, the flight mode can be changed to quickly reach the target.

Additionally, variable-wing drones can take off and land vertically, allowing them to be used in a variety of spaces.

Figure 1 is a configuration diagram of a variable wing drone according to an embodiment of the present invention.
Figure 2 is an exemplary diagram explaining that the variable wing drone according to Figure 1 operates from the delta wing mode to the forward wing mode.
Figure 3 is a detailed configuration diagram of the propulsion unit of the variable wing drone according to Figure 1.
Figure 4 is an example for explaining that a variable-wing drone according to Figure 1 generates propulsion according to the flight direction.
FIGS. 5 and 6 are exemplary diagrams for explaining the addition of a communication unit and an image acquisition unit to the variable wing drone according to FIG. 1.

Hereinafter, embodiments of the present invention will be described in detail with reference to the attached drawings. The terms used are terms selected in consideration of their functions in the embodiments, and the meanings of the terms may vary depending on the intention of the guardian or operator, precedents, etc. Therefore, the meanings of the terms used in the embodiments described below shall follow the definitions in this specification, and in the absence of a specific definition, they shall be interpreted as meanings generally recognized by those skilled in the art.

FIG. 1 is a configuration diagram of a variable-wing drone according to an embodiment of the present invention, FIG. 2 is an exemplary diagram explaining operation of the variable-wing drone according to FIG. 1 from a delta wing mode to a forward-swept wing mode, FIG. 3 is a detailed configuration diagram of a propulsion unit of the variable-wing drone according to FIG. 1, and FIG. 4 is an example explaining generation of propulsion force according to a flight direction of the variable-wing drone according to FIG. 1.

Referring to FIGS. 1 to 4, a variable wing drone (100) according to an embodiment of the present invention includes a body part (110), a wing part (120), a propulsion part (130), a detection part (140), and a control part (150).

The body part (110) is formed in a shape that becomes wider from the front end to the rear end. For example, the body part (110) may be formed in an overall triangular structure. When a pair of wing parts (120) formed on the side of the body part (110) are closely attached, a single triangular structure is completed. A sawtooth-shaped protrusion may be formed on the surface of the body part (110). This is to implement a stealth function that is not detected by radar. The body part (110) is connected to the wing part (120) and the propulsion part (130), and a detection part (140) and a control part (150), etc. may be mounted inside.

The wing portion (120) is formed rotatably on both sides of the body portion (110). The wing portions (120) are formed as a pair and are respectively connected to both sides of the body portion (110). The cross section of the wing portion (120) may be formed in an airfoil shape to induce lift. The wing portion (120) can fold or unfold a pair of wings by a wing drive portion (121). This wing drive portion (121) is driven by the control of the control portion (150). The pair of wing portions (120) maintain a delta wing shape in a state in which they are folded on the body portion (110) side. This delta wing is used to accelerate speed, such as during launch or rapid descent. When the wing portions (120) are unfolded, they maintain a forward wing shape. This forward wing is used for hovering flight.

In addition, a tail wing (122) (Empennage) is formed on the body part (110) to control the flight direction. The tail wing (122) can be controlled by the control unit (150) according to the flight altitude, flight direction, and flight speed. The number and type of the tail wings (122) can vary depending on the user's design. The tail wings (122) can also be controlled differently depending on the delta wing mode or the forward wing mode of the wing part (120).

The propulsion unit (130) is formed at the rear end of the body unit (110) and drives the propeller (131). For example, the propulsion unit (130) can be implemented using an EDF (Electric Ducted Fan) motor, a gas turbine for RC, or an RC jet. In this case, the propulsion unit (130) can have the pitches of multiple propellers (131) variable. The propulsion unit (130) can be controlled differently in rotation speed, rotation direction, etc. by the control unit (150). For example, in the case of the delta wing mode, the propulsion unit (130) drives the propeller (131) to accelerate the flight speed to enable rapid ascent or descent. In the forward wing mode, the propulsion unit (130) drives the propeller (131) to decelerate the flight speed to enable hovering flight. Accordingly, the speed can be variably adjusted depending on the flight altitude or flight mode of the variable wing drone (100).

In addition, the propulsion unit (130) can also take off and land the body (110) in a vertical direction. For example, in the takeoff and landing mode, the propulsion unit (130) can generate propulsive force from the rear end to the front end of the body (110) to move the body (110) vertically from the ground. In the flight mode, the propulsion unit (130) can rotate a plurality of propellers (131) by varying the second pitch to generate propulsive force from the front end to the rear end of the body (110) to move the body (110) horizontally from the ground. Accordingly, the variable-wing drone (100) can take off or land vertically, so that it can be utilized in various spaces. In FIG. 4, (a) represents the propulsive force when the variable-wing drone (100) flies horizontally, and (b) represents the propulsive force when the variable-wing drone (100) flies vertically.

