Method for manufacturing a propulsion unit having a rim wing, and a propulsion unit and a flying object manufactured by the method

Abstract

The present invention provides a method for manufacturing a propulsion unit having a rim wing, and a propulsion unit and an aircraft manufactured by the method. The rim wing can protect a propeller from surrounding obstacles while significantly reducing drag during forward flight. To this end, the present invention provides a method for manufacturing a propulsion unit having a rim wing, and a propulsion unit and an aircraft manufactured by the method. The method comprises: a plate member forming step of forming an airfoil-shaped plate member whose outer contour in a side view forms an airfoil; a rim wing forming step of forming a through hole in the airfoil-shaped plate member to form a rim wing member whose outer contour in a side view forms at least a portion of an airfoil; and a propeller setting step of setting a propeller in the through hole.

Description

Technical Field

[0001] The present invention relates to a method for manufacturing a propulsion unit having a rim wing (RIM FOIL), and a propulsion unit and an aircraft manufactured by the method. In particular, it relates to a method for manufacturing a propulsion unit having a rim wing that can reduce resistance during forward flight, and a propulsion unit and an aircraft manufactured by the method. Background Art

[0002] In recent years, the use of unmanned aerial vehicles (UAVs) has rapidly increased in a variety of fields, including surveillance, reconnaissance, transportation, and leisure. Among UAVs, multi-rotor UAVs are particularly capable of vertical takeoff and landing, omnidirectional movement, and hovering. Furthermore, multi-rotor UAVs offer advantages over other types of UAVs, such as coaxial reversing and single-rotor UAVs, in terms of simplicity and efficiency.

[0003] However, rotary-wing aircraft present problems. Because their propellers are completely exposed, obstacles such as branches can get caught on them, making it difficult to maintain flight. Furthermore, when flying close to crowded areas, the rotating force of the propellers can cause injuries. Especially in the design of large unmanned aerial vehicles, such as multi-rotor urban airmobility vehicles, exposed propellers pose a significant threat and can be fatal in the event of a crash in an urban area. Furthermore, there is a drawback that the noise generated by the propeller tips cannot be blocked.

[0004] To this end, the addition of a propeller protection ring or duct surrounding the propeller protects the propeller from obstacles and eliminates the risk of propeller injuries. Furthermore, the propeller protection ring or duct guides the flow of air through the propeller, reducing thrust loss during vertical takeoff and landing.

[0005] However, since the propeller protection ring or duct is designed only considering the flow characteristics of air passing through the propeller during vertical takeoff and landing of the aircraft, there is a problem of significantly increased resistance when the aircraft actually flies forward.

[0006] As a prior art document, there is Korean Patent Publication No. 2016-0041697 (published on April 18, 2016). Summary of the Invention

[0007] Technical problem to be solved by the invention

[0008] The purpose of the present invention is to solve the existing problems. The present invention provides a method for manufacturing a propulsion unit with a rim wing, as well as a propulsion unit and a flying body manufactured by the method. The rim wing can protect the propeller from the influence of surrounding obstacles while significantly reducing the resistance during flight.

[0009] Means used to solve problems

[0010] In order to achieve the above-mentioned purpose of the present invention, the manufacturing method of a propulsion unit with a rim wing according to one embodiment of the present invention is characterized in that it includes: a plate component forming step, forming an airfoil-type plate component whose outer contour line on the side view forms an airfoil shape; a rim wing forming step, forming a through hole at the airfoil-type plate component, forming a rim wing component whose outer contour line on the side view forms at least a part of the shape of the airfoil; and a propeller setting step, setting a propeller at the through hole.

[0011] In a method for manufacturing a propulsion unit with a rim wing according to an embodiment of the present invention, the airfoil-shaped plate component can be arranged so that its projection area in a top view surrounds the projection area of ​​the propeller, and the cross-sectional scale of the airfoil shape parallel to the forward direction can change continuously.

