KR102816010B1 - Foldable propeller structure, gas turbine engines and aircraft including the same, and control method of foldable propeller structure - Google Patents

Abstract

In one embodiment of the present invention, a foldable propeller structure may include: a shaft; a hub connected to one axial side of the shaft; and a plurality of blades connected to the hub at a circumferential interval with respect to the hub, wherein each of the plurality of blades is hinge-connected to the hub so as to be able to switch between a deployed state in which the blades are radially spread out from the hub and a folded state in which the blades are folded closer to the shaft than the deployed state; and a shaft drive unit connected to the shaft so as to provide a driving force for moving the shaft in the axial direction; and a blade drive unit connected to the plurality of blades so as to provide a driving force for switching the plurality of blades to either one of the deployed state and the folded state.

Description

FOLDABLE PROPELLER STRUCTURE, GAS TURBINE ENGINES AND AIRCRAFT INCLUDING THE SAME, AND CONTROL METHOD OF FOLDABLE PROPELLER STRUCTURE}

The present invention relates to a foldable propeller structure, a gas turbine engine and aircraft including the same, and a control method for the foldable propeller structure.

The research and development related to this invention was carried out with the support of the Korea Foundation for Advanced Studies' University Key Research Institute Support Project "Development of Future Aircraft Technology using Carbon Materials" project (KIS project number 202200610001, subproject number 2022R1A6A1A03056784, total research period 2022.06. 01 ~ 2031.05. 31) hosted by the Aerospace Industry Technology Research Institute of Korea Aerospace University.

The propeller, which is a device that converts the engine's rotational power into thrust in an aircraft, requires greater thrust and more propeller use during takeoff and landing than during flight. On the other hand, when an aircraft enters flight mode, it is possible to fly by the lift of the wings, and when the aircraft's flight speed reaches the speed of sound, a shock wave is generated in the propeller, which causes a rapid decrease in efficiency, which is a problem.

To solve these problems, foldable propellers are being developed.

However, existing folding propellers had blades that simply folded horizontally or vertically relative to the plane of rotation, and there was a problem in that the blades were exposed to the outside even when folded, which caused air resistance.

The background technology of this application is disclosed in Korean Patent Publication No. 10-2022-0056573.

The present invention is intended to solve the problems of the above-mentioned prior art, and aims to provide a foldable propeller structure in which the propeller can be folded and stored inside an airframe and a propulsion device and then deployed again to generate thrust, a gas turbine engine and aircraft including the same, and a control method for the foldable propeller structure.

However, the technical tasks to be achieved by the embodiments of the present invention are not limited to the technical tasks described above, and other technical tasks may exist.

As a technical means for achieving the above technical task, a foldable propeller structure according to one embodiment of the present invention may include: a shaft; a hub connected to one axial side of the shaft; and a plurality of blades connected to the hub at a circumferential interval relative to the hub, wherein each of the plurality of blades is hinge-connected to the hub so as to be able to switch between a deployed state in which the blades are radially spread out from the hub and a folded state in which the blades are folded closer to the shaft than the deployed state; and a shaft drive unit connected to the shaft so as to provide a driving force for moving the shaft along the axial direction; and a blade drive unit connected to the plurality of blades so as to provide a driving force for switching the plurality of blades to either one of the deployed state and the folded state.

In addition, the blade driving unit may include a blade moving block installed to surround the outer circumference of the shaft; a first screw member that is arranged adjacent to the shaft and extends in the axial direction and is screw-connected to the blade moving block to move the blade moving block in the axial direction in response to rotation of the member; a blade driving unit provided to rotate the first screw member; and a plurality of link members that connect the blade moving block and each of the plurality of blades, such that switching to either the unfolded state or the folded state is possible according to the axial movement of the blade moving block.

In addition, the shaft drive unit may include a worm gear installed to surround the outer circumference of the shaft so as to be axially moved in conjunction with the shaft; a rack gear gear-engaged with the worm gear so that the worm gear moves in the axial direction in response to rotation; and a shaft drive unit provided to rotate the worm gear.

In addition, the worm gear is installed relative to the shaft so as to have a rotational degree of freedom that is not coupled with the shaft, the blade drive unit is arranged relative to the worm gear so as to be coupled with the axial movement of the worm gear, and when the propeller is rotated in the unfolded state of the foldable propeller structure, the shaft drive unit is provided so as to be not coupled with the propeller rotation drive, the blade moving block and the plurality of link members among the blade drive units are provided so as to be coupled with the propeller rotation drive, and the first screw member and the blade drive unit among the blade drive units can be provided so as to be not coupled with the propeller rotation drive.

In addition, the shaft driving unit may include a shaft moving block installed to surround the outer circumference of the shaft so as to be axially moved in conjunction with the shaft; a second screw member that is arranged parallel to the shaft as a member extending in the axial direction, but is arranged at a preset interval from the first screw member and further from the shaft than the first screw member, and is screw-connected to the shaft moving block so as to move the shaft moving block in the axial direction in response to rotation of the member; and a shaft driving unit that is provided to rotate the second screw member.

In addition, the foldable propeller structure includes an integrated driving unit provided to selectively perform either an operation as the blade driving unit or an operation as the shaft driving unit, the integrated driving unit comprising: an integrated driving unit providing a rotational driving force for a rotational axis orthogonal to an axial direction of the shaft, the rotational axis being arranged to protrude toward the shaft side; an inner bevel gear mounted so as to face inwardly on the shaft side with respect to the rotational axis of the integrated driving unit; an outer bevel gear mounted so as to face outwardly on the opposite side of the shaft side with respect to the rotational axis of the integrated driving unit; a first spur gear provided to have the same rotational axis as the first screw member; a second spur gear disposed on one axial side of the shaft moving block and gear-engaged with the first spur gear; And a bevel gear for blade deployment arranged on one axial side of the second spur gear so as to have the same rotation axis as the second spur gear, and when the inner bevel gear is coupled with the bevel gear for blade deployment, the integrated driving unit can perform an operation as the blade driving unit.

In addition, the integrated driving unit includes a shaft moving bevel gear provided on one axial side of the second screw member to have the same rotational axis as the second screw member, and when the outer bevel gear is coupled with the shaft moving bevel gear, the integrated driving unit can perform an operation as the shaft driving unit.

In addition, the second spur gear and the bevel gear for blade deployment, and the inner bevel gear and the outer bevel gear are arranged with respect to the preset interval section, wherein the inner bevel gear and the outer bevel gear are arranged outside the second spur gear and the bevel gear for blade deployment, and the integrated driving unit may include an actuator that is provided to linearly move the integrated driving unit to which the inner bevel gear and the outer bevel gear are mounted in a interval direction corresponding to the preset interval among directions orthogonal to the axial direction of the shaft.

In addition, the preset interval may be set such that when the integrated drive unit is linearly moved inward by the actuator, when viewed in the axial direction, the inner bevel gear and the bevel gear for blade deployment are positioned at positions where bevel gear engagement is possible, and the outer bevel gear and the bevel gear for shaft movement are positioned at positions where bevel gear engagement is released, and when the integrated drive unit is linearly moved outward by the actuator, when viewed in the axial direction, the inner bevel gear and the bevel gear for blade deployment are positioned at positions where bevel gear engagement is released, and the outer bevel gear and the bevel gear for shaft movement are positioned at positions where bevel gear engagement is possible.

In addition, the bevel gear for moving the shaft may be provided at an axial position where the bevel gear engagement with the outer bevel gear may be formed when the integrated drive unit moves linearly in the outward direction, and the bevel gear for unfolding the blades may be provided at an axial position where the bevel gear engagement with the inner bevel gear may be formed only when the shaft has moved a preset distance in one axial direction, so that the plurality of blades can maintain the folding state until the shaft has moved a preset distance in one axial direction.

In addition, the preset distance is set in consideration of the fact that, for an aircraft to which the foldable propeller structure is applied, the foldable propeller structure is converted from an internally stowed state to an externally protruding state, and the externally protruding state may include a state in which at least a portion of the foldable propeller structure protrudes externally so that the plurality of blades can be converted from the folded state to the deployed state.

Additionally, the external protrusion state may include a state in which the plurality of blades are placed in the deployed state and then the foldable propeller structure is re-moved axially to the other side within a limit in which the propeller rotation drive of the plurality of blades is possible.

Additionally, a gas turbine engine according to one embodiment of the present invention may include a foldable propeller structure according to one embodiment of the present invention.

Additionally, an aircraft according to one embodiment of the present invention may include a foldable propeller structure according to one embodiment of the present invention.

In addition, a method for controlling a foldable propeller structure according to one embodiment of the present invention may include: (a) a step of moving the shaft and the propeller to one side in the axial direction; and (b) a step of converting the plurality of blades from the folded state to the unfolded state.

In addition, (c) the step (b) may include a step of re-moving the foldable propeller structure to the other axial direction within a limit in which the propeller rotation driving of the plurality of blades is possible after the plurality of blades are placed in the deployed state.

The above-described problem solving means are merely exemplary and should not be construed as limiting the present invention. In addition to the above-described exemplary embodiments, additional embodiments may exist in the drawings and detailed description of the invention.