Specifically, the propulsion unit (130) includes a propeller (131), a first driving unit (132), a plate (133), and a second driving unit (134). The propeller (131) has a pair of blades (131-1) formed in a cross section in the shape of an airfoil and connected in a straight line through a hub (131-2) at the center. In this case, the number of blades (131-1) may vary depending on the user setting, and will be described herein as a minimum unit. The pair of blades (131-1) are formed so that the pitch can be varied. The lower portion of the hub (131-2) is connected to the first driving unit (132) through a driving shaft (132-1), so that the pair of blades (131-1) rotate.

The first driving unit (132) is connected to the hub (131-2) of the propeller (131) through a central axis to rotate a pair of blades (131-1). The first driving unit (132) can be implemented as an electric motor, and it is preferable that it can accelerate and decelerate and rotate forward and reversely. The first driving unit (132) is located and fixed on the inside of the body (110), and is connected to a battery inside the body (110) to receive power. The rotation speed of the first driving unit (132) is controlled by the control unit (150) (140).

The plate (133) is a disc-shaped plate with a hole formed in the center and moves along the driving shaft (132-1). The plate (133) is connected to a pair of blades (131-1) through a plurality of first links (133-1). In addition, the plate (133) is connected to a second driving unit (134) described later through a plurality of second links (133-2). In other words, a plurality of first links (133-1) are connected to one side of the plate (133), and a plurality of second links (133-2) are connected to the other side. The plate (133) serves as an intermediate body that transmits the driving force of the second driving unit (134) to a pair of blades (131-1).

The second driving unit (134) is connected to the plate (133) through a plurality of second links (133-2). The second driving unit (134) may be formed as one, but is not necessarily limited thereto. For example, the second driving unit (134) may be implemented as a 1-servo system or a 3-servo system. The second driving unit (134) varies the height and inclination of the plate (133) through the second link (133-2), and as the plate (133) varies, the pitch of a pair of blades (131-1) varies in conjunction with this through the first link (133-1). In this case, the pitch and inclination of the rotational plane of the pair of blades (131-1) may also be varied.

The sensing unit (140) is formed in the body (110) and detects location information and movement information. For example, the sensing unit (140) may include GPS, an acceleration sensor, etc., but is not necessarily limited thereto. The sensing unit (140) outputs sensing information on flight position, flight speed, flight direction, etc. to the control unit (150). The sensing unit (140) determines the flight status of the variable wing drone (100) to determine whether the wing unit (120) will fly in the delta wing mode or the forward wing mode. For example, the drone may fly in the delta wing mode up to a preset altitude and then fly in the forward wing mode when the preset altitude is reached.

The control unit (150) controls the flight in a delta wing mode with a pair of wings (120) folded on the body (110) depending on the flight speed, or in a forward wing mode with a pair of wings (120) rotated from the body (110) at a preset angle to be deployed. Here, the flight speed can be set for each altitude. For example, when launched from a launcher, the drone can be set to fly in a delta wing mode up to a preset altitude, and then operate in a forward wing mode when the preset altitude is reached. This is to allow the variable wing drone (100) to quickly reach a specific altitude and then search for a target while performing a hovering flight.

The control unit (150) is formed inside the body (110) and rotates the plurality of blades (131-1) by varying the first pitch (+) when in the takeoff and landing mode. When a pair of blades (131-1) are varied to the first pitch, propulsion is generated as air moves from the rear end to the front end of the body (110). The fixed-wing drone (100) of the present invention performs vertical takeoff and landing with the rear end facing the sky and the front end facing the ground. Therefore, the fixed-wing drone (100) can take off and land or hover while the body (110) moves in the vertical direction.

In addition, the control unit (150) rotates the plurality of blades (131-1) in the second pitch (-) opposite to the first pitch when in flight mode. When a pair of blades (131-1) are varied to the second pitch, propulsion is generated as air moves from the front end to the rear end of the body (110). The fixed-wing drone (100) of the present invention changes its posture when a pair of blades (131-1) are varied from the first pitch to the second pitch. In the first pitch, the body (110) rises, descends, or stops in the vertical direction, and in the second pitch, the body (110) moves in the horizontal direction. Accordingly, it is possible to perform missions in various postures by taking off and landing in the vertical direction of the body (110).

FIGS. 5 and 6 are exemplary diagrams for explaining the addition of a communication unit and an image acquisition unit to the variable wing drone according to FIG. 1.

Referring to FIG. 5, a variable wing drone (100) according to an embodiment of the present invention may further include a communication unit (160).

