Propulsion device for airborne mobile equipment

Abstract

A propulsion device for an aerial maneuvering device includes: a housing having an internal space, wherein a plurality of slits are formed along a circumferential surface of the housing extending vertically; a drive unit having a connecting portion formed to mate with corresponding slits among the plurality of slits in the housing; a plurality of linkage units configured to mate with corresponding slits among the plurality of slits in the housing, wherein the linkage units are rotatably connected to the connecting portions of the drive unit; and a plurality of wing-shaped units configured to rotate in association with the linkage units, the wing-shaped units rotating during vertical movement of the drive unit, thereby being folded into or deployed from the housing. The propulsion device is configured to prevent accidents caused by propulsion dispersion when the aerial maneuvering device descends, and the propulsion device improves space utilization during storage of the aerial maneuvering device.

Description

Technical Field

[0001] This disclosure relates to a thruster device for air mobility equipment that prevents injury and / or property damage caused by thruster dispersion when the air mobility equipment descends, and that the thruster device improves space utilization during the storage of the air mobility equipment. Background Technology

[0002] Recently, air mobility vehicles (or “air mobility equipment”) that can be used in various fields such as cargo container transportation and medical transportation are under development, and energy efficiency and stability technologies for air mobility equipment have been developed and are approaching the stage of commercial use.

[0003] These aerial maneuvers fly by manipulating thrusters, and stability during descent is crucial in these maneuvers. Therefore, in such aerial maneuvers, the thrusters are selectively controlled in response to descent, but there are no safety measures in place for the eventual descent of these aerial maneuvers.

[0004] For example, when aerial maneuvering equipment descends, each rotating thruster impacts the ground. The impact of rapidly rotating thrusters creates debris that can scatter in the surrounding environment, potentially leading to secondary accidents.

[0005] The information disclosed in the background section of this invention is intended only to enhance the understanding of the general background of the invention and should not be construed as an admission or in any way implying that such information constitutes prior art known to those skilled in the art. Summary of the Invention

[0006] This disclosure provides a thruster device for airborne maneuvering equipment that prevents secondary accidents caused by thruster dispersion when the airborne maneuvering equipment descends, and that the thruster device can improve space utilization when storing airborne maneuvering equipment.

[0007] In view of the above, the propulsion device of the aerial maneuvering equipment according to the present disclosure includes: a housing having an internal space, wherein a plurality of slits are formed along the circumferential surface of the housing to extend in a vertical direction; a drive unit configured to move in a vertical direction within the internal space of the housing, and the drive unit having a connecting portion formed to match a corresponding slit among the plurality of slits in the housing; a plurality of linkage units disposed outside the housing, and the plurality of linkage units configured to match the slits among the plurality of slits in the housing, wherein the linkage units are rotatably connected to the connecting portions of the drive unit; and a plurality of wing-shaped units rotatably mounted to the housing, and the plurality of wing-shaped units are respectively connected to the linkage units and configured to rotate in association with the linkage units, the wing-shaped units rotating when the drive unit moves up and down, thereby being folded into or unfolded from the housing.

[0008] The drive unit includes: an actuator configured to generate power; and a drive rod configured to move up and down by receiving power from the actuator, wherein the drive rod extends such that a plurality of connecting portions arranged circumferentially along the drive rod mate with corresponding slits in the housing.

[0009] Each of the multiple linkage units may include multiple linkage components that are rotatably connected, and each of the multiple wing units may include multiple wing components that are rotatably connected to the respective linkage components and rotatably connected to each other.

[0010] Each of the plurality of wing-shaped units includes a first wing-shaped component and a second wing-shaped component, one end of the first wing-shaped component being rotatably connected to a housing, and the second wing-shaped component being rotatably connected to the other end of the first wing-shaped component. The first and second wing-shaped components are rotatably connected to a corresponding link component of one of the plurality of link units.

[0011] Each of the linkage units includes a first linkage component and a second linkage component. One end of the first linkage component is rotatably connected to one of a plurality of connecting parts, and the other end of the first linkage component is slidably and rotatably connected to a first wing-shaped component. One end of the second linkage component is rotatably connected to the other end of the first linkage component, and the other end of the second linkage component is rotatably connected to a second wing-shaped component.

[0012] The first wing-shaped member includes a guide groove formed in a linear shape along the longitudinal direction of the first wing-shaped member, and the first link member includes a guide portion formed at the other end of the first link member to connect to the guide groove.

