Aircraft and power unit

Abstract

To provide an aircraft with improved efficiency and flexibility in the aircraft configuration when integrating functional components into the airframe, and a power unit having a configuration for improving said efficiency and flexibility. [Solution] To provide an aircraft or the like having a power unit having a first space with at least one of its upper or lower surfaces open, a propeller having a first through space and connected to the power unit, and a functional part having a predetermined function and at least a portion of which is located within the internal space formed by the first space and the first through space.

Description

Technical Field

[0001] The present invention relates to a flying object and a power device.

Background Art

[0002] In recent years, efforts have been underway to put into practical use services using flying objects (hereinafter collectively referred to as "flying objects") such as drones and unmanned aerial vehicles (UAVs). Along with this, improvements in the performance and efficiency of flying objects are required. Also, in practice, a predetermined function may be added to a flying object by attaching various parts to the airframe. Patent Document 1 discloses a flying object equipped with landing legs capable of buffering the impact during landing.

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0004] However, the flying object of Patent Document 1 uses a method of directly attaching the support member of the landing leg to the arm or frame (hereinafter collectively referred to as "holding part") of the airframe. From the viewpoint of improving the efficiency of the airframe structure of the flying object, it is preferable that there are fewer constituent members. And it is desirable to be able to provide parts having a predetermined function or members (hereinafter referred to as "functional parts") that support the parts without significantly changing the conventional airframe structure.

[0005] Furthermore, since the propeller in Patent Document 1 is of the pull-type, the motor and propeller (hereinafter collectively referred to as the "rotating wing section") are attached to the upper part of the holding section, and the functional section (landing gear) can be attached to the lower part of the holding section. However, if the propeller is of the pusher type, the rotating wing is already attached to the lower part of the holding section, so if the functional section is to be attached to the lower part of the holding section, its placement is limited by the rotating wing. In particular, in the case of landing gear, it is difficult to position it in a way that provides high stability during landing (for example, near the rotating wing, which is far from the center of the aircraft). Therefore, especially in the case of landing gear, it is desirable to have a configuration that can be used for both pull-type and pusher-type aircraft. The same applies to other functional sections in that their placement is also limited.

[0006] Therefore, one objective of the present invention is to provide an aircraft with improved efficiency and flexibility in the aircraft configuration when integrating functional parts into the aircraft, and a power unit having a configuration for improving said efficiency and flexibility. [Means for solving the problem]

[0007] According to the present invention, it is possible to provide an aircraft having a power unit having a first space with at least one of its upper or lower surfaces being open, a propeller having a first through space and connected to the power unit, and a functional part having a predetermined function and at least a portion of which is located within the internal space formed by the first space and the first through space.

[0008] According to the present invention, it is possible to provide a power device having a first space with at least one of its upper or lower surfaces being open, wherein the power device includes a functional part that provides a predetermined function, and the functional part includes a configuration in which at least a portion is located in the first space and does not rotate.

[0009] According to the present invention, a power device is provided having a first space having an opening on at least one of its upper or lower surface, wherein the power device includes a support portion connected to a function-providing portion that provides a predetermined function, and the support portion is configured to be located in the first space with at least a portion of it and not to rotate. [Effects of the Invention]

[0010] According to the present invention, it is possible to provide an aircraft that improves the efficiency and flexibility of its configuration, and a power unit having a configuration for improving said efficiency and flexibility. [Brief explanation of the drawing]