[0012] In a method for manufacturing a propulsion unit having a rim wing according to an embodiment of the present invention, at least a portion of the cross-section of the rim wing component may include: a leading edge cross-section portion equipped with a leading edge (Leading Edge) at the front end portion; and a trailing edge cross-section portion equipped with a trailing edge (Trailing Edge) at the rear end portion.

[0013] A space cross-section may be provided between the leading edge cross-section and the trailing edge cross-section. The space cross-section is a portion of a through hole in which the propeller is provided.

[0014] In a method for manufacturing a propulsion unit having a rim wing according to an embodiment of the present invention, in the plate component forming step, the zero-lift angle of attack (Zero-lift Angle Of Attack) of the cross-section of the airfoil shape of the airfoil-shaped plate component can be set to a negative (-) angle.

[0015] In the method for manufacturing a propulsion unit having a rim wing according to an embodiment of the present invention, in the airfoil forming step, the through hole may be formed in a direction perpendicular to a chord line of a cross section of the airfoil shape of the rim wing component.

[0016] In a method for manufacturing a propulsion unit having a rim wing according to one embodiment of the present invention, in the propeller setting step, the rotation axis of the propeller can be arranged perpendicular to the chord line so that the chord line of the cross-section of the airfoil shape of the rim wing component is arranged parallel to the propeller.

[0017] In a propulsion unit according to an embodiment of the present invention, it is characterized in that the propulsion unit is manufactured by the aforementioned manufacturing method.

[0018] In an embodiment of the present invention, a flying object is characterized by comprising: a main body; and a propulsion unit having rim wings for making the main body fly.

[0019] The flying object according to an embodiment of the present invention may further include a fixed wing disposed between the main body and the rim wing member. In this case, the rim wing member and the fixed wing may have the same airfoil cross-section.

[0020] The flying object according to an embodiment of the present invention may further include a passenger cabin coupled to the main body, and a forward thrust propeller for forward thrust may be provided in the passenger cabin.

[0021] Effects of the Invention

[0022] According to the present invention, the airfoil-shaped rim having an airfoil-shaped cross-section can minimize damage to the propeller caused by surrounding obstacles during flight and safety accidents, and can reduce resistance during flight to significantly increase the lift and thrust of the flying body.

[0023] According to the present invention, there is also an effect of reducing noise by suppressing the formation of a vortex at the tip of the propeller. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 is a flow chart illustrating a method for manufacturing a propulsion unit with a rim wing according to an embodiment of the present invention.

[0025] Figure 2 FIG. 1 is a perspective view showing an airfoil-type panel component manufactured according to an embodiment of the present invention.

[0026] Figure 3 yes Figure 2 Top view (a), AA cross-section (b) and BB cross-section (c) of the airfoil-shaped plate component.

[0027] Figure 4 is a graph showing setting values ​​of an airfoil according to an embodiment of the present invention.

[0028] Figure 51 is a perspective view showing a rim wing member manufactured according to an embodiment of the present invention.

[0029] Figure 6 yes Figure 5 Top view (a), AA cross-section (b), BB cross-section (c) and CC cross-section (d) of the rim wing component.

[0030] Figure 7 is a side sectional view showing an arrangement state of a propeller according to an embodiment of the present invention.

[0031] Figure 8 is a perspective view showing a flying object according to an embodiment of the present invention.

[0032] Figure 9 It is enlarged to show Figure 8 A perspective view (a) and a top view (b) of the propulsion unit. DETAILED DESCRIPTION

[0033] Hereinafter, preferred embodiments of the present invention that can specifically achieve the above-mentioned problems to be solved will be described with reference to the accompanying drawings. When describing the embodiments, the same names and the same reference numerals may be used for the same structures, and additional description thereof may be omitted.

[0034] The present invention provides a method for manufacturing a propulsion unit with a rimfoil, which can protect a propeller from surrounding obstacles while reducing resistance during flight.