The communication unit (160) is formed in the body unit (110) and communicates with an external user terminal. For example, the communication unit (160) may communicate using LTE, WIFI, WIBRO, BLUETOOTH, etc., but is not necessarily limited thereto. The communication unit (160) is capable of two-way communication with the user terminal and may provide flight information, etc. about the variable wing drone (100) to the user terminal. The communication unit (160) may also receive a control signal from the user terminal and output it to the control unit (150). The communication unit (160) may also communicate with a plurality of variable wing drones (100) and perform group flight.

In this case, the control unit (150) receives a preset flight zone from the user terminal. This flight zone includes the altitude or flight range at which the variable wing drone (100) should fly. This information can use GPS coordinates. The control unit (150) causes the variable wing drone (100) to fly a pair of wings (120) in a delta wing mode until it reaches the flight zone. This is to maximize the flight speed and reach the target point in a short time.

In addition, the control unit (150) changes one pair of wings (120) into forward wing mode after the variable wing drone (100) reaches the flight area and performs a hovering flight. This is to search for target information while performing a hovering flight. The control unit (150) receives target information from the user terminal, and when the target information is searched, changes one pair of wings (120) into delta wing mode and performs a steep dive flight. This is to quickly descend and reach the target information.

Meanwhile, the variable wing drone (100) according to the embodiment of the present invention may further include an image acquisition unit (170).

Referring to Fig. 5, the image acquisition unit (170) is formed at the tip of the body part (110) to acquire an image. Since the tip of the body part (110) faces the ground, the image acquisition unit (170) photographs the ground. The ground situation can be monitored by the image acquisition unit (170). Image information acquired from the image acquisition unit (170) can be transmitted to an external server at a preset time cycle.

In this case, the control unit (150) can drive the image acquisition unit (170) when the body (110) switches from horizontal flight to vertical flight. In other words, when the fixed-wing drone (100) performs vertical takeoff and landing and then moves to a target point, the body (110) is made to fly horizontally, and then when the body (110) switches its attitude to vertical flight again at the target point, the image acquisition unit (170) is driven. This is to enable the fixed-wing drone (100) to acquire images only at a selected point when it has a reconnaissance mission.

In addition, the control unit (150) can change a pair of wings (120) into a delta wing mode to perform a steep dive flight when target information is recognized from the image information acquired from the image acquisition unit (170). This is to allow the variable wing drone (100) to perform a hovering flight and immediately perform a steep dive when target information is recognized and collide with the target. For example, if the variable wing drone (100) is used for military purposes, it can be equipped with a bomb to detonate an enemy target. If the variable wing drone (100) is used for firefighting, it can be equipped with a fire extinguishing agent to fall to a fire site and extinguish the fire.

Although the present invention has been described above with reference to the preferred embodiments described with reference to the drawings, it is not limited thereto. Accordingly, the present invention should be interpreted by the description of the claims intended to encompass obvious modifications that can be derived from the described embodiments.

100 : Variable wing drone
110 : Body
120 : Wings
121: Wing drive unit
122 : Tail Wing
130 : Propulsion Unit
131 : Propeller
131-1 : Blade
131-2 : Hub
132: 1st drive unit
132-1 : Drive shaft
133 : Plate
133-1 : First Link
133-2 : Second Link
134: 2nd drive unit
140 : Detection Unit
150 : Control Unit
160 : Communication Department
170 : Video acquisition department

Claims (3)

A body formed in a shape that becomes wider from the tip to the tail;
A pair of wing parts rotatably formed on both sides of the above body part;
A propulsion unit formed at the rear end of the above body part and driving a propeller;
A detection unit formed in the above body part to detect location information and movement information; and
A variable wing drone including a control unit that, depending on the flight speed, flies in a delta wing mode in which the pair of wings are folded relative to the body, or in a forward wing mode in which the pair of wings are rotated from the body at a preset angle and unfolded. In the first paragraph,
It further includes a communication unit formed in the above body part and communicating with an external user terminal,
The above control unit,
A variable wing drone that receives a preset flight zone from the user terminal, flies the pair of wings in the delta wing mode until reaching the flight zone, and after reaching the flight zone, changes the pair of wings to the forward wing mode to perform a hovering flight, and receives target information from the user terminal, and when the target information is detected, changes the pair of wings to the delta wing mode to perform a steep dive flight. In the first paragraph,
It further includes an image acquisition unit formed at the tip of the above body part to acquire an image of the surroundings,
The above control unit,
A variable wing drone that, when target information is recognized from image information acquired from the image acquisition unit, changes the pair of wings into the delta wing mode to perform a steep dive flight.