[0013] The second wing-shaped component includes a hinge connection that protrudes from one end of the second wing-shaped component to connect to the other end of the second link component, and the hinge connection is formed as a matching guide groove, and the hinge connection is inserted into the guide groove when the wing-shaped unit is deployed.

[0014] The first link component and the second link component are formed into a matching guide slot, and the first link component and the second link component are inserted into the guide slot when the wing-shaped unit is deployed.

[0015] Multiple recessed receiving slots are formed in the circumferential surface of the housing to match the corresponding wing-shaped units, and slits are formed in each receiving slot.

[0016] The drive unit is configured to operate such that the wing unit is folded when a descent signal is input to the drive unit according to the aerial maneuvering equipment.

[0017] By configuring the thruster device of the air mobility equipment as described above, the thruster device can prevent accidents caused by the scattering of thruster debris when the air mobility equipment descends, and the thruster device can improve the space utilization when storing the air mobility equipment. Attached Figure Description

[0018] The above and other aspects, features, and advantages of this disclosure will become more apparent from the following detailed description taken in conjunction with the accompanying drawings, in which:

[0019] Figure 1 This is a view showing the propulsion device of an aerial maneuvering device according to the present disclosure;

[0020] Figure 2 This is a view showing the process of folding the propulsion device of the aerial maneuvering equipment according to this disclosure;

[0021] Figure 3 This is a view showing the propulsion device of the aerial maneuvering equipment according to this disclosure in a folded state; and

[0022] Figure 4 This is a view showing the linkage unit and the wing unit according to this disclosure. Detailed Implementation

[0023] It should be understood that, as used herein, the terms “vehicle” or “of a vehicle” or other similar terms include motor vehicles in a broad sense (such as passenger cars, including sport utility vehicles (SUVs), buses, trucks, and various commercial vehicles), water vehicles (including various small boats and ships), aircraft, etc., and include hybrid vehicles, electric vehicles, plug-in hybrid electric vehicles, hydrogen-powered vehicles, and other alternative fuel vehicles (e.g., fuels derived from resources other than petroleum). As mentioned herein, a hybrid vehicle is a vehicle with two or more power sources, such as a gasoline-powered and an electric vehicle.

[0024] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit this disclosure. As used herein, unless the context clearly indicates otherwise, the singular forms “a,” “an,” and “the” are intended to also include the plural forms. It should also be understood that when the terms “comprises” and / or “comprising” are used in this specification, they specify the presence of the stated features, integrals, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components, and / or combinations thereof. As used herein, the term “and / or” includes any and all combinations of one or more of the associated listed items. Throughout the specification, unless explicitly stated otherwise, the word “comprise” and variations such as “comprises” or “comprising” will be understood to imply the inclusion of the stated elements, but do not exclude the inclusion of any other elements. Furthermore, the terms “unit,” “apparatus,” “machine,” and “module” described in the specification mean a unit for performing at least one function and operation, and can be implemented by hardware components or software components and combinations thereof.

[0025] Furthermore, the control logic of this disclosure can be implemented as a non-volatile computer-readable medium containing executable program instructions that can be executed by a processor, controller, or the like. Examples of computer-readable media include, but are not limited to, ROM, RAM, optical disc (CD)-ROM, magnetic tape, floppy disk, flash drive, smart card, and optical data storage devices. The computer-readable medium can also be distributed across a computer system connected to a network, enabling it to be stored and executed in a distributed manner, for example, via a telematics server or a controller area network (CAN).

[0026] In the following description, the propulsion device of the aerial maneuvering equipment according to the present disclosure will be described with reference to the accompanying drawings.

[0027] Figure 1 This is a view showing the propulsion device of an aerial maneuvering device according to the present disclosure. Figure 2 This is a view illustrating the process of folding the propulsion device of the aerial maneuvering equipment according to this disclosure. Figure 3 This is a view showing the propulsion device of the aerial maneuvering equipment according to this disclosure in a folded state, and Figure 4 This is a view showing the linkage unit and the wing unit according to this disclosure.

[0028] like Figures 1 to 3 As shown, the propulsion device of the aerial maneuvering equipment according to the present disclosure includes: a housing 100 having an internal space in which a plurality of slits 110 are formed along the circumferential surface of the housing 100 extending in a vertical direction; a drive unit 200 configured to move in a vertical direction within the internal space of the housing 100, and the drive unit having a connecting portion 221 formed to mate with a corresponding slit 110; a plurality of linkage units 300 disposed outside the housing 100, and the linkage units configured to mate with a corresponding slit 110, wherein the linkage units 300 are rotatably connected to a corresponding connecting portion 221 of the drive unit 200; and a plurality of wing-shaped units 400 rotatably mounted to the housing 100, connected to a corresponding linkage unit 300, and the plurality of wing-shaped units configured to rotate in association with a corresponding linkage unit 300, the wing-shaped units rotating as the drive unit 200 moves up and down, thereby being folded into or unfolded from the housing 100.