[0011] [Figure 1] This is a conceptual diagram of the power unit as seen from above in an embodiment of the present invention. [Figure 2] This is a conceptual diagram showing the power unit in Figure 1 with a propeller connected, viewed from the side. [Figure 3] Figure 2 is a conceptual diagram of the power unit after it has been disassembled and viewed from the side. [Figure 4] This is a side view of the aircraft in the first embodiment of the present invention. [Figure 5] This is a side view of the aircraft in the second and third embodiments of the present invention. [Figure 6] This is a conceptual diagram showing a disassembled power unit from another embodiment of the present invention, viewed from the side. [Figure 7] This is a functional block diagram of an aircraft in an embodiment of the present invention. [Figure 8] This is a side view of the aircraft in the fourth embodiment of the present invention. [Figure 9] Figure 8 is a top view of the aircraft. [Figure 10] This is a side view showing an existing aircraft equipped with propeller guards. [Figure 11] Figure 10 is a top view of the aircraft. [Figure 12] This is a side view of the aircraft in the fifth embodiment of the present invention. [Figure 13] A side view showing a flying object in the existing technology when it has a nozzle. [Figure 14] A side view of a flying object in the sixth embodiment of the present invention. [Figure 15] A side view of a flying object in the seventh embodiment of the present invention. [Figure 16] [[ID=IO]]A side view of a flying object in the seventh embodiment of the present invention.

Mode for Carrying Out the Invention

[0012] The contents of the embodiments of the present invention will be listed and described. The flying object according to the embodiment of the present invention has the following configuration. [Item 1] A power device having a first space with at least one of the upper surface or the lower surface open, A propeller having a first through-space and connected to the power device, A functional part having a predetermined function and located at least partially within the internal space formed by the first space and the first through-space. A flying object characterized by the above. [Item 2] The flying object according to Item 1, where the functional part includes a non-rotating configuration. A flying object characterized by the above. [Item 3] The flying object according to either Item 1 or Item 2, where a part of the functional part protrudes from the first through-space of the propeller. A flying object characterized by the above. [Item 4] The flying object according to any one of Items 1 to 3, where the first space is a second through-space penetrating the power device. A flying object characterized by the above. [Item 5] The flying object according to any one of Items 1 to 4, The aforementioned functional part includes a contact area that comes into contact with the ground during landing. An aircraft characterized by the following features. [Item 6] An aircraft described in any of items 1 through 5, A portion of the functional part protrudes from a side of the power unit that is in contact with the propeller, different from the other side. An aircraft characterized by the following features. [Item 7] An aircraft described in any of items 1 through 6, The aforementioned functional unit is A support portion located at least a part of the internal space, Includes a function-providing unit connected to the support unit and providing the predetermined function, An aircraft characterized by the following features. [Item 8] The aircraft described in item 7, The aforementioned function-providing unit includes a contact area that comes into contact with the ground during landing, An aircraft characterized by the following features. [Item 9] An aircraft as described in either item 7 or item 8, The aforementioned function-providing unit includes a propeller guard, An aircraft characterized by the following features. [Item 10] An aircraft described in any of items 7 through 9, The aforementioned function-providing unit includes a spraying means, An aircraft characterized by the following features. [Item 11] A power device having a first space in which at least one of the upper or lower surfaces is open, The power unit comprises a functional unit that provides a predetermined function, The functional part includes a configuration in which at least a portion is located in the first space and does not rotate. A power device characterized by the following features. [Item 12] A power device having a first space in which at least one of the upper or lower surfaces is open, The power unit includes a support unit connected to a function-providing unit that provides a predetermined function, The support portion includes a configuration in which at least a portion is located in the first space and does not rotate. A power device characterized by the following features. [Item 13] A power unit as described in either item 11 or item 12, The aforementioned first space is a through space that penetrates the power device. A power device characterized by the following features.

[0013] <Details of embodiments according to the present invention> The following describes an aircraft according to an embodiment of the present invention with reference to the drawings. In the accompanying drawings, identical or similar elements are given identical or similar reference numerals and names, and redundant descriptions of identical or similar elements may be omitted in the description of each embodiment. Furthermore, the features shown in each embodiment are applicable to other embodiments as long as they do not contradict each other.

[0014] Figures 1 and 2 illustrate an outer rotor type motor as a power unit 20 for an aircraft according to an embodiment of the present invention. The power unit 20 comprises, for example, a rotor 22 having permanent magnets 21 and a stator 24 having windings 23. The propeller 110 is connected to the power unit 20 and rotates in accordance with the rotation of the power unit 20, and is capable of generating lift from the lift-generating surface of the propeller 110.

