Telescoping propeller apparatus for aerial maneuvering vehicles

Abstract

A retractable propeller device for an airborne vehicle has a structure that allows the propeller to be exposed or concealed depending on whether the airborne vehicle is in high-speed flight or parked. Specifically, the retractable propeller device includes: a base having a mounting member with a space; a propeller unit disposed on the mounting member and configured to generate airflow; a cover configured to close the space and movable vertically relative to the mounting member; and a lifting unit disposed on the mounting member and connected to the cover, configured to move the cover. The cover selectively closes or opens the space based on the operation of the lifting unit, making the propeller unit operable.

Description

Technical Field

[0001] This disclosure generally relates to a retractable propeller device for an airborne motor vehicle, and more specifically, to a retractable propeller device for an airborne motor vehicle having a structure that allows the propeller to be exposed or concealed depending on whether the airborne motor vehicle is in high-speed flight or parked. Background Technology

[0002] The statements in this section are provided only as background information in relation to this disclosure and may not constitute prior art.

[0003] Recently, the development of air-mobile vehicles for various purposes (such as freight or medical transport) has been underway. Air-mobile vehicles are entering the practical application stage due to their increased energy efficiency and reliability.

[0004] This type of airborne vehicle flies by operating propellers, which also enables takeoff and landing. Takeoff and landing require significantly more thrust and higher propeller speeds compared to flight. Conversely, when the airborne vehicle is in flight, some of the propeller operations required for vertical takeoff are no longer needed. In particular, when the airborne vehicle is flying at high speeds, the propellers generate air resistance, resulting in energy loss during flight.

[0005] The foregoing is intended only to help understand the background of this disclosure and is not intended to imply that this disclosure falls within the scope of related technologies known to those skilled in the art. Summary of the Invention

[0006] This disclosure proposes a retractable propeller device for an airborne vehicle, having a structure that allows the propeller to be exposed or concealed depending on whether the airborne vehicle is in high-speed flight or parked. Therefore, the propeller can be effectively used in various flight situations to improve energy efficiency and thereby increase the ferry range of the airborne vehicle.

[0007] In one aspect of this disclosure, a retractable propeller device for an airborne motor vehicle includes: a base extending in a longitudinal direction, including a mounting member disposed in a portion thereof, the mounting member having a space through which air flows; a propeller unit disposed on the mounting member to generate airflow in a vertical direction; a cover configured to close the space and movable relative to the mounting member in a vertical direction; and a lifting unit disposed on the mounting member and connected to the cover, wherein the lifting unit, according to its operation, moves the cover such that the cover closes or opens the space, making the propeller unit operable.

[0008] The mounting components may include an upper mounting component and a lower mounting component respectively disposed on the upper and lower parts of the space, such that the upper mounting component and the lower mounting component are spaced apart from each other, and the propeller unit may be disposed between and inside the upper mounting component and the lower mounting component.

[0009] The cover may include an upper cover and a lower cover, the upper cover being configured to be movable outside the upper mounting member via an upper lifting unit, and the lower cover being configured to be movable outside the lower mounting member via a lower lifting unit.

[0010] The top and bottom covers can be configured to separate from each other in the vertical direction and detach from the base.

[0011] The mounting element may include multiple blocking surfaces and multiple through holes that are repeatedly formed along its longitudinal direction. The cover may include multiple closing surfaces and multiple through holes that are repeatedly formed along its longitudinal direction.

[0012] The mounting element may include a mounting portion disposed on its longitudinal central portion, wherein the propeller unit is disposed on the mounting portion. A blocking surface and through-holes may be repeatedly formed on the mounting element relative to the mounting portion in the longitudinal direction.

[0013] The blocking surface of the mounting and the closing surface of the cover can have the same shape as the outer portion of the base.

[0014] The blocking surface of the mounting piece can match the through hole of the cover, the through hole of the mounting piece can match the closing surface of the cover, the blocking surface and the through hole can have the same shape, and the through hole and the closing surface can have the same shape.