[0029] Here, the drive motor M is mounted in the housing 100, and when the drive motor M rotates, the wing-shaped unit 400 can generate thrust by rotating in the deployed state. The drive unit 200 is mounted in the housing 100, and a plurality of slits 110 are formed along the circumferential surface of the housing 100. That is, in the housing 100, the number of slits 110 is as many as the number of wing-shaped units 400 constituting the thruster, and the drive unit 200 is mounted in the internal space to rotate together with the housing 100.

[0030] The drive unit 200 is configured to move vertically within the interior space of the housing 100, and the drive unit is provided with a connecting portion 221 that matches the corresponding slit 110. When the drive unit 200 is driven, the linkage unit 300 and the wing unit 400 operate in a manner connected to each other, causing the wing unit 400 to fold or unfold.

[0031] Therefore, the drive unit 200 includes: an actuator 210 configured to generate power; and a drive rod 220 configured to move up and down by receiving power from the actuator 210, wherein the drive rod 220 extends such that a plurality of connecting portions 221 arranged circumferentially thereon mate with corresponding slits 110. That is, the actuator 210 is mounted in the housing 100, and when the actuator 210 is operated, the drive rod 220 moves up and down in the vertical direction while being pulled out or pulled into the actuator 210. Here, the plurality of connecting portions 221 extend circumferentially along the drive rod 220 to mate with corresponding slits 110. Therefore, when the actuator 210 is operated, the drive rod 220 moves in the vertical direction, thereby allowing the linkage unit 300 connected to the corresponding connecting portion 221 of the drive rod 220 to rotate in a manner associated with the movement of the drive rod 220, thereby causing the wing-shaped unit 400 to rotate.

[0032] That is, when the drive unit 200 moves vertically inside the housing 100, the linkage unit 300 connected via the connection portion 221 of the drive unit 200 rotates vertically outside the housing 100. Therefore, the wing-shaped unit 400 connected to the corresponding linkage unit 300 rotates vertically in association with the linkage unit 300. Thus, the wing-shaped unit 400 can be folded into or deployed from the housing 100. Specifically, when storing the aerial maneuvering equipment or when the aerial maneuvering equipment descends, the wing-shaped unit 400 can be folded into the housing 100, and during normal operation, the wing-shaped unit 400 remains deployed and rotates with the housing 100, thereby generating thrust.

[0033] The linkage unit 300 and the wing unit 400 of this disclosure, provided for this purpose, will be described in detail below.

[0034] Each linkage unit 300 may include a plurality of rotatably connected linkage components, and each wing unit 400 may include a plurality of wing components, with the corresponding linkage components rotatably connected to the wing components, and the plurality of wing components rotatably connected to each other.

[0035] In this way, since each wing unit 400 includes multiple wing components, and the wing components are rotatably connected via multiple linkage components, the space occupied by the wing components in the folded state can be further reduced, because each wing component is folded when the wing unit 400 is folded.

[0036] Specifically, such as Figure 4As shown, each wing-shaped unit 400 includes a first wing-shaped component 410 and a second wing-shaped component 420. One end 410a of the first wing-shaped component is rotatably connected to the housing 100, and the second wing-shaped component is rotatably connected to the other end 410b of the first wing-shaped component 410. The first wing-shaped component 410 and the second wing-shaped component 420 are rotatably connected to the corresponding link component of the corresponding link unit 300.

[0037] Here, the linkage unit 300 includes a first linkage component 310 and a second linkage component 320. One end 310a of the first linkage component is rotatably connected to a corresponding connecting portion 221, and the other end 310b of the first linkage component is slidably and rotatably connected to the first wing-shaped component 410. One end 320a of the second linkage component is rotatably connected to the other end 310b of the first linkage component 310, and the other end 320b of the second linkage component is rotatably connected to the second wing-shaped component 420.

[0038] The first wing-shaped component 410, the second wing-shaped component 420, the first link component 310, and the second link component 320 are each formed as a hinged connection structure and are rotatably connected to each other. Thus, when the drive unit 200 moves up and down, and the first link component 310 connected to the drive unit 200 moves up and down with the drive unit 200, the second link component 320, the first wing-shaped component 410, and the second wing-shaped component 420 interlock and rotate, thereby allowing the first wing-shaped component 410 and the second wing component 420 to fold or unfold.