[0015] The configuration of the power unit 20 is not limited to this, and any configuration that includes the internal space and functional unit 10 described later is acceptable. For example, in the case of an inner rotor type motor, it may be a motor having a pipe-shaped hollow structure and a hollow shaft, in which the through space within the hollow shaft is used as the first space described later.

[0016] As illustrated in Figures 1 and 3, the power unit 20 includes a space 25 located, for example, in the center of a top view (hereinafter referred to as the "first space 25"). This first space 25 is open on at least one of the top or bottom surfaces of the power unit 20, allowing the functional unit 10 to protrude from the power unit 20. For example, in Figure 3, only the top surface of the power unit 20 is open, while in Figure 4, both the top and bottom surfaces of the power unit 20 are open. In Figure 1, the opening of the first space 25 is located in the center of a top view, but it is not limited to the center of a top view; it may be located anywhere as long as the functional unit 10 does not obstruct the operation of the propeller 110. The propeller 110 also includes a first through space 112. Here, the space in which the first space 25 of the power unit 20 and the first through space 112 of the propeller 110 are connected to each other is referred to as the "internal space". Each of these spaces may be linear, bent, or curved, and their shape is not particularly limited.

[0017] The functional part 10 of the aircraft according to an embodiment of the present invention may, for example as shown in Figure 3, protrude from the center of the stator 24 in a top view, and the rotor 22 may protrude from the power unit 20 through the first space 25. Furthermore, the functional part 10 may be configured to protrude through the propeller 110, and the functional part 10 itself may function as, for example, the landing gear of the aircraft 100, as shown in Figure 4. Alternatively, as shown in Figure 5, for example, the functional part 10 may consist of a support part 11 located at least a portion of the internal space, and a function-providing part 12 connected to the support part 11 and providing a predetermined function (for example, landing gear).

[0018] Figure 6 illustrates a modified example of a functional part 10 provided in an aircraft according to an embodiment of the present invention. The functional part 10 may protrude from external components of the power unit 20, such as the holding parts 120a and 120b of the aircraft that hold the rotor blade section including the power unit 20 and the propeller 110 (for example, including a motor mount (not shown) if one is present). Alternatively, the functional part 10 may protrude indirectly via a fixing member (not shown) for the functional part 10. These functional parts 10 may be configured to protrude from the power unit 20 and the propeller 110 through a first space in the power unit 20 and a first through space in the propeller 110.

[0019] Furthermore, the functional unit 10 may be configured so that it does not touch the rotor 22 of the power unit 20, and at least the support portion 11 does not rotate, or the entire functional unit 10 does not rotate. Alternatively, if there is a through shaft, the functional unit 10 may be configured so that the power unit 20 does not touch the through shaft, or the functional unit 10 contacts the through shaft using bearings or the like. In this way, the functional unit 10 may be configured not to rotate, unaffected by the rotation of the power unit 20. Note that these embodiments are merely simplified examples, and necessary components may be added as appropriate.

[0020] In this way, by utilizing the internal space of the power unit 20 and the propeller 110, a functional unit 10 with a predetermined function can be easily provided without significantly altering the conventional aircraft configuration. Furthermore, regardless of whether the propeller 110 is a pull-type or pusher-type, the functional unit 10 can be positioned using the space above and below the rotor blades, so its placement is not particularly limited.

[0021] Furthermore, the functional unit 10 can have various functions. For example, the functional unit 10 can be a landing gear, lighting device, antenna, propeller guard, thruster (nozzle), heat sink, airflow rectifier, wheel, aerodynamic parts, or support member for payloads.

[0022] The function-providing unit 12 may be configured to be connectable to and replaceable with multiple types of attachments on the support unit 11, depending on the requirements. If replacement is possible, it is desirable that the mounting part of the support unit 11 be standardized so that multiple types of attachments can be easily attached and detached. The attachment connection configuration of the mounting part can be easily replaced by using well-known connection methods such as connectors and screws.