[0035] The rim wing is a streamlined propeller protection rim that is configured to surround the propeller to minimize damage to the propeller from surrounding obstacles and safety accidents, and has an airfoil-shaped side profile to maximize lift and minimize drag during forward flight.

[0036] Furthermore, an airfoil generally refers to a streamlined shape, such as the cross-section of a fixed-wing wing, a rudder, or a propeller, designed to maximize lift and minimize drag during movement within a fluid. In such an airfoil, the amount of lift and drag generated varies depending on the chord line, which is the straight line connecting the leading edge and the trailing edge. Furthermore, the angle of attack, which is the angle between the chord line and the direction of the relative airflow, is also known to be an important factor in determining lift.

[0037] Figure 1 is a flow chart illustrating a method for manufacturing a propulsion unit with a rim wing according to an embodiment of the present invention.

[0038] Reference Figure 1 The manufacturing method of the propulsion unit with the rim wing according to the embodiment of the present invention may include: a plate component forming step S110, a rim wing forming step S120, and a propeller setting step S130.

[0039] Figure 2 is a perspective view showing an airfoil-type plate component manufactured according to one embodiment of the present invention, Figure 3 yes Figure 2 Top view (a), AA cross-section (b) and BB cross-section (c) of the airfoil-shaped plate component.

[0040] Further references Figure 2 and Figure 3 The plate member forming step S110 is a step of forming the airfoil-shaped plate member 110 .

[0041] In the airfoil type panel member 110 according to the present embodiment, the contour line in the side view may form an airfoil shape.

[0042] The projected area of ​​the airfoil-shaped plate member 110 in a plan view may be set to surround the projected area of ​​the propeller 130 .

[0043] Furthermore, in the airfoil type plate member 110 , the cross-sectional dimension of the airfoil shape parallel to the advancing direction may continuously change.

[0044] That is, in the airfoil type plate member 110, as Figure 3 As shown in (a) in FIG. 1 , the airfoil section 111 disposed on the center line C1 in the advancing direction A1 may have the largest area, and the area of ​​the airfoil section 111 may gradually decrease as moving along the left and right side directions A2 perpendicular to the advancing direction A1 .

[0045] Furthermore, the airfoil-profile plate member 110 may have both ends in the left and right directions A2 perpendicular to the advancing direction A1 cut off, and vertical surfaces 110 a may be provided at both left and right ends of the airfoil-profile plate member 110 .

[0046] In addition, the airfoil-shaped plate member 110 may be filled as shown in the figure, or may be provided with a hollow portion inside as opposed to the figure.

[0047] As a method for processing the airfoil-shaped plate member 110 according to this embodiment, the surface of the plate member can be cut to form an airfoil shape, or the plate member can be bent to form an airfoil shape. In addition, multiple plate members can be assembled and connected to form an airfoil shape.

[0048] On the other hand, in the panel member forming step S110 according to the present embodiment, the zero-lift angle of attack of the airfoil-shaped cross section 111 of the airfoil-shaped panel member 110 may be set to have a negative (-) angle.

[0049] In some cases, a rotary wing-shaped aircraft such as the propeller 130 is required to slightly tilt the aircraft body including the propeller 130 in the forward direction A1 to obtain thrust during forward travel.

[0050] When the zero-lift angle of attack (Zero-lift Angle Of Attack) of the airfoil section is set to maintain 0 degrees, as mentioned above, when the flying body is tilted in the forward direction to fly forward, since the angle of attack (Angle Of Attack) of the airfoil section changes to a negative (-) angle, negative lift and drag will occur and increase in the downward direction.

[0051] However, as in this embodiment, when setting the airfoil cross-section of the airfoil-shaped plate member 110, an airfoil is designed with a zero-lift angle of attack having a negative (-) angle. Thus, even when the aircraft, including the propeller 130, is tilted in the forward direction A1 for forward flight, the angle of attack of the airfoil cross-section 111 can continue to maintain a positive (+) lift coefficient in order to obtain thrust. Consequently, the drag caused by the airfoil shape can be further reduced during forward flight.