According to the solution to the problem of the present invention described above, a foldable propeller structure according to one embodiment of the present invention includes a propeller and a shaft drive unit that provides a driving force for moving the shaft along an axial direction, whereby the propeller can be folded and stored inside a fuselage and a propulsion device by folding it so that the propeller can be folded and stored again inside the fuselage and propulsion device, and can be used to generate thrust by folding it and providing a shaft drive unit so that the propeller can be folded and stored inside the fuselage and propulsion device.

In addition, according to the solution to the problem of the present invention described above, the foldable propeller structure according to one embodiment of the present invention includes a propeller in which a plurality of blades are provided to enable switching between an unfolded state and a folded state, and a shaft drive unit that provides a driving force for moving the shaft along the axial direction, thereby having a structure and mechanism for switching the propeller to the folded state and moving the shaft along the axial direction so that the propeller is accommodated inside the airframe and the propulsion device, thereby minimizing a shape protruding outward, thereby reducing air resistance caused by the propeller.

Figure 1 is a schematic conceptual diagram for explaining a method of deploying a foldable propeller structure according to one embodiment of the present invention.
FIG. 2 is a schematic conceptual diagram illustrating a method of lowering a propeller of a foldable propeller structure according to one embodiment of the present invention in a deployed state.
FIG. 3 is a schematic conceptual diagram illustrating one implementation example of a foldable propeller structure according to one embodiment of the present invention.
FIG. 4 is a schematic conceptual diagram for explaining a deployment mechanism of a foldable propeller structure according to one embodiment of the present invention.
FIG. 5 is a schematic conceptual diagram illustrating another implementation example of a foldable propeller structure according to one embodiment of the present invention.
FIGS. 6A and 6B are schematic conceptual diagrams for explaining a deployment mechanism of a foldable propeller structure according to another embodiment of the foldable propeller structure according to one embodiment of the present invention.
FIG. 7 is a schematic conceptual diagram illustrating an implementation example in which the axis of a foldable propeller structure according to one embodiment of the present invention is located at the center of the housing.
FIG. 8 is a three-dimensional conceptual diagram illustrating an implementation example in which the axis of a foldable propeller structure according to one embodiment of the present invention is located at the center of the housing.
FIG. 9 is a schematic conceptual diagram illustrating an implementation example in which the axis of a foldable propeller structure according to one embodiment of the present invention is arranged on one side with respect to the housing.
FIG. 10 is a three-dimensional conceptual diagram illustrating an implementation example in which the axis of a foldable propeller structure according to one embodiment of the present invention is arranged on one side with respect to the housing.
FIG. 11 is a schematic conceptual diagram illustrating one embodiment of a foldable propeller structure including a shaft guide according to one embodiment of the present invention.
FIG. 12 is a schematic conceptual diagram for explaining a deployment mechanism of a foldable propeller structure according to one embodiment of the present invention, wherein the foldable propeller structure includes a shaft guide.
FIG. 13 is a schematic conceptual diagram illustrating an implementation example in which a foldable propeller structure according to one embodiment of the present invention is arranged relative to a housing while including a shaft guide.
FIG. 14 is a schematic conceptual diagram illustrating a gas turbine engine including a foldable propeller structure according to one embodiment of the present invention.
FIG. 15 is a schematic conceptual diagram illustrating a gas turbine engine including a foldable propeller structure according to one embodiment of the present invention including a shaft guide.
FIG. 16 is a schematic conceptual diagram illustrating a state in which a vertical folding propeller structure and a horizontal folding propeller structure of an aircraft including a foldable propeller structure according to one embodiment of the present invention are deployed.
FIG. 17 is a schematic conceptual diagram illustrating a state in which a vertically foldable propeller structure of an aircraft including a foldable propeller structure according to one embodiment of the present invention is stowed and a horizontally foldable propeller structure is deployed.
FIG. 18 is a schematic conceptual diagram illustrating a state in which a vertical folding propeller structure and a horizontal folding propeller structure of an aircraft including a foldable propeller structure according to one embodiment of the present invention are stored.
Figure 19 is a flowchart for explaining a control method of a foldable propeller structure according to one embodiment of the present invention.
FIG. 20 is a detailed drawing (cross-sectional view) for explaining a blade moving block of a foldable propeller structure according to one embodiment of the present invention.

Below, with reference to the attached drawings, embodiments of the present invention are described in detail so that those with ordinary skill in the art can easily practice the present invention. However, the present invention may be implemented in various different forms and is not limited to the embodiments described herein. In addition, in order to clearly describe the present invention in the drawings, parts that are not related to the description are omitted, and similar parts are assigned similar drawing reference numerals throughout the specification.

Throughout this specification, when a part is said to be "connected" to another part, this includes not only the case where it is "directly connected" but also the case where it is "electrically connected" with another element in between.

Throughout this specification, when it is said that an element is located “on,” “above,” “below,” “under,” or “below” another element, this includes not only cases where an element is in contact with another element, but also cases where another element exists between the two elements.

Throughout this specification, whenever a part is said to "include" a component, this does not exclude other components, but rather includes other components, unless otherwise specifically stated.

Hereinafter, a foldable propeller structure (hereinafter referred to as “the propeller structure”) according to one embodiment of the present invention will be described.

FIG. 1 is a schematic conceptual diagram for explaining a method of deploying a foldable propeller structure according to one embodiment of the present invention, and FIG. 2 is a schematic conceptual diagram for explaining a method of lowering a propeller of a foldable propeller structure according to one embodiment of the present invention in a deployed state.

Referring to FIGS. 1 and 2, the propeller structure (100) may include a shaft (110), a propeller (120), and a blade driving unit (130). For example, the shaft (110) may be provided as a rotation axis of the propeller (120).

Referring to FIGS. 1 and 2, the propeller (120) may include a plurality of blades (121) and a hub (122). The hub (122) may be connected to one axial side of the shaft (110). For example, referring to FIG. 1 (a), one axial side of the shaft (110) may be in a direction that protrudes in a developed state described below. For example, the direction that protrudes may be upward or forward, and may be in the 12 o'clock direction based on FIG. 1 (a). In the following description, for convenience of explanation, the direction that protrudes will be described with the upward direction as the standard.

Also, referring to FIGS. 1 and 2, a plurality of blades (121) may be provided to be connected to the hub (122) at intervals in the circumferential direction with respect to the hub (122). For example, the propeller (120) may be provided to rotate about the shaft (110) as the rotation axis. The propeller (120) may be provided to be linked with the rotational drive of the shaft (110).

Each of the plurality of blades (121) may be hinge-connected to the hub (122) to enable transition between a deployed state in which they spread radially from the hub (122) and a folded state in which they fold closer to the shaft (110) than the deployed state. For example, referring to FIGS. 1 and 2, each of the plurality of blades (121) may be hinge-connected to the hub (122) to enable transition between a folded state (see FIG. 1 (a) and FIG. 2 (a)) and a deployed state (see FIG. 1 (e), FIG. 2 (e) and (g)).

For example, referring to (a) of FIG. 1, the folding state of the plurality of blades (121) can be achieved by hinge-rotating around the hub (122) so that the plurality of blades (121) come closer to the shaft (110). In addition, referring to (e) of FIG. 1, for example, the unfolding state of the plurality of blades (121) can be achieved by hinge-rotating around the hub (122) so that the plurality of blades (121) move away from the shaft (110).

In addition, for example, a plurality of blades (121) may be hinge-connected to the hub (122) by a hinge connection unit, but is not limited thereto, and may be implemented in a hinge connection method that is obvious to those skilled in the art or to be developed in the future.

FIG. 3 is a schematic conceptual diagram for explaining an implementation example of a shaft drive unit and a blade drive unit of a foldable propeller structure according to an embodiment of the present disclosure, FIG. 4 is a schematic conceptual diagram for explaining a deployment mechanism of a foldable propeller structure according to an implementation example of a shaft drive unit and a blade drive unit of a foldable propeller structure according to an embodiment of the present disclosure, and FIG. 20 is a detailed diagram (cross-sectional view) for explaining a blade moving block of a foldable propeller structure according to an embodiment of the present disclosure.

Referring to FIGS. 3 and 4, the blade driving unit (130) can be connected to the plurality of blades (121) to provide a driving force to switch the plurality of blades (121) to either an unfolded state or a folded state.

Referring to FIG. 3, the blade driving unit (130) may include a blade moving block (131), a first screw member (132), a blade driving unit (133), and a plurality of link members (134).

Referring to FIGS. 3, 4 and 20, the blade moving block (131) can be installed to surround the shaft (110) and the outer circumference of the shaft (110).

For example, referring to FIG. 20, the blade movement block (131) may be provided so that the blade movement block (131) can slide axially along the outer circumference of the shaft (110) when rotating by screw engagement with the first screw member (132) described later, while being axially moved in conjunction with the shaft (110). For reference, the axial movement may be a movement in the 12 o'clock-6 o'clock direction based on FIG. 3.

Also, referring to FIG. 3, the first screw member (132) is a member extending in the axial direction and can be arranged parallel to and adjacent to the shaft (110). For example, referring to FIG. 3, the first screw member (132) can be arranged parallel to the shaft (110).

In addition, referring to (c) to (e) of FIG. 3 and FIG. 4, the first screw member (132) may be screw-connected to the blade moving block (131) to move the blade moving block (131) in the axial direction in response to the rotation of the member (the first screw member). In addition, referring to FIG. 3, the blade driving unit (133) of the blade driving unit (130) may be provided to rotate the first screw member (132). For example, the blade driving unit (133) may be a motor.