[0039] Here, the guide groove 411 may be formed in a linear shape along the longitudinal direction in the first wing-shaped member 410, and the guide portion 311 connected to the guide groove 411 may be formed at the other end 310b of the first connecting rod member 310. That is, in the first wing-shaped member 410, the guide groove 411 may extend in a linear shape, and the guide portion 311 formed at the other end of the first connecting rod member 310 may be inserted into the guide groove 411 so as to be movable along the guide groove 411. The guide groove 411 may be formed to be recessed into the first wing-shaped member 410, and the groove may extend in the longitudinal direction on the opposite side of the recessed portion. In addition, the guide portion 311 may be formed in the first connecting rod member 310 to be inserted into the guide groove 411, and the guide portion may have a pin formed on its opposite side to be inserted into a corresponding groove in the guide groove 411. Therefore, the other end 310b of the first link member 310 can slide along the guide groove 411 in the first wing member 410 via the guide portion 311, and the other end of the first link member can rotate about the pin.

[0040] Therefore, in this disclosure, one end 310a of the first link member 310 is hingedly connected to the corresponding connecting portion 221 of the drive unit 200, and one end 410a of the first wing-shaped member 410 is hingedly connected to the housing 100. Here, the other end 310b of the first link member 310 is slidably and rotatably connected to the first wing-shaped member 410. Therefore, when the drive unit 200 moves up and down, one end 310a of the first link member 310 moves in the vertical direction and slides in the first wing-shaped member 410 while rotating the first wing-shaped member 410, and one end 410a of the first wing-shaped member is rotatably connected to the housing 100. At the same time, the rotational interlock between the second link member 320 and the first link member 310 causes the angle between the second link member 320 and the first link member 310 to change, and the second wing-shaped member 420 connected to the second link member 320 folds or unfolds while rotating relative to the first wing-shaped member 410.

[0041] In this way, depending on whether the drive unit 200 is operational, the first wing-shaped component 410 and the second wing-shaped component 420 can be deployed to form a thruster, or can be folded to cope with descent or reduce the space occupied by the thruster when storing aerial maneuvering equipment.

[0042] Meanwhile, a hinge connection portion 421 protruding from one end 420a of the second wing-shaped member 420 is connected to the other end 320b of the second link member 320. Furthermore, the hinge connection portion 421 is formed as a matching guide groove 411, and the hinge connection portion is inserted into the guide groove 411 when the wing-shaped unit 400 is deployed.

[0043] That is, the second wing-shaped member 420 is hingedly connected to the other end 320b of the second link member 320 via a hinge connection portion 421. Specifically, the hinge connection portion 421 has a protruding shape to allow connection to the second link member 320 and an appearance formed to match the guide groove 411, thereby inserting the hinge connection portion 421 into the guide groove 411 to form a support structure when the first wing-shaped member 410 and the second wing-shaped member 420 are deployed. Therefore, the support performance is improved when the first wing-shaped member 410 and the second wing-shaped member 420 are deployed.

[0044] Furthermore, the first link component 310 and the second link component 320 are formed into a matching guide groove 411, allowing the first link component 310 and the second link component 320 to be inserted into the guide groove 411 when the wing-shaped unit 400 is deployed. Therefore, when the first wing-shaped component 410 and the second wing-shaped component 420 are deployed, the first link component 310 and the second link component 320 are inserted into the guide groove 411, thereby forming a stable support structure. Additionally, since the first link component 310 and the second link component 320 are inserted into and engaged with the guide groove of the first wing-shaped component 410, the rigidity of the first link component 310 and the second link component 320 is ensured, thereby reducing vibration caused by rotation.

[0045] At the same time, such as Figure 1 As shown, a plurality of recessed receiving slots 120 are formed in the circumferential surface of the housing 100 to match the corresponding wing-shaped units 400, and slits 110 are formed in the corresponding receiving slots 120.

[0046] The number of receiving slots 120 formed in the housing 100 is the same as the number of connecting rod units 300 and wing units 400, and the receiving slots 120 are formed to match the corresponding wing units 400, such that when the wing units 400 are folded, the wing units 400 are inserted and placed in the corresponding receiving slots 120. Therefore, when the wing units 400 are folded, the amount of external protrusions of the wing units 400 is minimized because the wing units 400 are inserted and received in the corresponding receiving slots 120 in the housing 100, thus reducing the space used to store the wing units 400, and since the wing units 400 do not collide with the ground during descent, secondary accidents caused by debris are avoided.