[0052] The zero lift angle of attack of the preferred airfoil section 111 according to this embodiment may be set within a range of -9 degrees to -5 degrees.

[0053] Here, -9 degrees to -5 degrees may be the maximum angle at which the airfoil section 111 can be tilted along the forward direction A1 during forward flight.

[0054] For example, Figure 4 The graph shows the setting values ​​of the airfoil according to the embodiment of the present invention, showing the angle of attack (Angle Of Attack), the ratio of lift to drag (L / D), the lift coefficient (C L :Lift coefficient), drag coefficient (C P :Drag coefficient) and the pressure center on the chord (C D : Center of Pressure in % of Chord from leading edge, the center of pressure of the chord from the leading edge, in %) value.

[0055] like Figure 4 As shown, the selected airfoil is set to have a zero lift angle of attack of -9 degrees.

[0056] Right now, Figure 4 The illustrated airfoil is configured to have a zero-lift angle of attack of -9 degrees. Thus, when performing forward flight while maintaining a slope of less than 9 degrees along the forward direction A1, a positive (+) lift coefficient is consistently achieved. Consequently, when performing forward flight while maintaining a slope of less than 9 degrees, drag due to the airfoil's cross-sectional shape is reduced, while lift and thrust are further increased.

[0057] Figure 5 is a perspective view showing a rim wing component manufactured according to an embodiment of the present invention, Figure 6 yes Figure 5 Top view (a), AA cross-section (b), BB cross-section (c) and CC cross-section (d) of the rim wing component.

[0058] As described above, when the manufacture of the airfoil-profile panel member 110 is completed, the rim wing member 120 is formed from the airfoil-profile panel member 110 .

[0059] Further references Figure 5 and Figure 6 The rim wing forming step S120 is a step of forming the rim wing member 120 from the airfoil type plate member 110 .

[0060] The rim wing part 120 according to the embodiment may be formed by forming a through hole 121 at the airfoil type plate part 100 .

[0061] The through hole 121 is a portion forming the inner diameter of the rim wing member 120 and in which the propeller 130 is provided, and may have a diameter greater than that of the propeller 130 .

[0062] In addition, the through hole 121 may be formed in a direction perpendicular to the chord line CL of the airfoil section 111. Such a through hole 121 may guide the airflow passing through the propeller 130 to a downward direction.

[0063] The rim wing member 120 manufactured in this manner may have a ring shape and may have an inner diameter D1 larger than the diameter of the propeller 130. In addition, the rim wing member 120 may be formed to have the same width W along the circumferential direction except for the vertical surface 110a.

[0064] In addition, the outline of the rim wing member 120 in a side view may constitute at least a portion of the airfoil shape. At least a portion of the cross section of the rim wing member 120 may include a leading edge section 122a having a leading edge at the front end and a trailing edge section 122b having a trailing edge at the rear end.

[0065] That is, Figure 6As shown in (a) of FIG. 1 , the rim wing member 120 may include a central region CA where the propeller 130 is arranged and side regions SA arranged at both left and right ends of the central region CA in a left-right direction A2 perpendicular to the forward direction A1 .

[0066] Here, if Figure 6 (b) and Figure 6 As shown in (c), the central area CA of the rim wing part 120 includes, relative to the cross section parallel to the forward direction A1, a leading edge cross section 122a equipped with a leading edge at the front end, and a trailing edge cross section 122b equipped with a trailing edge at the rear end.

[0067] Between the front edge cross-sectional portion 122a and the rear edge cross-sectional portion 122b, a space cross-sectional portion 122c is arranged as a part of the through hole 121. Here, the space cross-sectional portion 122c is a virtual cross-sectional portion connecting the front edge cross-sectional portion 122a and the rear edge cross-sectional portion 122b.