For example, referring to (c) to (e) of FIGS. 3 and 4, the first screw member (132) can be rotated by the blade driving unit (133), and accordingly, the blade moving block (131) screw-coupled to the first screw member (132) can be moved axially with respect to the first screw member (132) and the screw (110).

In addition, for example, the first screw member (132) may be provided such that the blade moving block (131) moves to one axial side (for example, the 12 o'clock direction as shown in FIG. 3) when rotated in the first direction (for example, counterclockwise), and may be provided such that the blade moving block (131) moves to the other axial side (for example, the 6 o'clock direction as shown in FIG. 3) when rotated in the second direction (for example, clockwise). However, the present invention is not limited thereto, and conversely, the first screw member (132) may be provided such that when rotated in the first direction, the blade moving block (131) moves to the other axial side, and when rotated in the second direction, the blade moving block (131) moves to one axial side.

Additionally, for example, the first screw member (132) may be replaced with a worm gear member. Accordingly, the blade moving block (131) coupled with the first screw member (132) may be provided with a member corresponding to the worm gear member.

In addition, referring to FIGS. 3 and 4, a plurality of link members (134) of the blade driving unit (130) can connect the blade moving block (131) and each of the plurality of blades (121).

In addition, referring to FIGS. 3 and 4, the plurality of link members (134) can be connected so as to enable transition to either a deployed state or a folded state according to the axial movement of the blade moving block (131). For example, referring to FIGS. 4 (c) to (e), the plurality of link members (134) connect the blade moving block (131) and the plurality of blades (121), respectively, so that the plurality of blades (121) can be transitioned from a folded state to a deployed state as the blade moving block (131) is moved to one side in the axial direction (12 o'clock direction based on FIG. 4 (c)) by the rotation of the first screw member (132).

In addition, for example, referring to (e), (d), and (c) of FIG. 4 in that order, a plurality of link members (134) may connect the blade moving block (131) and each of the plurality of blades (121), so that the plurality of blades (121) may be switched from an unfolded state to a folded state as the blade moving block (131) is moved to the other axial side (6 o'clock direction based on (e) of FIG. 4) by the rotation of the first screw member (132).

Referring to FIG. 3 and FIG. 20, the blade moving block (131) and the plurality of link members (134) among the blade driving unit (130) may be provided to be linked with the rotational drive of the propeller (120). For example, referring to FIG. 3, the plurality of link members (134) connected to each of the plurality of blades (121) and the blade moving blocks (131) connected to the plurality of link members (134) may be provided to rotate together when the propeller (120) is rotated.

In addition, referring to FIG. 3 and FIG. 20, the first screw member (132) and the blade drive unit (133) among the blade drive members (130) may be provided so as not to be coupled with the rotational drive of the propeller (120). For example, referring to FIG. 3, the first screw member (132) and the blade drive unit (133) may be provided so as not to rotate when the propeller (120) rotates.

For example, referring to FIG. 20, the blade moving block (131) can be connected to the first screw member (132) through a bearing in the form of a ring bearing (donut-shaped bearing). For example, the first screw member (132) can be screw-coupled to a hole (for example, a hole with a female thread formed) formed in the ring bearing. In addition, for example, referring to FIG. 20, the blade moving block (131) can be coupled in a form in which the inner and outer peripheries of the ring bearing are wrapped by the blade moving block (131), so that the blade moving block (131) and the first screw member (132) can be bearing-coupled through the ring bearing. For example, the blade moving block (131) can be provided in a 'ㄷ' shape or a 'C' shape and can be coupled in a form in which the inner and outer peripheries of the ring bearing are wrapped. Accordingly, by the screw connection of the hole formed in the ring bearing and the first screw member (132), the blade movement block (131) can slide axially along the outer circumference of the shaft (110) when the first screw member (132) rotates, and when the shaft (110) rotates, the blade movement block (131) and the plurality of link members (134) rotate by linkage with the propeller rotation drive, but the first screw member (132) that is connected to the blade movement block (131) through the ring bearing can be non-rotated with the blade movement block (131), and accordingly, the first screw member (132) can maintain a state in which it is not linked with the propeller rotation and is not rotated. In this way, the first screw member (132) is not directly connected to a structure that rotates when the propeller rotates, such as the blade movement block (131), but can be provided with a structure that is fixed to another structure, such as a ring bearing, and does not rotate.

Referring to FIG. 3, the propeller structure (100) may include a shaft drive unit (140). The shaft drive unit (140) may be connected to the shaft (110) to provide a driving force for moving the shaft (110) along the axial direction. For example, the shaft drive unit (140) may provide a driving force for moving the shaft (110) to one axial side (12 o'clock direction based on FIG. 3). In addition, for example, the shaft drive unit (140) may provide a driving force for moving the shaft (110) to the other axial side (6 o'clock direction based on FIG. 3).

Referring to FIG. 3, the shaft drive unit (140) may include a worm gear (141), a rack gear (142), and a shaft drive unit.

Referring to FIG. 3, the worm gear (141) may be installed to surround the outer circumference of the shaft (110) so that the axial movement is linked with the shaft (110). In addition, for example, the axial movement may be a movement in the 12 o'clock-6 o'clock direction based on FIG. 3.

In addition, for example, the worm gear (141) and the shaft (110) are linked in axial movement, and when the worm gear (141) rotates by gear engagement (mesh) with the rack gear (142) described later, the worm gear (141) is moved axially by gear engagement with the rack gear (142), and the shaft (110) can also move axially. For example, when the worm gear (141) is rotated in a first direction (e.g., counterclockwise) with the shaft (110) as the rotation axis and moves to one axial side (e.g., the 12 o'clock direction based on FIG. 3), the shaft (110) can also move to one axial side by linking the axial movement with the worm gear (141). In addition, for example, when the worm gear (141) is rotated in the second direction (e.g., clockwise) with the shaft (110) as the rotation axis, and moves to the other axial side (e.g., 6 o'clock direction based on FIG. 3), the shaft (110) can also move to the other axial side by linking the axial movement with the worm gear (141).

In addition, referring to FIG. 3, the worm gear (141) may be arranged relative to the worm gear (141) so that the blade drive unit (133) is coupled with the axial movement of the worm gear (141). For example, referring to FIG. 3, the blade drive unit (133) may be provided to be arranged on the worm gear (141). In addition, for example, referring to FIG. 4, the blade drive unit (133) may be arranged relative to the worm gear (141) so as to move axially together with the worm gear (141) when the worm gear (141) moves in the axial direction of the shaft (110).

In addition, the worm gear (141) may be installed relative to the shaft (110) so as to have a rotational degree of freedom that is not coupled with the rotation of the shaft (110). For example, the worm gear (141) and the shaft (110) may be installed so that they do not constrain the rotational degrees of freedom of each other, and the shaft (110) does not rotate when the worm gear (141) rotates, and conversely, the worm gear (141) may be installed so as not to rotate when the shaft (110) rotates. For example, the shaft drive unit (140) may include a bearing interposed between the worm gear (141) and the shaft (110). In addition, for example, the worm gear (141) may be connected to the shaft (110) so that the axial movement of the shaft (110) is coupled as described above, but the rotation of the shaft (110) is not coupled by the bearing (so that the rotational degree of freedom of the worm gear is not constrained by the shaft). In other words, the worm gear (141) and the shaft (110) are connected through a bearing or the like interposed between the two components, so that the rotation of one component is not transmitted to the other component (their rotations are not coupled with each other), so that when the worm gear (141) rotates, the shaft (110) does not rotate, and when the shaft (110) rotates, the worm gear (141) does not rotate, but their axial movements are coupled, so that when the worm gear (141) moves axially, the shaft (110) can also move axially. However, the connection method in which the axial movements of the shaft (110) and the worm gear (141) are coupled while their rotations are not coupled with each other is not limited to this, and can be implemented by an installation method that is obvious to a person skilled in the art or that will be developed in the future.

Referring to FIG. 3, the shaft drive unit may be provided to rotate the worm gear (141). For example, the shaft drive unit may be a motor, but is not limited thereto. For example, the shaft drive unit may be provided such that the rotation axis of the shaft drive unit is connected (directly or indirectly) to the worm gear (141) so that the shaft drive unit can rotate the worm gear (141). For example, the shaft drive unit may be provided in a form combined with the blade moving block (131), or may be provided in the form of a driving device such as a motor on an external structure other than the blade moving block (131) to rotate the worm gear (141).

In addition, referring to FIG. 3, the rack gear (142) of the shaft drive unit (140) may be gear-coupled with the worm gear (141) so that the worm gear (141) moves axially in response to the rotation. For example, the worm gear (141) may be provided to have a rotation axis corresponding to the axial direction of the shaft (110), and the rack gear (142) may be provided to have a rotation axis orthogonal to the rotation axis of the worm gear (141).

For example, referring to (a) to (c) of FIGS. 3 and 4, the worm gear (141) can be rotated by the shaft drive unit, and the rotated worm gear (141) can move in the axial direction depending on the progress of gear engagement with the rack gear (142).