[0015] The cover may have multiple support portions that extend longitudinally to contact the side surface of the mounting element, thereby maintaining contact with the mounting element.

[0016] The support portion may be a pair of support members that contact the two side surfaces of the mounting member, and the mounting member may include a reinforcing portion disposed on the portion of it that contacts the support portion.

[0017] The lifting unit may include: a first linkage unit comprising a plurality of zigzag-connected linkage members and pivotally connected to a mount and a cover; a second linkage unit comprising a plurality of zigzag-connected linkage members pivotally connected to the mount and cover at locations spaced apart from the locations where the first linkage unit is connected to the mount and cover, so as to intersect with the first linkage unit; and an actuator comprising a first end and a second end, the first end being connected to a first linkage member of the plurality of first linkage members of the first linkage unit connected to the mount, and the second end being connected to a second linkage member of the plurality of second linkage members of the second linkage unit connected to the cover, wherein the length of the actuator is variable in its longitudinal direction.

[0018] The base can be extended to connect to individual wings of airborne vehicles.

[0019] The propeller unit may include a drive motor mounted on a mounting and a plurality of propeller blades connected to the drive motor to rotate by receiving rotational power from the drive motor. The propeller blades may be a pair of blades arranged to extend linearly from the drive motor.

[0020] The cover can be configured to cover the drive motor and propeller blades.

[0021] In the retractable propeller device of an airborne vehicle with the above-described structure, the propeller can be exposed or concealed depending on whether the airborne vehicle is in high-speed flight or parked. Therefore, the propeller can be effectively used in various flight situations to improve energy efficiency and thus increase the continuous unloaded range of the airborne vehicle.

[0022] Other application areas will become apparent from the description provided herein. It should be understood that this description and specific examples are intended for illustrative purposes only and are not intended to limit the scope of this disclosure. Attached Figure Description

[0023] In order to make this disclosure well understood, its various forms will now be described with reference to the accompanying drawings, which are given by way of example, wherein:

[0024] Figure 1 This is a view showing a retractable propeller device of an airborne motor vehicle according to an exemplary form of this disclosure;

[0025] Figure 2 and Figure 3 It shows Figure 1 A view of the retractable propeller device of an airborne vehicle in its retracted state;

[0026] Figure 4 It shows Figure 1 An assembly diagram of the retractable propeller device for an airborne mobile vehicle;

[0027] Figure 5 It shows Figure 1 A cross-sectional view of the retractable propeller device of the airborne motor vehicle shown;

[0028] Figure 6 It shows Figure 1 A view of the lifting unit of the retractable propeller device of the shown airborne motor vehicle;

[0029] Figure 7 and Figure 8 It shows Figure 1A view showing the operational status of the retractable propeller device of an airborne vehicle; and

[0030] Figure 9 It shows Figure 1 A view showing the deployed state of the retractable propeller device of an aerial motor vehicle.

[0031] The accompanying drawings described herein are for illustrative purposes only and are not intended to limit the scope of this disclosure in any way. Detailed Implementation

[0032] The following description is exemplary in nature only and is not intended to limit this disclosure, its application, or its use. It should be understood that in all the drawings, corresponding reference numerals denote the same or corresponding parts and features.

[0033] In the following, a retractable propeller device of an exemplary form of an airborne motor vehicle according to the present disclosure will be described in detail with reference to the accompanying drawings.

[0034] Figure 1 This is a view showing a retractable propeller device of an airborne motor vehicle according to one form of the present disclosure. Figure 2 and Figure 3 It shows Figure 1 A view showing the retractable propeller assembly of an airborne vehicle in its retracted state. Figure 4 It shows Figure 1 The diagram shows an assembly of a retractable propeller device for an aerial motor vehicle. Figure 5 It shows Figure 1 The diagram shows a cross-sectional view of the retractable propeller device of an airborne vehicle. Figure 6 It shows Figure 1 A view of the lifting unit of the retractable propeller device of an aerial motor vehicle. Figure 7 and Figure 8 It shows Figure 1 A view showing the operational status of the retractable propeller device of an airborne mobile vehicle, and Figure 9 It shows Figure 1 A view showing the deployed state of the retractable propeller device of an aerial motor vehicle.