[0068] At this time, the outer contours of the leading edge cross-section portion 122 a , the space cross-section portion 122 c , and the trailing edge cross-section portion 122 b form an airfoil shape 122 corresponding to the airfoil cross section 111 of the airfoil-shaped panel member 111 .

[0069] In addition, if Figure 6 As shown in (d) , the side area SA of the rim wing member 120 may have an airfoil-shaped cross section corresponding to the airfoil cross section 111 of the airfoil-shaped plate member 111 excluding the space cross section 122 c from a cross section parallel to the advancing direction A1 .

[0070] Therefore, the leading edge cross-section portion 122a including the leading edge LE can reduce the drag during forward flight, and the trailing edge cross-section portion 122b including the trailing edge TE can suppress the generation of excessive vortices in the rear region of the rim wing during forward flight.

[0071] In addition, since the propeller 130 disposed inside the through hole 121 is not exposed outside the rim wing member 120 in a side view, damage to the propeller 130 caused by surrounding obstacles during operation and safety accidents can be minimized.

[0072] Furthermore, the propeller 130 disposed inside the through hole 121 can avoid the airflow guided by the rim wing member 120 .

[0073] Therefore, the rim wing member 120 can reduce the resistance to relative airflow during forward flight and can further increase lift and thrust.

[0074] On the other hand, the left and right ends of the rim wing member 120 may be provided with vertical surfaces 110 a previously formed in the plate member forming step S110 . Such vertical surfaces 110 a may be combined with the main body of the flying object or the fixed wing.

[0075] As described above, when the manufacture of the rim wing member 120 is completed, the propeller 130 is installed.

[0076] That is, the propeller setting step S130 is a step of setting the propeller 130 at the through hole 121 of the rim wing member 120 .

[0077] Figure 7 is a side sectional view showing an arrangement state of a propeller according to an embodiment of the present invention.

[0078] Further references Figure 7 , the propeller 130 can be configured inside the through hole 121 .

[0079] At this time, the rotation axis 130 c of the propeller 130 may be arranged perpendicular to the chord line CL so that the propeller 130 is arranged parallel to the chord line CL of the airfoil 111 .

[0080] That is, the center line of the through hole 121 and the rotation axis 130c of the propeller 130 can be arranged on the same axis. Therefore, not only can the propeller 130 be arranged to minimize the gap between it and the through hole 121, but the airflow passing through the propeller 130 can be more stably and evenly guided downward through the through hole 121.

[0081] Furthermore, by appropriately adjusting the distance between the inner diameter D1 of the through hole 121 and the tip of the propeller 130 or making design changes, the vortex at the tip of the propeller 130 can be controlled to reduce noise.

[0082] Furthermore, since the propeller 130 disposed inside the through hole 121 is not exposed outside the rim wing member 120 in a side view, damage to the propeller 130 caused by surrounding obstacles during operation and safety accidents can be minimized.

[0083] When the position of the propeller 130 is set in this manner, the driving unit 140 may be connected to the rotating shaft 130c of the propeller 130. The driving unit 140 rotates the propeller 130 and may use a motor directly connected to the rotating shaft 130c of the propeller 130.

[0084] Hereinafter, a flying object according to an embodiment of the present invention will be described.

[0085] Figure 8 is a perspective view showing a flying object according to an embodiment of the present invention, Figure 9 It is enlarged to show Figure 8A perspective view (a) and a top view (b) of the propulsion unit.

[0086] Reference Figure 8 and Figure 9 , the flying object 1000 according to this embodiment may include a main body 200 and a propulsion unit 100 .

[0087] The main body 200 can provide storage space for items or passengers. For example, in the case of an unmanned aerial vehicle, it can provide space for batteries, cameras, communication components, control components, etc. Furthermore, in the case of a manned aerial vehicle, it can provide space for engines, communication components, control components, an adjustment room, and passenger space. The form of the main body 200 is not particularly limited.