The shaft drive unit (140) may be provided so as to be non-interlocked with the rotational drive of the propeller (120) when the propeller structure (100) is in a deployed state. For example, the shaft drive unit (140) may be connected to the shaft (110), but non-interlocked with the rotational drive of the shaft (110). For example, the shaft drive unit (140) may be installed so that the worm gear (141) surrounds the outer circumference of the shaft (110) that rotates when the propeller (120) is rotated, but has a rotational degree of freedom that is non-interlocked, so that the shaft (110) and the worm gear (141) may be non-interlocked with each other in rotation. For example, a bearing or the like may be interposed between the worm gear (141) and the shaft (110) so that the shaft drive unit (140) does not rotate together with the propeller (120), so that its rotation is not coupled when the propeller (120) rotates.

For example, referring to (a) of FIG. 4, the propeller structure (100) is in an internally stored state where the propeller (120) does not protrude, and referring to (b) and (c) of FIG. 4, the shaft drive unit rotates the worm gear (141) in the first direction so that the worm gear (141) can move to one axial direction (for example, to the 12 o'clock direction based on (b) of FIG. 4) by gear engagement with the rack gear (142), and as the worm gear (141) moves in the axial direction, the shaft (110) whose axial movement is linked with the worm gear (141) can also move to one axial direction, and the propeller structure (100) can perform an upward movement. In addition, for example, referring to (c) to (e) of FIG. 4, when the propeller (120) is in a protruding external protrusion state, the blade driving unit (133) rotates the first screw member (132) so that the blade driving unit (133) screw-connected with the first screw member (132) can move to one side in the axial direction, and accordingly, the plurality of link members (134) connected to the blade driving unit (133) can cause the propeller (120) to be switched to a deployed state. In addition, for example, referring to (f) of FIG. 4, the propeller structure (100) can be moved to the other axial side (for example, the 6 o'clock direction based on (f) of FIG. 4) by rotating the worm gear (141) in the second direction in a deployed state in which a plurality of blades (121) of the propeller (120) are deployed, and as the worm gear (141) is moved in the axial direction, the shaft (110) can also be moved to the other axial side, and the propeller structure (100) can perform a descending motion.

Referring to (c) to (e) of FIG. 4, the external protrusion state may include a state in which at least a portion of the propeller structure (100) protrudes outwardly so that the plurality of blades (121) can be switched from a folded state to a deployed state. In other words, for example, the external protrusion state may include a state in which at least a portion of the propeller structure (100) protrudes outwardly so that the plurality of blades (121) do not interfere with a storage space (a housing described later) when the plurality of blades (121) are switched from a folded state to a deployed state.

In addition, referring to (e) and (f) of FIG. 4, the external protrusion state may include a state in which the plurality of blades (121) are placed in a deployed state and then the propeller structure (100) is re-moved to the other axial side within the limit of the propeller (120) rotation drive of the plurality of blades (121). For example, the other axial side may be the 6 o'clock direction with respect to (f) of FIG. 4.

Meanwhile, FIG. 5 is a schematic conceptual diagram for explaining another embodiment of a shaft drive unit of a foldable propeller structure according to one embodiment of the present invention, and FIGS. 6a and 6b are schematic conceptual diagrams for explaining a deployment mechanism of a foldable propeller structure according to another embodiment of a shaft drive unit of a foldable propeller structure according to one embodiment of the present invention. For example, FIGS. 6a and 6b may be schematic conceptual diagrams for explaining a method in which the propeller structure (100) includes an actuator and moves the position of the drive gear using the actuator.

Referring to FIGS. 5, 6a and 6b, the shaft drive unit (140) of the present propeller structure (100) may include a shaft moving block (144), a second screw member (145) and a shaft drive unit.

Referring to FIG. 5, the shaft movement block (144) may be installed to surround the outer circumference of the shaft (110) so that the shaft (110) and the axial movement are linked. For example, the shaft movement block (144) may be a moving plate.

In addition, for example, the shaft movement block (144) may be installed relative to the shaft (110) so as to have a rotational degree of freedom that is not coupled with the rotation of the shaft (110). For example, the shaft movement block (144) and the shaft (110) may be installed so that they do not constrain the rotational degrees of freedom of each other, and the shaft (110) does not rotate when the shaft movement block (144) rotates, and conversely, the shaft movement block (144) may be installed so as not to rotate when the shaft (110) rotates. For example, the shaft drive unit (140) may include a bearing interposed between the worm gear (141) and the shaft (110). In addition, for example, the worm gear (141) may be connected to the shaft (110) so that the axial movement of the shaft (110) is coupled as described above, but the rotation of the shaft (110) is not coupled by the bearing (so that the rotational degree of freedom of the worm gear is not constrained by the shaft). However, the connection method in which the axial movement of the shaft (110) and the worm gear (141) are linked while their rotations are not linked is not limited to this, and can be implemented by an installation method that is obvious to those skilled in the art or will be developed in the future.

For example, referring to FIG. 5, a shaft movement block (144) may be installed on a shaft (110) such that the shaft movement block (144) and the shaft (110) constrain each other's axial movement degrees of freedom. For example, the axial movement may be a 12 o'clock-6 o'clock movement based on FIG. 5.

In addition, for example, the shaft movement block (144) and the shaft (110) are linked in the axial movement, so that when the second screw member (145) described later rotates, the shaft movement block (144) is moved in the axial direction, and the shaft (110) can also be moved in the axial direction. For example, when the shaft movement block (144) is moved to one axial side (for example, the 12 o'clock direction based on FIG. 5) by the rotation of the second screw member (145), the shaft (110) can also be moved to one axial side by linking the axial movement of the shaft movement block (144). In addition, for example, when the shaft movement block (144) is moved to the other axial side (for example, the 6 o'clock direction based on FIG. 5) by the rotation of the second screw member (145), the shaft (110) can also be moved to the other axial side by linking the axial movement of the shaft movement block (144).

Referring to FIG. 5, the second screw member (145) is a member that extends in the axial direction and is arranged adjacent to the shaft (110) in parallel with the shaft (110), but may be arranged at a preset interval from the first screw member (132) and further from the shaft (110) than the first screw member (132). For example, referring to FIG. 5, the second screw member (145) may be arranged parallel to the shaft (110). Also, for example, the second screw member (145) may be arranged parallel to the first screw member (132).

In addition, the preset interval here may correspond to the interval according to the arrangement position of the integrated driving unit (150) described later, and a detailed description thereof will be described later.

In addition, referring to FIGS. 5 and 6A, the second screw member (145) may be screw-connected with the shaft moving block (144) to move the shaft moving block (144) axially in response to the rotation of the member (the second screw member). In addition, the shaft drive unit may be provided to rotate the second screw member (145).

For example, referring to FIGS. 5 and 6A, the second screw member (145) can be rotated by the shaft drive unit, and accordingly, the shaft moving block (144) screw-coupled to the second screw member (145) can be moved axially with respect to the second screw member (145) and the shaft (110).

For example, referring to FIG. 6A, the second screw member (145) may be provided such that when the shaft moving block (144) is rotated in a first direction (e.g., counterclockwise) by the shaft drive unit, the shaft moving block (144) moves to one axial side (e.g., 12 o'clock direction with respect to (a) of FIG. 6A), and when the second screw member (145) is rotated in a second direction (e.g., clockwise), the shaft moving block (144) moves to the other axial side (e.g., 6 o'clock direction with respect to (a) of FIG. 6A). However, the present invention is not limited thereto, and conversely, when the second screw member (145) is rotated in the first direction, the shaft moving block (144) may be provided such that when the second screw member (145) is rotated in the first direction, the shaft moving block (144) moves to the other axial side, and when the second screw member (145) is rotated in the second direction, the shaft moving block (144) moves to one axial side.

Additionally, for example, the second screw member (145) may be replaced with a worm gear member. Accordingly, the shaft movement block (144) coupled with the second screw member (145) may be provided with a member corresponding to the worm gear member.

Referring to FIG. 5, the propeller structure (100) may include an integrated driving unit (150) provided to selectively perform either an operation as a blade driving unit (133) or an operation as a shaft driving unit. For example, referring to FIG. 6a, the integrated driving unit (150) may perform an operation as a shaft driving unit, and referring to FIG. 6b, the integrated driving unit (150) may be provided to perform an operation as a blade driving unit (133).

Referring to FIG. 5, the integrated drive unit (150) may include an integrated drive unit (151), an inner bevel gear (153), and an outer bevel gear (152).

Referring to FIG. 5, the integrated drive unit (151) provides a rotational driving force for a rotational axis orthogonal to the axial direction of the shaft (110), and the rotational axis may be arranged to protrude toward the shaft side. For example, the integrated drive unit (151) may be a motor.

In addition, for example, the rotation axis orthogonal to the axial direction of the integrated drive unit (151) may be in the 3 o'clock-9 o'clock direction as shown in FIG. 5. In addition, for example, the rotation axis of the integrated drive unit (151) may be arranged to protrude toward the 3 o'clock direction as shown in FIG. 5.