[0035] like Figures 1 to 4As shown, the retractable propeller device of the air-mobile vehicle M includes: a base 100 extending longitudinally and including a mounting member 110 disposed in a portion thereof, on which an airflow space S is provided; a propeller unit 200 disposed on the mounting member 110 to generate an airflow in a vertical direction; a cover 300 configured to enclose (or seal) the space S and movable relative to the mounting member 110 in a vertical direction; and a lifting unit 400 disposed on the mounting member 110 and connected to the cover 300, wherein the lifting unit 400 moves the cover 300 according to its operation, such that the cover 300 encloses or opens the space S, thereby making the propeller unit 200 operable. Here, each of the propeller unit 200 and the lifting unit 400 can be operated under the control of a controller (not shown).

[0036] The airborne vehicle M according to this disclosure is capable of vertical takeoff and landing, and includes a wing M1 that generates thrust during high-speed flight and a base 100 that serves as a support structure for connecting the wing. Therefore, the base 100 can extend to connect individual wings of the airborne vehicle M. A mounting member 110 is disposed on a portion of the base 100, and a propeller unit 200, a cover 300, and a lifting unit 400 are disposed on the mounting member 110.

[0037] In other words, the propeller unit 200 is mounted on the space S of the base 100 via the mounting member 110, and the space S is selectively opened or closed by the cover 300, which is movable by the lifting unit 400. The base 100 is a support structure connecting the plurality of wings. The propeller unit 200, which generates airflow to the mounting member 110, is mounted on the base 100 such that the operation of the propeller unit 200 generates thrust that enables the airborne vehicle to fly vertically. The propeller unit 200 may include a drive motor 210 mounted on the mounting member 110 and a plurality of propeller blades 220 connected to the drive motor 210 to rotate by receiving rotational power from the drive motor 210. In one embodiment of this disclosure, the mounting member 110 extends longitudinally, and the propeller blades are configured as a pair of propeller blades that extend linearly from the drive motor 210, such that the propeller blades can be retracted through the mounting member 110 and the cover 300.

[0038] Here, the position of the cover 300, which is mounted on the mounting member 110 of the base 100, can be moved vertically by the lifting unit 400. In this way, the cover 300 can close the space S to hide (i.e., retract) the propeller unit 200 or open the space S to expose (i.e., deploy) the propeller unit 200 for operation. The cover 300 is configured to cover the drive motor 210 and the propeller blades 220, thereby forming a closed structure (or sealed structure) that protects the drive motor 210 and the propeller blades 220 when the cover 300 closes the space S. Therefore, the portion of the cover 300 adjacent to the relatively large drive motor 210 can be made wider. When the airborne vehicle M is flying at high speed, the cover 300 closes the space S, hiding the propeller unit 200. Therefore, the increase in air resistance caused by the propeller blades 220 can be prevented, thereby enabling the airborne vehicle M to fly effectively. Furthermore, during the vertical flight of the airborne vehicle M, the cover 300 opens the space S, exposing the propeller unit 200. Therefore, the propeller unit 200 can be driven, enabling the airborne vehicle M to take off and land.

[0039] Exemplary forms of this disclosure will be described in more detail below. For example... Figure 4 As shown, the mounting member 110 includes an upper mounting member 110a and a lower mounting member 110b respectively disposed on the upper and lower parts of the space S, such that the upper mounting member 110a and the lower mounting member 110b are spaced apart from each other. The propeller unit 200 may be disposed between and inside the upper mounting member 110a and the lower mounting member 110b.