[0047] Meanwhile, the drive unit 200 is configured to operate such that the wing unit is folded when a descent signal from the air maneuvering equipment is input to the drive unit.

[0048] That is, the drive unit 200 operates under the control of a controller, which uses various sensors installed in the aerial maneuvering device to collect information such as the altitude and tilt of the aerial maneuvering device to determine whether the aerial maneuvering device is descending. Therefore, when it is determined that the aerial maneuvering device is descending, the controller sends a signal related to the descent of the aerial maneuvering device to the drive unit 200 to activate the drive unit 200, causing the drive unit 200 to fold the wing unit 400. Thus, accidents caused by the wing unit 400 colliding with the ground and scattering debris from the wing unit 400, or by the wing unit 400 rotating, can be avoided.

[0049] In summary, the propulsion device of the aerial maneuvering equipment configured as described above can prevent accidents caused by the scattering of propulsion debris when the aerial maneuvering equipment descends, and can improve space utilization when storing the aerial maneuvering equipment.

[0050] Although this disclosure has been shown and explained with respect to specific embodiments thereof, it will be apparent to those skilled in the art that various modifications and alterations may be made to this disclosure without departing from the scope of the technical concept defined in the appended claims.

Claims

1. A propulsion device for an aerial maneuvering device, the propulsion device comprising: A housing having an internal space, wherein a plurality of slits are formed along the circumferential surface of the housing and extend in a vertical direction; A drive unit is configured to move vertically within the interior space of the housing, and the drive unit has a plurality of connecting portions formed to match corresponding slits among the plurality of slits in the housing; A plurality of linkage units are disposed outside the housing and configured to mate with corresponding slits among a plurality of slits in the housing, wherein each linkage unit is rotatably connected to the connecting portion of the drive unit; and Multiple wing-shaped units are rotatably mounted to the housing, each wing-shaped unit is connected to a linkage unit, and the wing-shaped units are configured to rotate in association with the linkage unit. The wing-shaped units rotate as the drive unit moves up and down, thereby being folded into or unfolded from the housing. Each of the plurality of linkage units includes a plurality of linkage components that are rotatably connected to each other, and Each of the plurality of wing-shaped units includes a plurality of wing-shaped components, which are rotatably connected to corresponding link components in the plurality of link components and are rotatably connected to each other; Each of the plurality of wing-shaped units includes a first wing-shaped component and a second wing-shaped component. One end of the first wing-shaped component is rotatably connected to the housing, and the second wing-shaped component is rotatably connected to the other end of the first wing-shaped component. The first wing-shaped component and the second wing-shaped component are rotatably connected to the plurality of link components of one of the plurality of link units. Furthermore, each of the linkage units includes a first linkage component and a second linkage component. One end of the first linkage component is rotatably connected to one of the plurality of connecting parts, and the other end of the first linkage component is slidably and rotatably connected to the first wing-shaped component. One end of the second linkage component is rotatably connected to the other end of the first linkage component, and the other end of the second linkage component is rotatably connected to the second wing-shaped component.

2. The propeller device of claim 1, wherein, The drive unit includes: an actuator configured to generate power; and a drive rod configured to move up and down by receiving power from the actuator, wherein the drive rod extends such that the plurality of connecting portions arranged circumferentially along the drive rod mate with corresponding slits among the plurality of slits in the housing.

3. The thruster apparatus of claim 1, wherein, The first wing-shaped member includes a guide groove formed in a linear shape along the longitudinal direction of the first wing-shaped member, and the first link member includes a guide portion formed at the other end of the first link member to connect to the guide groove.

4. The thruster device according to claim 3, wherein, The second wing-shaped component includes a hinge connection portion that protrudes from one end of the second wing-shaped component to connect to the other end of the second linkage component, and, The hinge connection is formed to match the guide groove, and the hinge connection is inserted into the guide groove when the wing unit is deployed.

5. The propulsion device according to claim 3, wherein, The first link component and the second link component are configured to mate with the guide slot, and when the wing-shaped unit is deployed, the first link component and the second link component are inserted into the guide slot.

6. The thruster device according to claim 1, wherein, Multiple recessed receiving slots are formed in the circumferential surface of the housing to match the corresponding wing-shaped units, and the slit is formed in each of the multiple receiving slots.

7. The thruster device according to claim 1, wherein, The drive unit is configured to operate such that the wing unit is folded when a descent signal is input to the drive unit according to the aerial maneuvering equipment.

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