Also, referring to FIG. 5, the inner bevel gear (153) may be mounted facing inwardly toward the shaft (110) with respect to the rotational axis of the integrated drive unit (151). Also, the outer bevel gear (152) may be mounted facing outwardly opposite to the shaft (110) with respect to the rotational axis of the integrated drive unit (152). For example, referring to FIG. 5, the outer bevel gear (152) and the inner bevel gear (153) may be mounted on the rotational axis of the integrated drive unit (151), and the outer bevel gear (152) may be mounted facing outwardly (9 o'clock direction with respect to FIG. 5) and the inner bevel gear (153) may be mounted facing inwardly (3 o'clock direction with respect to FIG. 5).

Additionally, for example, the outer bevel gear (152) and the inner bevel gear (153) can be rotated by the rotational driving force of the integrated driving unit (151).

In addition, referring to FIGS. 5 and 6A, the integrated driving unit (150) may include a bevel gear (157) for shaft movement. The bevel gear (157) for shaft movement may be provided to have the same rotational axis as the second screw member (145) on one axial side of the second screw member (145). For example, the bevel gear (157) for shaft movement may be provided to be rotationally coupled with the second screw member (145). For example, the bevel gear (157) for shaft movement may be provided such that as it (the bevel gear for shaft movement) rotates, the second screw member (145) also rotates.

Referring to FIGS. 5 and 6A, the integrated driving unit (150) may be capable of operating as a shaft driving unit when the outer bevel gear (152) is bevel-gear coupled with the shaft-moving bevel gear (157). For example, the rotation axis of the outer bevel gear (152) and the rotation axis of the shaft-moving bevel gear (157) may be provided to have rotation axes that are orthogonal to each other, and thus, the outer bevel gear (152) and the shaft-moving bevel gear (157) may be capable of bevel-gear coupling.

For example, referring to FIG. 6A, when the outer bevel gear (152) and the shaft movement bevel gear (157) are bevel gear-coupled, the outer bevel gear (152) is rotated by the integrated drive unit (151), and the shaft movement bevel gear (157) coupled with the outer bevel gear (152) can be rotated, and as the shaft movement bevel gear (157) is rotated, the second screw member (145) whose rotation is linked with the shaft movement bevel gear (157) is rotated, and the shaft movement block (144) screw-coupled with the second screw member (145) can be moved to one side in the axial direction, and accordingly, the shaft (110) whose axial movement is linked with the shaft movement block (144) is moved to one side in the axial direction, so that the propeller structure (100) can be transformed from an internally stored state to an externally protruding state.

Referring to FIG. 5, the integrated drive unit (150) may include a first spur gear (154), a second spur gear (155), and a bevel gear (156) for blade deployment.

Referring to FIG. 5, the first spur gear (154) may be provided to have the same rotation axis as the first screw member (132). For example, the first spur gear (154) may be provided to be rotationally coupled with the first screw member (132). For example, the first spur gear (154) may be rotated according to gear engagement with the second spur gear (155), and the first spur gear (154) may be rotated, and the first screw member (132) coupled therewith may also be provided to be rotated.

For example, referring to FIG. 5, the first flat gear (154) may be positioned on the axial side (e.g., the 6 o'clock direction based on FIG. 5) of the first screw member (132).

Also, referring to FIG. 5, the second spur gear (155) may be arranged on one axial side of the shaft moving block (144) (for example, the 12 o'clock direction based on FIG. 5) and may be gear-engaged with the first spur gear (154). For example, the first spur gear (154) may be arranged on one axial side of the shaft moving block (144) like the second spur gear (155) so that gear-engagement (mesh) with the second spur gear (155) is possible.

Referring to FIG. 5, the bevel gear (156) for blade deployment of the integrated driving unit (150) may be arranged on one axial side of the second spur gear (155) so as to have the same rotational axis as the second spur gear (155). For example, the bevel gear (156) for blade deployment may be provided so as to be rotationally linked with the second spur gear (155). For example, the second spur gear (155) may be rotated based on the same rotational axis as the bevel gear (156) for blade deployment rotates.

Referring to FIGS. 5 and 6B, the integrated driving unit (150) can perform an operation as a blade driving unit (133) when the inner bevel gear (153) is bevel-gear coupled with the blade deployment bevel gear (156). For example, the rotation axis of the inner bevel gear (153) and the rotation axis of the blade deployment bevel gear (156) can be provided to have rotation axes that are orthogonal to each other, and thus, the inner bevel gear (153) and the blade deployment bevel gear (156) can be bevel-gear coupled.

For example, referring to FIG. 6B, when the inner bevel gear (153) and the blade deployment bevel gear (156) are bevel gear-coupled, the inner bevel gear (153) is rotated by the integrated drive unit (151), and the blade deployment bevel gear (156) coupled with the inner bevel gear (153) can be rotated, and as the blade deployment bevel gear (156) is rotated, the second spur gear (155) is also rotated, and the first spur gear (154) gear-coupled with the second spur gear (155) is also rotated, and the first screw member (132) whose rotation is linked with the first spur gear (154) is rotated, so that the blade drive unit (133) screw-coupled with the first screw member (132) can be moved to one side in the axial direction, and accordingly, the plurality of link members (134) connected to the blade drive unit (133) can be brought into a state where the propeller (120) is deployed. It is possible to make the transition happen.

Also, referring to FIG. 5, the second spur gear (155) and the bevel gear (156) for blade deployment, and the inner bevel gear (153) and the outer bevel gear (152) are arranged with respect to a preset interval section, and the inner bevel gear (153) and the outer bevel gear (152) may be arranged outside the second spur gear (155) and the bevel gear (156) for blade deployment. Also, for example, the inner bevel gear (153) and the outer bevel gear (152) may be arranged inside the bevel gear (157) for shaft movement. Also, for example, the first spur gear (155) may be arranged inside the second spur gear (155) and the bevel gear (156) for blade deployment.

That is, for example, referring to FIG. 5, the integrated driving unit (150) may be arranged in the following order: from the outside (9 o'clock direction based on FIG. 5), a bevel gear (157) for shaft movement, an outer bevel gear (152), an inner bevel gear (153), a bevel gear (156) for blade deployment, a second spur gear (155), and a first spur gear (154).

Referring to FIG. 5, the integrated driving unit (150) may include an actuator (158). The actuator (158) may be provided to linearly move the integrated driving unit (151) equipped with an inner bevel gear (153) and an outer bevel gear (152) in a direction perpendicular to the axial direction of the shaft (110) in a gap direction corresponding to a preset gap.

Here, the preset interval can be set so that, when the integrated drive unit (151) is moved inwardly linearly by the actuator (158), when viewed in the axial direction, the inner bevel gear (153) and the bevel gear for blade deployment (156) are positioned at positions where the bevel gear engagement is possible, and the outer bevel gear (152) and the bevel gear for shaft movement (157) are positioned at positions where the bevel gear engagement is released. In addition, the preset interval can be set so that, when the integrated drive unit (151) is moved outwardly linearly by the actuator (158), when viewed in the axial direction, the inner bevel gear (153) and the bevel gear for blade deployment (156) are positioned at positions where the bevel gear engagement is released, and the outer bevel gear (152) and the bevel gear for shaft movement (157) are positioned at positions where the bevel gear engagement is possible.

That is, for example, referring to FIG. 6B, the actuator (158) can cause the integrated drive unit (151) to move linearly inwardly, so that the inner bevel gear (153) and the blade deployment bevel gear (156) engage the bevel gears, and the outer bevel gear (152) and the shaft movement bevel gear (157) disengage the bevel gears, so that when the integrated drive unit (151) provides rotational driving force, the integrated drive unit (150) can perform an operation as the blade drive unit (133).

In addition, for example, referring to FIG. 6A, the actuator (158) may move the integrated drive unit (151) outwardly linearly, so that the outer bevel gear (152) and the bevel gear for shaft movement (157) engage the bevel gears, and the inner bevel gear (153) and the bevel gear for blade deployment (156) disengage the bevel gears, so that when the integrated drive unit (151) provides rotational driving force, the integrated drive unit (150) may perform an operation as a shaft drive unit.

Referring to FIGS. 5, 6a, and 6b, the bevel gear (157) for shaft movement may be provided at an axial position at which bevel gear engagement with the outer bevel gear (152) may be formed when the integrated drive unit (151) moves outwardly linearly. For example, the bevel gear (157) for shaft movement may be provided at an axial position at which bevel gear engagement with the outer bevel gear (152) may be formed when the integrated drive unit (151) moves outwardly linearly, and at which bevel gear engagement with the outer bevel gear (152) may be released when the integrated drive unit moves inwardly linearly. That is, for example, the axial position of the bevel gear (157) for shaft movement may be fixed, and the bevel gear engagement between the bevel gear (157) for shaft movement and the outer bevel gear (152) may be formed or released only by linear movement in a gap direction corresponding to a preset gap of the integrated drive unit (151). However, it is not limited to this.

In addition, referring to FIGS. 5, 6a, and 6b, the bevel gear (156) for blade deployment may be provided at an axial position where the bevel gear engagement with the inner bevel gear (153) can be achieved only when the shaft (110) has moved a preset distance in one axial direction, so that the plurality of blades (121) can be maintained in a folded state until the shaft (110) has moved a preset distance in one axial direction. For example, the bevel gear (156) for blade deployment may be arranged on one axial direction of the shaft moving block (144) and may be provided at an axial position where the bevel gear engagement with the inner bevel gear (153) can be achieved only when the shaft moving block (144) has moved a preset distance.