[0088] Furthermore, the flying object 1000 according to this embodiment may further include a passenger cabin 300 .

[0089] The passenger compartment 300 is coupled to the main body 200 and can provide additional cargo or passenger space as needed. The passenger compartment 300 can be detachably mounted on the main body 200. The form of the passenger compartment 300 is not particularly limited.

[0090] Furthermore, the passenger cabin 300 may be equipped with a forward thrust propeller 310 for providing thrust in the forward direction.

[0091] In this way, when the passenger cabin 300 is equipped with a forward thrust propeller 310, the inclination angle of the flying body 1000 including the propulsion unit 100 can be reduced when the flying body 1000 is flying forward, so in the case of the propulsion unit 100 having a rim wing, the lift can be further increased and the thrust of the flying body 1000 can be improved.

[0092] The propulsion unit 100 may form an airflow toward the lower portion of the main body 200 to make the main body 200 fly.

[0093] The propulsion unit 100 may include a propeller 130, a driving unit 140 for rotating the propeller 130, and a ring-shaped rim wing member 120 coupled to the body 200 and surrounding the propeller 130. Repeated detailed description of the propulsion unit 100 having such a rim wing will be omitted.

[0094] The main body 200 may be connected to at least one propulsion unit 100, and the propulsion units 100 according to the embodiment may be arranged radially from the center of the main body 200. In this embodiment, six propulsion units 100 are shown, but the number is not particularly limited.

[0095] In addition, the flying object 1000 according to this embodiment may further include fixed wings 150 .

[0096] The fixed wing 150 may be disposed between the main body 200 and the propulsion unit 100 and may have an airfoil-shaped cross section. In this case, the fixed wing 150 and the rim wing member 120 may have the same airfoil-shaped cross section.

[0097] One end of the fixed wing 150 may be coupled to the main body 200, and the other end may be coupled to the rim wing part 120 of the propulsion unit 100. With such a fixed wing 150, the lift of the flying object 1000 may be further increased, and a more stable flight may be ensured.

[0098] Furthermore, a cantilever support beam 141 for supporting the propeller 130 and the driving unit 140 may be provided at the other end of the fixed wing 150 .

[0099] Various cables for providing power to the driving portion 140 or controlling the propulsion unit 100 may be built inside the support beam 141 .

[0100] Furthermore, the support beam 141 can be formed to extend from the end of the fixed wing 150 toward the propulsion unit 100 without protruding toward the upper and lower surfaces of the fixed wing 150 and the rim wing member 120, so as to avoid the flow of airflow directed from the surfaces of the fixed wing 150 and the rim wing member 120. In other words, the cross-sectional width of the support beam 141 can be formed to be smaller than the cross-sectional width of the fixed wing end region where the support beam 141 is provided, and can also be formed to be smaller than the cross-sectional width of the fixed wing joint provided at the rim wing member 120.

[0101] In addition, the support beam 141 may also be disposed on the lower side of the fixed wing 150 and the rim wing member 120 . In this case, the cantilevered support beam 141 may more stably support the propulsion unit 100 through the fixed wing 150 .

[0102] On the other hand, the other end of the fixing wing 150 can be coupled to the vertical surface of the rim wing member 120 (110a: see Figure 6 At this time, the rigidity may be weakened depending on the specifications of the fixed wing 150 and the propulsion unit 100.

[0103] To address this issue, one end of the rim wing member 120 that connects to the fixed wing 150 can be cut to form a joint surface 127. This joint surface 127 allows the fixed wing 150 and the rim wing member 120 to be joined over a wider area, thus ensuring a stable connection between the fixed wing 150 and the propulsion unit 100. Furthermore, since the airfoil cross-section is maintained at the connection between the fixed wing 150 and the rim wing member 120, lift can also be increased.