[0040] In other words, since the mounting member 110 includes an upper mounting member 110a and a lower mounting member 110b spaced apart from each other in the vertical direction, the strength of the base 100 can be obtained, thereby preventing a reduction in strength due to the provision of space S. In particular, since the propeller unit 200 is disposed between the upper mounting member 110a and the lower mounting member 110b and is fixedly disposed by the upper mounting member 110a and the lower mounting member 110b, the stability provided by the propeller unit 200 can be provided.

[0041] like Figure 3 As shown, cover 300 may include an upper cover 300a and a lower cover 300b. The upper cover 300a is configured to be movable outside the upper mounting member 110a via the upper lifting unit 400a. The lower cover 300b is configured to be movable outside the lower mounting member 110b via the lower lifting unit 400b.

[0042] In this manner, cover 300 includes an upper cover 300a and a lower cover 300b, while lifting unit 400 includes an upper lifting unit 400a and a lower lifting unit 400b. That is, the upper cover 300a is disposed on the upper mounting member 110a, allowing it to move via the upper lifting unit 400a. The lower cover 300b is disposed on the lower mounting member 110b, allowing it to move via the lower lifting unit 400b. Therefore, the upper cover 300a and the lower cover 300b can move vertically, thereby opening and closing the space S of the base 100.

[0043] Here, the upper cover 300a and the lower cover 300b can be configured to be detached from the base 100 in the vertical direction. Therefore, when the upper cover 300a and the lower cover 300b enclose the space S, they are coplanar with the base 100, thereby reducing air resistance during flight. That is, as... Figure 3 As shown, when the base 100 is circular, each of the upper cover 300a and the lower cover 300b is semi-circular. When the upper cover 300a and the lower cover 300b enclose the space S, the upper cover 300a and the lower cover 300b are circular like the base 100, so that their outer surfaces are smoothly aligned with the outer surface of the base 100.

[0044] Mounting member 110 has a plurality of blocking surfaces 111 and a plurality of through holes 112 that are repeatedly formed along its longitudinal direction. Cover 300 may have a plurality of closing surfaces 310 and a plurality of through holes 320 that are repeatedly formed along its longitudinal direction.

[0045] like Figure 3 and Figure 4 As shown, the mounting member 110 has through holes 112 that are perforated therein and spaced apart from each other in the longitudinal direction, allowing air to flow through them in the vertical direction. A blocking surface 111 is configured to alternate with the through holes 112. The cover 300 has through holes 320 that are perforated therein and spaced apart from each other in the longitudinal direction, allowing air to flow through them in the vertical direction. A sealing surface 310 is configured to alternate with the through holes 320. When the cover 300 is open, a channel through which air can flow in the vertical direction is formed by the through holes 320 of the cover 300 and the through holes 112 of the mounting member 110, allowing air to pass through the cover 300 and the mounting member 110 during operation of the propeller unit 200. Therefore, operation of the propeller unit 200 can provide a certain amount of airflow, thereby improving the flight performance obtained by the propeller unit 200.

[0046] Here, the mounting portion 113 on which the propeller unit 200 is disposed is located in the longitudinal center portion of the mounting member 110. The blocking surface 111 and the through hole 112 are repeatedly formed relative to the mounting portion 113 in the longitudinal direction.

[0047] In this manner, the mounting portion 113 is disposed in the longitudinal center portion of the mounting member 110, thereby securely mounting the propeller unit 200. The mounting portion 113 can be configured to match the shape of the upper or lower part of the propeller unit 200, thereby securely mounting the propeller unit 200. Furthermore, since the mounting portion 113 is disposed in the longitudinal center portion of the mounting member 110, the load caused by the placement of the propeller unit 200 is evenly distributed, and space is readily available for the propeller unit 200 to operate therein. Since the blocking surface 111 and the through hole 112 are repeatedly disposed on both sides of the mounting portion 113, the propeller unit 200 can be securely mounted, and the airflow generated by the propeller unit 200 can flow through the through hole 112.