Additionally, for example, the bevel gear (156) for blade deployment may not engage with the inner bevel gear (153) until the shaft (110) is moved axially one way by a preset distance, even if the integrated drive unit (151) is moved inwardly linearly by the actuator (158).

Here, the preset distance may be set by considering that the propeller structure (100) is converted from an internally stowed state to an externally protruding state for an aircraft to which the propeller structure (100) is applied. For example, the internally stowed state of the propeller structure (100) may include a state in which the propeller structure (100) is in a folded state and a plurality of blades (121) are stowed with respect to the aircraft, as shown in (a) of FIG. 4 and (a) of FIG. 6a.

In addition, for example, the external protrusion state of the present propeller structure (100) may include a state in which at least a portion of the present propeller structure (100) protrudes outwardly so that the plurality of blades (121) can be switched from a folded state to a deployed state, as shown in (c) to (e) of FIG. 4 and (a) to (c) of FIG. 6b. In addition, the external protrusion state of the present propeller structure (100) may include a state in which the plurality of blades (121) are placed in a deployed state and then the present propeller structure (100) is axially re-moved to the other side within a limit in which the propeller (120) rotational drive of the plurality of blades (121) is possible, as shown in (f) of FIG. 4 and (d) of FIG. 6b.

For example, referring to FIG. 6A, in the propeller structure (100), when the propeller (120) is in an internally stored state without protruding, the integrated drive unit (151) is moved outward linearly by the actuator (158), so that the outer bevel gear (152) and the shaft-moving bevel gear (157) are bevel-gear-coupled, the outer bevel gear (152) is rotated by the integrated drive unit (151), the shaft-moving bevel gear (157) coupled with the outer bevel gear (152) is rotated, and as the shaft-moving bevel gear (157) is rotated, the second screw member (145) whose rotation is linked with the shaft-moving bevel gear (157) is rotated, and the shaft-moving block (144) screw-coupled with the second screw member (145) can be moved to one side in the axial direction, so that the shaft-moving block (144) and the axial movement are The connected shaft (110) can be moved to one side in the axial direction so that the propeller structure (100) can be changed from an internally stored state to an externally protruding state.

In addition, for example, referring to (a) to (c) of FIG. 6b, in the propeller structure (100), in the external protrusion state, the integrated drive unit (151) is moved inwardly by the actuator (158), so that the inner bevel gear (153) and the bevel gear for blade deployment (156) are bevel-gear-engaged, the inner bevel gear (153) is rotated by the integrated drive unit (151), the bevel gear for blade deployment (156) that is bevel-gear-engaged with the inner bevel gear (153) is rotated, and as the bevel gear for blade deployment (156) is rotated, the second spur gear (155) is also rotated, the first spur gear (154) that is gear-engaged with the second spur gear (155) is also rotated, and the first screw member (132) that is rotationally linked with the first spur gear (154) is rotated to drive the blade that is screw-engaged with the first screw member (132). The unit (133) can be moved axially to one side, thereby causing a plurality of link members (134) connected to the blade drive unit (133) to change the state of the propeller (120) to the deployed state.

In addition, for example, referring to (f) of FIG. 6b, in the propeller structure (100), in the deployed state where the plurality of blades (121) of the propeller (120) are deployed, the integrated drive unit (151) is moved outward linearly by the actuator (158), so that the outer bevel gear (153) and the bevel gear for shaft movement (157) are bevel-gear-engaged, the outer bevel gear (152) is rotated by the integrated drive unit (151), the bevel gear for shaft movement (157) coupled with the outer bevel gear (152) is rotated, and as the bevel gear for shaft movement (157) is rotated, the second screw member (145) whose rotation is linked with the bevel gear for shaft movement (157) is rotated, and the shaft movement block (144) screw-engaged with the second screw member (145) can be moved to the other axial direction, thereby causing the shaft to move. The propeller structure (100) can perform a downward motion by moving the shaft (110) in conjunction with the block (144) to the other side in the axial direction.

For example, referring to (a) and (b) of FIG. 6A, when the propeller structure (100) is in a state where at least a portion of the propeller structure (100) protrudes outwardly so that the plurality of blades (121) can be in a state transition from a folded state to a deployed state in an internally stored state, the integrated drive unit (151) can provide a rotational driving force so that the second screw member (145) rotates in a first direction (e.g., counterclockwise). In addition, referring to (f) of FIG. 6B, for example, when the propeller structure (100) is in a descending motion in which the plurality of blades (121) are placed in a deployed state and then re-moved to the other axial side within a limit in which the propeller (120) can be rotated, the integrated drive unit (151) can provide a rotational driving force so that the second screw member (145) rotates in a second direction (e.g., clockwise).

For example, the present propeller structure (100) is provided with a separate driving device and mechanism, and can be folded and unfolded by these. For example, referring to FIG. 6a, the present propeller structure (100) can raise the propeller (120) in the folded state above the reference plane by the worm gear (141) or the shaft moving block (144) of the shaft driving unit (140) based on the stored state. In addition, for example, referring to FIG. 6b, the present propeller structure (100) in the state where the propeller (120) has completed rising can be placed in the unfolded state by unfolding a plurality of blades (121) by the blade driving unit (130), and when the unfolding of the plurality of blades (121) is completed, the propeller rotation drive can be operated even in this state. In addition, for example, referring to (c) and (d) of FIG. 6b, the deployed propeller (120) can be lowered to a reference plane by a shaft drive unit (140), and when the lowering is completed, the propeller rotation drive can be activated.

For example, in order to change the propeller (120) of the propeller structure (100) from the unfolded state back to the folded state and place it in the internal storage state, the reverse order of the above description can be followed.

For example, the present propeller structure (100) has a structure and mechanism that are housed inside the fuselage and the propulsion device, thereby minimizing the shape protruding to the outside, thereby reducing air resistance by the propeller (120).

FIG. 7 is a schematic conceptual diagram for explaining an implementation example in which the axis of the foldable propeller structure according to one embodiment of the present invention is positioned at the center of the housing, and FIG. 8 is a conceptual diagram illustrating in three dimensions an implementation example in which the axis of the foldable propeller structure according to one embodiment of the present invention is positioned at the center of the housing.

For example, the present propeller structure (100) may be arranged relative to the housing (170). For example, here, the housing (170) may be a storage space for arranging the present propeller structure (100) relative to the aircraft, and thus, an internal space may be provided.

Additionally, for example, the housing (170) may be arranged on the wing of an aircraft so that the propeller structure (100) is driven.

Referring to FIGS. 7 and 8, the propeller structure (100) may be positioned relative to the housing (170) so that the central axis of the housing (170) and the shaft (110) correspond to each other. The propeller structure (100) may be provided so that the integrated driving unit (150) is accommodated in the accommodation space of the housing (170) and has a symmetrical accommodation space therefor.

FIG. 9 is a schematic conceptual diagram for explaining an implementation example in which the axis of the foldable propeller structure according to one embodiment of the present invention is arranged at one side with respect to the housing, and FIG. 10 is a conceptual diagram illustrating in three dimensions an implementation example in which the axis of the foldable propeller structure according to one embodiment of the present invention is arranged at one side with respect to the housing.

In addition, for example, referring to FIGS. 9 and 10, the propeller structure (100) may be arranged so that the central axis of the housing (170) and the shaft (110) do not correspond, and may be arranged on one side with respect to the housing (170). For example, referring to FIGS. 9 (a) and 10 (a), the space where the integrated driving unit (150) of the propeller structure (100) is arranged (for example, the 9 o'clock direction based on FIG. 9 (a)) may be provided so as to have a wide storage space for the housing (170) based on the shaft (110), and the space where the integrated driving unit (150) is not arranged (for example, the 3 o'clock direction based on FIG. 9 (a)) may be provided so as to have a narrow storage space for the housing (170) based on the shaft (110).

For example, the way in which this main propeller structure (100) is arranged on one side relative to the housing (170) can reduce the storage space of the housing (170).

For example, referring to FIGS. 7 to 10, the propeller structure (100) may be arranged so that the shaft (110) corresponds to the center of the housing (170), and as another example, the shaft (110) may be arranged on one side without corresponding to the center of the housing (170). The arrangement of the propeller structure (100) with respect to the housing (170) may be arranged depending on securing thrust during flight of the aircraft or the storage space and arrangement efficiency of the housing (170), and therefore, a more detailed description thereof will be omitted.

FIG. 11 is a schematic conceptual diagram for explaining an embodiment of a foldable propeller structure according to one embodiment of the present invention, wherein the foldable propeller structure includes a shaft guide, and FIG. 12 is a schematic conceptual diagram for explaining a deployment mechanism of a foldable propeller structure according to one embodiment of the present invention, wherein the foldable propeller structure includes a shaft guide.

For example, referring to FIGS. 11 and 12, the propeller structure (100) may include a shaft guide (160). For example, referring to FIG. 11, the shaft guide (160) may be installed to surround the outer circumference of the shaft (110). In addition, the shaft guide (160) may be provided to support the outer circumference of the shaft (110) so that the axial direction of the shaft (110) is maintained without being tilted by a predetermined amount or more, and may be installed with respect to the shaft (110). For example, the shaft (110) may be provided to be inserted into the inner hollow portion of the shaft guide (160).