[0023] Furthermore, since the functional unit 10 can operate independently of the rotation of the power unit 20, it is possible to perform predetermined rotations and oscillations using a servo or motor provided separately from the power unit 20. This allows for, for example, changing the direction of the nozzle or changing the angle of the aerodynamic parts.

[0024] <Configuration of the flying object 100> The aircraft 100, as illustrated in Figure 4, etc., is equipped with at least a propeller 110 and a power unit 20, and it is desirable that it carries energy (for example, a secondary battery, fuel cell, fossil fuel, etc.) to operate them.

[0025] Note that the aircraft 100 shown in the illustration is simplified for the purpose of facilitating the explanation of the structure of the present invention, and detailed components such as the control unit are not shown.

[0026] The aircraft 100 may, for example, have its direction of travel in the direction of arrow D in the figure (-Y direction). In the following explanation, terms may be used according to the following definitions: Forward / backward direction: +Y direction and -Y direction, Up / down direction (or vertical direction): +Z direction and -Z direction, Left / right direction (or horizontal direction): +X direction and -X direction, Forward direction of travel (forward): -Y direction, Backward direction (backward): +Y direction, Upward direction (up): +Z direction, Downward direction (downward): -Z direction

[0027] The propellers 110a and 110b rotate in response to the output from the power unit 20. The rotation of the propellers 110a and 110b generates thrust to allow the aircraft 100 to take off from its starting point, move, and land at its destination. The propellers 110a and 110b can rotate to the right, stop, and rotate to the left, among other things.

[0028] The propeller 110 of the aircraft 100 of the present invention has one or more blades. The number of blades (rotor) can be any number (e.g., 1, 2, 3, 4, or more). The shape of the blade can be any shape, such as flat, curved, twisted, tapered, or a combination thereof. The shape of the blade can be changed (e.g., extension, folding, bending, etc.). The blade may be symmetrical (having the same upper and lower surfaces) or asymmetrical (having upper and lower surfaces of different shapes). The blade can be formed into an airfoil, wing, or a geometric shape suitable for generating dynamic aerodynamic forces (e.g., lift, thrust) when the blade is moved through the air. The geometric shape of the blade can be appropriately selected to optimize the dynamic aerodynamic characteristics of the blade, such as increasing lift and thrust and reducing drag.

[0029] Furthermore, the propeller of the aircraft 100 of the present invention may be fixed-pitch, variable-pitch, or a combination of fixed-pitch and variable-pitch, but is not limited to these.

[0030] The power unit 20 generates the rotation of the propeller 110, and the drive unit may include, for example, an electric motor or an engine. The blades are driveable by the motor and rotate around the motor's axis of rotation (for example, the motor's long axis).

[0031] The blades can all rotate in the same direction, or they can rotate independently. Some blades can rotate in one direction, while others rotate in other directions. The blades can all rotate at the same speed, or they can rotate at different speeds. The speed can be determined automatically or manually based on the dimensions of the moving object (e.g., size, weight) and the control state (speed, direction of movement, etc.).

[0032] The aircraft 100 uses a flight controller or radio control system to determine the rotation speed of each motor and the flight angle according to the wind speed and direction. This allows the aircraft to move, such as ascending and descending, accelerating and decelerating, and changing direction.

[0033] The aircraft 100 can perform autonomous flight in accordance with routes and rules set in advance or during flight, or it can be controlled using a remote control.

[0034] <Functional block diagram of aircraft 100> Figure 7 shows a functional block diagram of the aircraft 100, and the functional block in Figure 7 is a minimum reference configuration. The flight controller is a so-called processing unit. The processing unit may have one or more processors, such as a programmable processor (e.g., a central processing unit (CPU)). The processing unit has memory (not shown) that is accessible. The memory stores logic, code, and / or program instructions that the processing unit can execute to perform one or more steps. The memory may include a separable medium such as an SD card or random access memory (RAM), or an external storage device. Data acquired from cameras and sensors may be transmitted directly to and stored in memory. For example, still images and video data captured by cameras, etc., are recorded in internal memory or external memory.