[0048] Additionally, the blocking surface 111 of the mounting member 110 can mate with the through hole 320 of the cover 300. The through hole 112 of the mounting member 110 can mate with the closing surface 310 of the cover 300. The blocking surface 111 and the through hole 320 can have the same shape, and the through hole 112 and the closing surface 310 can have the same shape.

[0049] In other words, the blocking surface 111 of the mounting member 110 matches the through hole 320 of the cover 300 in the vertical direction, and the through hole 112 of the mounting member 110 matches the closing surface 310 of the cover 300 in the vertical direction. Therefore, when the cover 300 moves toward the mounting member 110 to close the space S, the blocking surface 111 of the mounting member 110 matches the through hole 320 of the cover 300, thereby closing the through hole 320. Even when the through hole 320 is formed in the cover 300 as described above, the blocking surface 111 that matches the through hole 320 can close the through hole 320, thereby forming a closed space S in which the outer surface of the cover 300 extends smoothly. In addition, since the closing surface 310 of the cover 300 matches the through hole 112 of the mounting member 110, a structure that closes the cover 300 and the mounting member 110 can be provided.

[0050] In other words, when the cover 300 is open, air flows vertically through the through-hole 320 of the cover 300 and the through-hole 112 of the mounting member 110. When the cover 300 is closed, the outer surface extends smoothly due to the closing surface 310 of the cover 300 and the blocking surface 111 of the mounting member 110.

[0051] In this respect, the blocking surface 111 and the through hole 320 can have the same shape, and the through hole 112 and the closing surface 310 can have the same shape. The blocking surface 111 of the mounting member 110 and the closing surface 310 of the cover 300 can have the same shape as the peripheral portion of the base 100. Therefore, when the cover 300 closes the space S, the cover 300 and the mounting member 110 can close the space S. Since the blocking surface 111 of the mounting member 110 and the closing surface 310 of the cover 300 have the same shape, the outer surface can have a shape that is smoothly aligned with the base 100.

[0052] In addition, such as Figure 4 and Figure 5 As shown, the cover 300 may have multiple support portions 330 extending longitudinally to contact the side surface of the mounting member 110, thereby maintaining contact with the mounting member 110. Since the support portions 330 of the cover 300 contact the mounting member 110 in this manner, the cover 300 can be supported to the mounting member 110 via the support portions 330, thus reliably maintaining its position. That is, when the cover 300 moves to the open position of the mounting member 110, wind force generated by the flight of the airborne vehicle M can be applied to the cover 300, causing the cover 300 to vibrate. Conversely, according to this disclosure, maintaining the contact between the cover 300 and the mounting member 110 via the support portions 330 reduces vibration and maintains a stable supported state. Furthermore, when the cover 300 moves via the lifting unit 400, this movement is guided by the support portions 330, enabling reliable movement operations.

[0053] A pair of support portions 330 are provided on the inner periphery of the cover 300 to contact the two side surfaces of the mounting member 110. Furthermore, the number and thickness of the support portions 330 can be adjusted according to the mobility reliability and support performance of the cover 300.

[0054] Mounting member 110 may have a reinforcing portion 114 formed on its portion that contacts the support portion 330. Multiple reinforcing portions 114 may be arranged along the longitudinal direction of mounting member 110 and extend in the same direction as the blocking surface 111, thereby increasing the strength of mounting member 110. Furthermore, the reinforcing portions 114 are formed in the portion of mounting member 110 that contacts the support portion 330, thereby increasing the strength of vulnerable portions susceptible to contact with the support portion 330.

[0055] The lifting unit 400 may include a first linkage unit 410, a second linkage unit 420, and an actuator 430. The first linkage unit 410 includes a plurality of zig-connected linkage members and is pivotally connected to the mount 110 and the cover 300. The second linkage unit 420 includes a plurality of zig-connected linkage members pivotally connected to the mount 110 and the cover 300 at locations spaced apart from the locations where the first linkage unit 410 is connected to the mount 110 and the cover 300, so as to intersect with the first linkage unit 410. The actuator 430 is configured such that one end is connected to the linkage member of the first linkage unit 410 connected to the mount 110, and the other end is connected to the linkage member of the second linkage unit 420 connected to the cover 300, and its length is variable in its longitudinal direction.