In addition, for example, referring to (a) to (c) of FIG. 12, the shaft guide (160) may be provided to provide a guide length for the axial movement of the shaft (100) when the propeller structure (100) is converted from an internally stored state to an externally protruding state. For example, referring to (c) of FIG. 12, the shaft guide (160) may be provided to hold the other axial side of the shaft (110) in the externally protruding state of the propeller structure (100).

By applying such a shaft guide (160) to the shaft (110), the axial length of the shaft (110) of the propeller structure (100) can be reduced compared to when the shaft guide (160) is not applied. For example, looking at FIG. 12 in comparison with FIG. 2, a portion of the shaft (110) is accommodated inside the shaft guide (160) and then moves along the axial direction, protrudes from the shaft guide (160), and the length can be expanded in a manner that the length thereof is expanded, and accordingly, the length of the shaft (110) can be reduced, and the application space of the propeller structure (100) can also be reduced more compactly. When such a shaft guide (160) is applied, the axial length of the shaft (110) may be a length that allows the plurality of blades (121) to be switched from a folded state to an unfolded state when the axial side of the shaft (110) is connected to one axial side of the shaft guide (160) while the propeller structure (100) is in an externally protruding state.

FIG. 13 is a schematic conceptual diagram illustrating an implementation example in which a foldable propeller structure according to one embodiment of the present invention is arranged relative to a housing while including a shaft guide.

Referring to FIG. 13, the propeller structure (100) may be arranged so that the shaft (110) corresponds to the center of the housing (170). Also, as another example, the shaft (110) may be arranged on one side without corresponding to the center of the housing (170). The arrangement of the propeller structure (100) with respect to the housing (170) may be arranged according to securing thrust or the housing (170) storage space and arrangement efficiency during the flight of the aircraft, and therefore, a more detailed description will be omitted.

The shaft guide (160) of the present propeller structure (100) may be provided in a manner that is obvious to those skilled in the art or will be developed in the future, so a more detailed description will be omitted.

The present propeller structure (100) can be applied to aircraft and vertical take-off and landing aircraft, and can increase aerodynamic efficiency during vertical take-off and landing and horizontal flight. In addition, the present propeller structure (100) can be applied to gas turbine engines, and can be changed to a propulsion type such as a turbine prop engine, a turbofan engine, a turbojet engine, and can utilize high propulsion efficiency depending on the propulsion type. In addition, it can be utilized to improve the performance of existing aircraft and propulsion engines, and can be utilized for the development of new types of aircraft, etc.

Hereinafter, a gas turbine engine (hereinafter referred to as “the gas turbine engine”) including the propeller structure (100) according to one embodiment of the present invention will be described. However, since the gas turbine engine (200) shares the same or corresponding technical features as the propeller structure (100), the same drawing reference numerals will be used for the same or similar configurations as those of the propeller structure (100), and any duplicate descriptions will be brief or omitted.

FIG. 14 is a schematic conceptual diagram for explaining a gas turbine engine including a foldable propeller structure according to one embodiment of the present invention, and FIG. 15 is a schematic conceptual diagram for explaining a gas turbine engine including a foldable propeller structure according to one embodiment of the present invention including a shaft guide.

Referring to FIGS. 14 and 15, a gas turbine engine (200) may include the propeller structure (100).

For example, referring to (a) of FIG. 14 and (a) of FIG. 15, the gas turbine engine (200) can be driven in a turbojet engine mode when the propeller structure (100) is in an internally stored state. In addition, referring to (b) and (c) of FIG. 14 and (b) of FIG. 15, the gas turbine engine (200) can be driven in a turboprop engine mode when the propeller structure (100) is in an deployed state capable of propeller rotation driving.

For example, referring to FIGS. 14 and 15, the gas turbine engine (200) can be easily changed in shape to a turboprop engine, a turbofan engine, a turbojet engine, etc. by including the propeller structure (100), and high propulsion efficiency according to the propulsion type can all be utilized.

For example, referring to (b) of FIG. 14, the gas turbine engine (200) can secure a storage space compared to a conventional gas turbine engine. Accordingly, the propeller structure (100) can be stored internally in a folded state in the storage space of the gas turbine engine (200). In addition, for example, the gas turbine engine (200) can have a larger outer diameter than a conventional gas turbine engine due to the securing of the storage space, but is not limited thereto, and can be provided so as to maintain the outer diameter and secure only the storage space. The storage space and outer diameter of the gas turbine engine (200) can vary depending on design conditions, etc.

Hereinafter, an aircraft (hereinafter referred to as “the aircraft”) including the propeller structure (100) according to one embodiment of the present invention will be described. However, since the aircraft (300) shares the same or equivalent technical features as the propeller structure (100), the same drawing reference numerals will be used for the same or similar configurations as those of the propeller structure (100), and any duplicate descriptions will be brief or omitted.

FIG. 16 is a schematic conceptual diagram illustrating a state in which a vertically foldable propeller structure and a horizontally foldable propeller structure of an aircraft including a foldable propeller structure according to an embodiment of the present disclosure are deployed, FIG. 17 is a schematic conceptual diagram illustrating a state in which a vertically foldable propeller structure of an aircraft including a foldable propeller structure according to an embodiment of the present disclosure is stowed and a horizontally foldable propeller structure is deployed, and FIG. 18 is a schematic conceptual diagram illustrating a state in which a vertically foldable propeller structure and a horizontally foldable propeller structure of an aircraft including a foldable propeller structure according to an embodiment of the present disclosure are stowed.

Referring to FIGS. 16 to 18, the aircraft (300) may include the propeller structure (100). When the axial direction of the shaft (110) of the propeller structure (100) is arranged vertically, it may be referred to as a vertically foldable propeller structure (100a). However, in the vertically foldable propeller structure (100a), the term 'vertical' is not necessarily limited to a completely vertical arrangement, but is broadly understood to also include a case where it has a predetermined inclination so as to roughly face upward. In addition, the propeller structure (100) may be referred to as a horizontally foldable propeller structure (100b) when the shaft (110) is arranged horizontally or close to horizontally. However, 'horizontal' may also be understood to include a range of angles that are somewhat inclined in the same or similar way as the aforementioned 'vertical'.

For example, referring to FIG. 16, the aircraft (300) may be provided such that the vertical folding propeller structure (100a) and the horizontal folding propeller structure (100b) are in an externally protruding state, and the propeller (120) of the vertical folding propeller structure (100a) and the propeller (120) of the horizontal folding propeller structure (100b) are in a deployed state. At this time, for example, the propeller (120) of the vertical folding propeller structure (100a) and the propeller (120) of the horizontal folding propeller structure (100b) of the aircraft (300) may be driven to rotate the propellers.

In addition, for example, referring to FIG. 17, the aircraft (300) may be provided such that the vertical folding propeller structure (100a) is in an internally stowed state, the horizontal folding propeller structure (100b) is in an externally protruding state, and the propeller (120) of the horizontal folding propeller structure (100b) is in a deployed state. At this time, for example, the propeller (120) of the horizontal folding propeller structure (100b) of the aircraft (300) may be driven to rotate the propeller.

Additionally, for example, referring to FIG. 18, the aircraft (300) may be equipped with a vertical folding propeller structure (100a) and a horizontal folding propeller structure (100b) in an internally stored state.

Additionally, for example, referring to FIGS. 14 to 18, the present aircraft (300) may include the present gas turbine engine (200) including the present propeller structure (100).

Hereinafter, a control method of the present propeller structure (100) according to one embodiment of the present invention (hereinafter referred to as “the present control method”) will be described. However, since the present control method shares the same or corresponding technical features as the present propeller structure (100), the same drawing reference numerals are used for the same or similar configurations as those of the present propeller structure (100), and any duplicate descriptions will be brief or omitted.

Figure 19 is a flowchart for explaining a control method of a foldable propeller structure according to one embodiment of the present invention.

Referring to (a) to (c) of FIG. 1, (a) to (c) of FIG. 2, and FIG. 19, the present control method may include a step (step S110) of moving the shaft (110) and the propeller (120) to one axial direction. For example, in step S110, the present control method may rotate the shaft drive unit of the shaft drive unit (140) of the present propeller structure (100) to move the shaft (100) and the propeller (120) to one axial direction.

In addition, referring to (c) to (e) of FIG. 1, (c) to (e) of FIG. 2, and FIG. 19, the present control method may include a step (step S120) of converting a plurality of blades (121) from a folded state to a deployed state. For example, in step S120, the present control method may convert a plurality of blades (121) from a folded state to a deployed state by rotating a blade drive unit (130) of a blade drive unit (130) of the present propeller structure (100).

In addition, referring to (e) to (g) of FIG. 2 and FIG. 19, the present control method may include a step (step S130) of re-moving the propeller structure (100) to the other axial direction within a limit in which the propeller rotation drive of the plurality of blades (121) is possible after the plurality of blades (121) are placed in a deployed state at step S120. For example, at step S120, the present control method may move the shaft (110) and the propeller (120) to the other axial direction by rotating the shaft drive unit of the shaft drive unit (140) in a direction opposite to the rotation drive of the shaft drive unit at step S110.

In addition, for example, in order to convert the propeller structure (100) into an internal storage state, the control method may be performed in reverse order. For example, the propeller structure (100) placed in the deployed state and moved to the other axial side may be re-moved to one axial side again, the plurality of blades (121) may be converted from the deployed state to the folded state, and the propeller structure (100) placed in the folded state may be re-moved to the other axial side again.