[0035] The processing unit includes a control module configured to control the state of the rotorcraft. For example, the control module has six degrees of freedom (translational motion x, y, and z, and rotational motion θ).x , θ y and θ z The control module controls the propulsion mechanism (power unit 20, etc.) of a rotary-wing aircraft to adjust its spatial arrangement, speed, and / or acceleration. The control module can control one or more of the states of the mounted components and sensors.

[0036] The processing unit can communicate with a transceiver configured to transmit and / or receive data from one or more external devices (e.g., terminals, display devices, or other remote controllers). The transceiver can use any suitable means of communication, such as wired or wireless communication. For example, the transceiver can utilize one or more of the following: local area networks (LANs), wide area networks (WANs), infrared, wireless, Wi-Fi, point-to-point (P2P) networks, telecommunications networks, cloud communication, etc. The transceiver can transmit and / or receive one or more of the following: data acquired by sensors, processing results generated by the processing unit, predetermined control data, user commands from terminals or remote controllers, etc.

[0037] The sensors according to this embodiment may include inertial sensors (accelerometers, gyroscopes), GPS sensors, proximity sensors (e.g., LiDAR), or vision / image sensors (e.g., cameras).

[0038] <Details of the first embodiment> Figure 4 illustrates a configuration in which the functional unit 10 functions as a landing gear, as a first embodiment of the present invention.

[0039] As described above, in a vertical takeoff and landing aircraft 100, a wider spacing between the landing legs provides greater stability when the aircraft 100 touches the landing surface. Therefore, the ideal position for the landing legs to allow for a wide spacing without extending the retaining section 120 is, for example, near the bottom of the rotor blades. However, especially when the propeller 110 is a pusher type, the landing legs must be positioned to avoid contact with the propeller 110, thus avoiding the propeller's rotation plane. As a result, avoiding the landing legs towards the center of the aircraft reduces their spacing, while avoiding them towards the outside of the aircraft requires extension of the retaining section 120 for landing leg connection. Consequently, with conventional configurations, especially when the propeller 110 is a pusher type, it has been difficult to achieve both improved landing stability and improved aircraft efficiency.

[0040] Therefore, in the first embodiment shown in Figure 4, the functional unit 10 utilizes the internal space consisting of the first space 25 of the power unit 20 and the first through space 112 of the propeller 110 to enable the provision of landing gear below the power unit 20 even in a propeller-driven aircraft 100.

[0041] The landing gear has a contact surface that makes contact with the ground, and may also be equipped with dampers or other devices to mitigate impact during landing or when placing the aircraft down.

[0042] This makes it possible to achieve both improved landing stability and increased aircraft efficiency, even when the Propeller 110 is a pusher type.

[0043] Furthermore, in the design of an aircraft, the power unit 20 connected to the propeller 110 and the holding parts 120a and 120b are generally mounted robustly from the perspective of anticipated loads. Therefore, especially when the functional part 10 is the landing gear, it becomes possible to mount the landing gear, which is subjected to loads during landing, in the same location as or close to the power unit 20, etc., and the area requiring robustness can be concentrated, thereby suppressing weight increase and dispersion of the center of gravity.

[0044] <Details of the second embodiment> Figure 5 illustrates a second embodiment of the present invention, in which the function-providing unit 12 of the functional unit 10 functions as a landing gear.

[0045] As illustrated in Figure 5, in an aircraft 100 using a tractor-type propeller 110, for example, the placement of the landing gear is not restricted by the propeller 110 when the landing gear is provided near the bottom of the rotor blades and retaining parts 120a and 120b, as in the conventional method. However, by utilizing the internal space formed by the first space 25 of the power unit 20 and the first through space 112 of the propeller 110, it becomes possible to provide the landing gear with a simpler configuration. Also, as illustrated in Figure 5, the functional part 10 may consist of a support part 11 protruding from the power unit 20 and a function providing part 12 connected to the support part 11 and providing the function of a landing gear.

[0046] <Details of the third embodiment> Figure 5 illustrates a third embodiment of the present invention, in which the function-providing unit 12 of the functional unit 10 functions as a lighting device (e.g., an LED) or an antenna device.