[0056] like Figure 6 As shown, the lifting unit 400 includes a first linkage unit 410 and a second linkage unit 420, each composed of multiple linkage members, wherein an actuator 430 is connected to the first linkage unit 410 and the second linkage unit 420. Specifically, the first linkage unit 410 is configured such that its multiple linkage members are pivotally connected in a zigzag pattern to form a hinge structure, and the linkage members at its two ends are pivotally connected to the mounting member 110 and the cover 300, respectively. Similarly, the second linkage unit 420 is configured such that its multiple linkage members are pivotally connected in a zigzag pattern to form a hinge structure, and the linkage members at its two ends are pivotally connected to the mounting member 110 and the cover 300 at positions different from those of the first linkage unit 410. Therefore, the first linkage unit 410 and the second linkage unit 420 form a structure that supports the cover 300 relative to the mounting member 110. The connection structure of the first linkage unit 410 and the second linkage unit 420 achieves strength. The lengths of the first linkage unit 410 and the second linkage unit 420 can be adjusted vertically via an actuator 430 connected thereto. The actuator 430 can be a linear actuator capable of changing its length through linear motion. Therefore, the cylinder 430a of the actuator 430 is connected to the linkage member of the first linkage unit 410 connected to the mounting member 110, and the piston 430b of the actuator 430 is connected to the linkage member of the second linkage unit 420 connected to the cover 300. When the length of the actuator 430 changes, the first linkage unit 410 and the second linkage unit 420 can unfold or fold (or retract) vertically, thereby raising or lowering the cover 300. The lifting unit 400 can raise or lower the cover 300 solely through the operation of the actuator 430. Various methods, such as rack and pinion structures or gear structures, can be used to achieve the operation of raising or lowering the cover 300.

[0057] The operation of raising or lowering cover 300 according to one form of this disclosure will now be described.

[0058] When cover 300 closes space S, cover 300 moves toward mounting member 110 to close space S, so that propeller unit 200 is also hidden, and cover 300 is smoothly aligned with base 100, as... Figure 2 and Figure 7 As shown. Therefore, during high-speed flight, the increase in air resistance caused by the propeller blades 220 can be prevented, thereby enabling the airborne motor vehicle M to fly effectively.

[0059] Furthermore, when the cover 300 opens the space S, the operation of the lifting unit 400 enables the cover 300 to be raised or lowered, such as... Figure 8 and Figure 9 As shown above, when the cover 300 opens the space S, the propeller unit 200 is exposed, and the propeller blades 220 of the propeller unit 200 are provided in a space in which they can rotate, so that flight can be achieved by rotating the propeller blades 220.

[0060] Furthermore, during the opening of the cover 300, a channel for air to flow vertically is formed by the through-hole 320 of the cover 300 and the through-hole 112 of the mounting member 110, allowing air to pass through the cover 300 and the mounting member 110 during the operation of the propeller unit 200. Therefore, the operation of the propeller unit 200 can provide a certain amount of airflow, thereby improving the flight performance obtained by the propeller unit 200. This can be used during the vertical flight of the airborne vehicle M. The airborne vehicle M can take off or land due to the operation of the propeller unit 200.

[0061] As described above, the retractable propeller device of the airborne vehicle M has the aforementioned structure, allowing the propeller to be exposed or concealed depending on whether the airborne vehicle is in a high-speed flight position or a parked position. Therefore, the propeller can be effectively used in various flight situations to improve energy efficiency, thereby increasing the airborne vehicle's continuous ferry range.

[0062] Although exemplary forms of this disclosure have been described for illustrative purposes, those skilled in the art will understand that various modifications, additions, and substitutions are possible without departing from the scope and spirit of this disclosure.