The above description of the present invention is for illustrative purposes only, and those skilled in the art will understand that the present invention can be easily modified into other specific forms without changing the technical idea or essential features of the present invention. Therefore, it should be understood that the embodiments described above are exemplary in all respects and not restrictive. For example, each component described as a single component may be implemented in a distributed manner, and likewise, components described as distributed may be implemented in a combined manner.

The scope of the present application is indicated by the claims described below rather than the detailed description above, and all changes or modifications derived from the meaning and scope of the claims and their equivalent concepts should be interpreted as being included in the scope of the present application.

100: Folding propeller structure
100a: Vertical folding propeller structure
100b: Horizontal folding propeller structure
110: Shaft
120: Propeller
121: Blade
122: hub
130: Blade drive unit
131: Blade movement block
132: First screw member
133: Blade drive unit
134: Link missing
140: Shaft drive unit
141: Worm Gear
142: Rack Gear
144: Shaft movement block
145: Second screw member
150: Integrated drive unit
151: Integrated drive unit
152: Outer bevel gear
153: Inner bevel gear
154: 1st flat gear
155: 2nd flat gear
156: Bevel gear for blade deployment
157: Bevel gear for shaft movement
158: Actuator
160: Shaft Guide
170: Housing
200: Gas turbine engine
300: Aircraft

Claims (16)

In a foldable propeller structure,
shaft;
A propeller including a hub connected to one axial side of the shaft and a plurality of blades connected to the hub at a circumferential interval relative to the hub, wherein each of the plurality of blades is hinge-connected to the hub so as to be able to switch between a deployed state in which it is radially deployed from the hub and a folded state in which it is folded closer to the shaft than the deployed state; and
A shaft drive unit connected to the shaft to provide a driving force for moving the shaft along an axial direction;
Including a blade driving unit connected to the plurality of blades to provide a driving force for switching the plurality of blades to one of the unfolded state and the folded state,
The above blade driving unit,
A blade moving block installed to surround the outer circumference of the above shaft;
A first screw member, which is arranged adjacent to the shaft and parallel to the shaft as a member extending in the axial direction, and is screw-connected to the blade moving block so as to move the blade moving block in the axial direction in response to rotation of the member;
A blade driving unit provided to rotate the first screw member; and
The blade moving block and each of the plurality of blades are connected to each other, and a plurality of link members are included so that the connection can be switched to one of the unfolded state and the folded state according to the axial movement of the blade moving block.
The above shaft drive unit,
A worm gear installed to wrap around the outer circumference of the shaft so that the shaft and axial movement are linked;
A rack gear geared with the worm gear so that the worm gear moves in the axial direction in response to rotation; and
Including a shaft drive unit provided to rotate the above worm gear,
The above worm gear is installed relative to the shaft so as to have a rotational degree of freedom that is not coupled with the rotation of the shaft,
The above blade driving unit is arranged relative to the worm gear so as to be linked with the axial movement of the worm gear,
When the propeller is rotated in the unfolded state of the above-mentioned foldable propeller structure, the shaft driving unit is provided so as to be uncoupled from the propeller rotation driving,
Among the above blade driving units, the blade moving block and the plurality of link members are provided to be linked with the propeller rotation drive.
A foldable propeller structure, wherein the first screw member and the blade drive unit among the above blade drive units are provided so as to be uncoupled from the propeller rotation drive. delete delete delete In a foldable propeller structure,
shaft;
A propeller including a hub connected to one axial side of the shaft and a plurality of blades connected to the hub at a circumferential interval relative to the hub, wherein each of the plurality of blades is hinge-connected to the hub so as to be able to switch between a deployed state in which it is radially deployed from the hub and a folded state in which it is folded closer to the shaft than the deployed state; and
A shaft drive unit connected to the shaft to provide a driving force for moving the shaft along an axial direction;
Including a blade driving unit connected to the plurality of blades to provide a driving force for switching the plurality of blades to one of the unfolded state and the folded state,
The above blade driving unit,
A blade moving block installed to surround the outer circumference of the above shaft;
A first screw member, which is arranged adjacent to the shaft and parallel to the shaft as a member extending in the axial direction, and is screw-connected to the blade moving block so as to move the blade moving block in the axial direction in response to rotation of the member;
A blade driving unit provided to rotate the first screw member; and
The blade moving block and each of the plurality of blades are connected to each other, and a plurality of link members are included so that the connection can be switched to one of the unfolded state and the folded state according to the axial movement of the blade moving block.
The above shaft drive unit,
A shaft movement block installed to surround the outer circumference of the shaft so that the shaft and axial movement are linked;
A second screw member, which is arranged parallel to the shaft as a member extending in the axial direction, but is arranged at a preset interval from the first screw member and further from the shaft than the first screw member, and is screw-connected to the shaft moving block so as to move the shaft moving block in the axial direction in response to rotation of the member; and
A foldable propeller structure comprising a shaft drive unit configured to rotate the second screw member. In paragraph 5,
The above foldable propeller structure includes an integrated driving unit provided to selectively perform either operation as the blade driving unit or operation as the shaft driving unit,
The above integrated driving unit is,
An integrated drive unit that provides a rotational driving force for a rotational axis orthogonal to the axial direction of the shaft, and wherein the rotational axis is arranged to protrude toward the shaft side;
An inner bevel gear mounted so as to face inwardly toward the shaft with respect to the rotation axis of the integrated drive unit;
An outer bevel gear mounted facing outward on the opposite side of the shaft with respect to the rotation axis of the integrated drive unit;
A first spur gear provided to have the same rotation axis as the first screw member;
A second spur gear arranged on one axial side of the shaft moving block and gear-engaged with the first spur gear; and
Including a bevel gear for blade deployment arranged on one axial side of the second spur gear so as to have the same rotation axis as the second spur gear;
A foldable propeller structure, wherein when the inner bevel gear is coupled with the blade unfolding bevel gear, the integrated driving unit is capable of performing an operation as the blade driving unit. In Article 6,
The above integrated driving unit includes a bevel gear for shaft movement provided on one axial side of the second screw member so as to have the same rotational axis as the second screw member,
A foldable propeller structure, wherein when the outer bevel gear is coupled with the bevel gear for moving the shaft, the integrated driving unit is capable of performing an operation as the shaft driving unit. In Article 7,
The second spur gear and the bevel gear for blade deployment, and the inner bevel gear and the outer bevel gear are arranged with respect to the preset interval section, and the inner bevel gear and the outer bevel gear are arranged outside the second spur gear and the bevel gear for blade deployment,
A foldable propeller structure, wherein the integrated driving unit includes an actuator provided to linearly move the integrated driving unit, in which the inner bevel gear and the outer bevel gear are mounted, in a direction orthogonal to the axial direction of the shaft, in an interval direction corresponding to the preset interval. In Article 8,
The above preset intervals are,
When the integrated drive unit is moved inwardly linearly by the actuator, when viewed in the axial direction, the inner bevel gear and the bevel gear for blade deployment are positioned at positions where bevel gear engagement is possible, and the outer bevel gear and the bevel gear for shaft movement are positioned at positions where bevel gear engagement is released.
A foldable propeller structure, wherein when the integrated drive unit is moved outward linearly by the actuator, when viewed in the axial direction, the inner bevel gear and the blade unfolding bevel gear are positioned at a position where the bevel gear engagement is released, and the outer bevel gear and the shaft moving bevel gear are positioned at a position where the bevel gear engagement is possible. In Article 9,
The above-mentioned bevel gear for shaft movement is provided at an axial position where the bevel gear can be engaged with the outer bevel gear during the outer linear movement of the integrated drive unit.
A foldable propeller structure, wherein the above-described blade unfolding bevel gear is provided at an axial position where the bevel gear engagement with the inner bevel gear can be achieved only when the shaft has moved a preset distance in one axial direction, so that the plurality of blades can maintain the folded state until the shaft has moved a preset distance in one axial direction. In Article 10,
The above preset distance is set by considering that the foldable propeller structure is converted from an internally stowed state to an externally protruding state for an aircraft to which the foldable propeller structure is applied.
A foldable propeller structure, wherein the above external protrusion state includes a state in which at least a portion of the foldable propeller structure protrudes outwardly so that the plurality of blades can be switched from the folded state to the unfolded state. In Article 11,
A foldable propeller structure, wherein the above external protrusion state includes a state in which the plurality of blades are placed in the deployed state and then the foldable propeller structure is re-moved axially to the other side within a limit in which the propeller rotation drive of the plurality of blades is possible. A gas turbine engine comprising a foldable propeller structure according to claim 1 or 5. An aircraft comprising a foldable propeller structure according to claim 1 or 5. A method for controlling a foldable propeller structure according to Article 1 or Article 5,
(a) a step of moving the shaft and the propeller axially to one side; and
(b) A method for controlling a foldable propeller structure, comprising the step of converting the plurality of blades from the folded state to the unfolded state. In Article 15,
(c) a method for controlling a foldable propeller structure, comprising a step of re-moving the foldable propeller structure to the other axial direction within a limit in which the propeller rotation driving of the plurality of blades is possible after the plurality of blades are placed in the unfolded state in the step (b).

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