[0104] Moreover, when setting the airfoil shape of the fixed wing 150, by setting it so that the zero-lift angle of attack (Zero-lift Angle Of Attack) formed by the chord line CL and the relative airflow has a negative (-) angle, even if the fixed wing 150 is tilted in the forward direction A1 to obtain thrust, the positive (+) lift coefficient can continue to be maintained, so that the resistance of the flying body 1000 will be reduced during forward flight, and the lift and thrust will be further increased.

[0105] As described above, the preferred embodiments of the present invention have been described with reference to the accompanying drawings. However, those skilled in the art can make various modifications or changes to the present invention without departing from the scope of the concept and field of the present invention described in the claims.

[0106] Industrial Availability

[0107] The present invention uses an airfoil-shaped rim with an airfoil-shaped cross-section to minimize damage to the propeller and safety accidents caused by surrounding obstacles during flight, reduce resistance during flight, and thus significantly increase the lift and thrust of the flying body, and reduce noise by suppressing the formation of vortexes at the tip of the propeller. Therefore, it can be widely used in the aircraft industry, such as vertical take-off and landing flying bodies such as drones.

Claims

1. A method for manufacturing a propulsion unit having a rim wing, characterized in that: include: a plate component forming step, forming an airfoil-shaped plate component with an outer contour line on a side view to form an airfoil shape; a rim wing forming step of forming a through hole in the airfoil-shaped plate component to form a rim wing component whose outer contour line in a side view is formed into at least a part of the shape of an airfoil; as well as The propeller setting step comprises setting a propeller at the through hole. Cutting off one end portion of the rim wing member to form a joint surface for joining a fixed wing having an airfoil-shaped cross section extending from the main body, In the airfoil-shaped plate component, the cross-sectional dimension parallel to the advancing direction changes continuously, and the cross-sectional area of ​​the airfoil shape decreases toward the left and right sides perpendicular to the advancing direction. The airfoil-shaped plate member and the fixed wing are formed so that the zero-lift angle of attack of the cross section of the airfoil shape has a negative angle. The rim wing member has a central region where the propeller is arranged and side regions arranged on both sides of the central region, wherein a cross section parallel to the forward direction in the side region has an airfoil-shaped cross section corresponding to a cross section of the airfoil-shaped plate member. The central region includes, with respect to a cross section parallel to the advancing direction, a leading edge cross section having a leading edge at a front end portion and a trailing edge cross section having a trailing edge at a rear end portion; and a space cross-sectional portion disposed between the front edge cross-sectional portion and the rear edge cross-sectional portion and forming a portion of the through hole.

2. The method for manufacturing a propulsion unit with a rim wing according to claim 1, characterized in that: The airfoil-shaped plate member is arranged so that its projection area in a plan view surrounds the projection area of ​​the propeller.

3. The method for manufacturing a propulsion unit with a rim wing according to claim 1, characterized in that: The zero-lift angle of attack is set to -9 degrees to -5 degrees.

4. The method for manufacturing a propulsion unit with a rim wing according to claim 1, characterized in that: In the airfoil forming step, the through hole is formed in a direction perpendicular to a chord line of a cross section of the airfoil shape of the rim wing member.

5. The method for manufacturing a propulsion unit with a rim wing according to claim 4, characterized in that: In the propeller installation step, the rotation axis of the propeller is arranged perpendicularly to the chord line so that the chord line of the cross section of the airfoil shape of the rim wing member and the propeller are arranged in parallel.

6. A propulsion unit manufactured by the method of any one of claims 1 to 5.

7. A flying object comprising: A propulsion unit according to claim 6 for causing the body to fly.

8. The flying object according to claim 7, wherein: The fixed wing is arranged between the main body and the rim wing member, The rim wing member and the fixed wing have cross-sections of the same airfoil shape.

9. The flying object according to claim 7, wherein: Also included is a passenger compartment coupled to the main body, The passenger cabin is equipped with a forward thrust propeller for providing thrust in the forward direction.

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