Claims

1. A retractable propeller device for an air-mobile vehicle, the retractable propeller device comprising: A base extending in a longitudinal direction includes a mounting member disposed in a portion of the base, wherein the mounting member is provided with a space through which air flows; A propeller unit is mounted on the mounting and configured to generate airflow in the vertical direction; A cover, configured to enclose the space and movable relative to the mounting member in the vertical direction; and A lifting unit is disposed on the mounting member and connected to the cover, and is configured to move the cover. The cover is configured to selectively close or open the space based on the operation of the lifting unit, so that the propeller unit can operate; The mounting component includes a plurality of blocking surfaces and a plurality of through holes repeatedly formed along its longitudinal direction, and the cover includes a plurality of closing surfaces and a plurality of through holes repeatedly formed along its longitudinal direction; and The plurality of blocking surfaces of the mounting component match the plurality of through holes of the cover, the plurality of through holes of the mounting component match the plurality of closing surfaces of the cover, the plurality of blocking surfaces and the plurality of through holes of the cover have the same shape, and the plurality of through holes and the plurality of closing surfaces of the mounting component have the same shape.

2. The retractable propeller device according to claim 1, wherein: The mounting components include an upper mounting component and a lower mounting component respectively disposed on the upper and lower parts of the space, such that the upper mounting component and the lower mounting component are spaced apart from each other, and The propeller unit is disposed between the upper mounting component and the lower mounting component and is located inside the upper mounting component and the lower mounting component.

3. The retractable propeller device according to claim 2, wherein, The cover includes an upper cover and a lower cover, the upper cover being configured to be moved to the outside of the upper mounting member via an upper lifting unit, and the lower cover being configured to be moved to the outside of the lower mounting member via a lower lifting unit.

4. The retractable propeller device according to claim 3, wherein, The upper cover and the lower cover are configured to be detachable from each other along the vertical direction and from the base.

5. The retractable propeller device according to claim 1, wherein: The mounting component includes a mounting portion disposed on its longitudinal central portion, wherein the propeller unit is disposed on the mounting portion. The plurality of through holes and the plurality of blocking surfaces of the mounting member are repeatedly formed on the mounting member relative to the mounting portion along the longitudinal direction.

6. The retractable propeller device according to claim 1, wherein, The plurality of blocking surfaces of the mounting element and the plurality of closing surfaces of the cover have the same shape as the peripheral portion of the base.

7. The retractable propeller device according to claim 1, wherein, The cover has a plurality of support portions that extend along the longitudinal direction to contact the side surface of the mounting member, thereby maintaining contact with the mounting member.

8. The retractable propeller device according to claim 7, wherein: The plurality of support portions include a pair of support members that contact the side surface of the mounting member, and The mounting component includes a reinforcing portion disposed on the portion of the mounting component that contacts the plurality of support portions.

9. The retractable propeller device according to claim 1, wherein, The lifting unit includes: The first linkage unit includes a plurality of first linkage members connected to each other in a zigzag pattern and is pivotally connected to the mounting and the cover; The second linkage unit includes a plurality of second linkage members connected to each other in a zigzag pattern, pivotally connected to the mounting and the cover at positions spaced apart from where the first linkage unit is connected to the mounting and the cover, so as to intersect with the first linkage unit; and Actuator, including: The first end, connected to the first link member of the plurality of first link members of the first link unit, and the first link member connected to the mounting member, and The second end is connected to the second link member of the plurality of second link members of the second link unit that is connected to the cover, wherein the length of the actuator is variable in its longitudinal direction.

10. The retractable propeller device according to claim 1, wherein, The base extends to connect to the individual wings of the airborne vehicle.

11. The retractable propeller device according to claim 1, wherein, The propeller unit includes: A drive motor is mounted on the mounting component, and Multiple propeller blades are connected to the drive motor and configured to rotate by receiving rotational power from the drive motor. The plurality of propeller blades includes a pair of propeller blades arranged to extend linearly from the drive motor.

12. The retractable propeller device according to claim 11, wherein, The cover is configured to cover the drive motor and the plurality of propeller blades.

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