[0047] As illustrated in Figure 5, even in an aircraft 100 using a tractor-type propeller 110, the functional unit 10 can be placed above the rotor blades. More specifically, for example, a lighting device or an antenna device can be placed above the rotor blades as a functional unit 12. Although the configuration shown in Figure 5 is for an aircraft 100 using a tractor-type propeller 110, it can also be provided for an aircraft 100 using a pusher-type propeller 110 instead. Furthermore, the functional unit 10 is not limited to being placed on the connection side of the propeller 110, but can be used in any configuration, such as above or below a pusher-type aircraft, above or below a tractor-type aircraft, or in both the upper and lower directions for pusher-type and tractor-type aircraft. This makes it possible to reduce the weight increase of the aircraft by reducing the number of components, and to improve the efficiency of the aircraft by improving the flexibility of placement.

[0048] <Details of the fourth embodiment> Figures 8 and 9 illustrate a fourth embodiment of the present invention, in which the functional unit 10, or the function-providing unit 12 within the functional unit 10, functions as a propeller guard.

[0049] Since the propeller guards can be attached from the top of the aircraft 100, the attachment and removal of the propeller guards while the aircraft 100 is on the ground is easier compared to attachment from the side or from below, as shown in Figures 10 and 11.

[0050] The configurations shown in Figures 8 and 9 are for an aircraft 100 using a tractor-type propeller 110, but it is also possible to equip an aircraft 100 using a pusher-type propeller 110 instead. Furthermore, the functional unit 10 is not limited to being installed on the connection side of the propeller 110, but can be used in any configuration, such as being installed above or below a pusher-type aircraft, above or below a tractor-type aircraft, or in both the upper and lower directions for pusher-type and tractor-type aircraft. This makes it possible to reduce the weight increase of the aircraft by reducing the number of components, and to improve the efficiency of the aircraft by improving the flexibility of placement.

[0051] <Details of the Fifth Embodiment> Figure 12 illustrates a fifth embodiment of the present invention, in which the functional unit 10, or the function-providing unit 12 within the functional unit 10, functions as an injection means.

[0052] The functional unit 10 is a pipe or hose through which a predetermined liquid or powder passes. If necessary, as illustrated in Figure 12, the pipe or the like may be made part of the support unit 11, and a spraying means (nozzle) connected to the pipe or the like, which performs spraying, atomizing, or ejection, may be made the functional unit 12. By providing the functional unit 10, or the functional unit 12 within the functional unit 10, on the lower side of the aircraft 100, effects such as strongly hitting the target object with the wake of the propeller 110 or flying the liquid or powder further can be obtained.

[0053] In existing multi-rotor type pesticide spraying aircraft, when utilizing a similar effect, as shown in Figure 13, pipes for passing liquids or powders are provided externally, separate from the aircraft's holding sections 120a and 120b. In the functional section 10 according to the present invention, by providing pipes for passing liquids or powders inside the aircraft's holding sections 120a and 120b, air resistance during flight can be reduced compared to the aircraft 100, which has separate pipes on the outside.

[0054] The configuration shown in Figure 12 is for an aircraft 100 using a tractor-type propeller 110, but it can also be provided for an aircraft 100 using a pusher-type propeller 110 instead. However, the configuration is not limited to providing the functional unit 10 on the connection side of the propeller 110; it can be used in any configuration, such as providing the functional unit 10 above or below a pusher-type aircraft, above or below a tractor-type aircraft, or in both the upper and lower directions for pusher-type and tractor-type aircraft. This makes it possible to reduce the weight increase of the aircraft by reducing the number of components, and to improve the efficiency of the aircraft by improving the flexibility of placement. Furthermore, as mentioned above, if the thrust direction is the same as the direction of the propeller wake, effects such as efficient utilization of the propeller wake can be expected.

[0055] <Details of the sixth embodiment> Figure 14 illustrates a sixth embodiment of the present invention, in which the functional unit 10, or the function-providing unit 12 within the functional unit 10, functions as a heat sink.

[0056] As illustrated in Figure 14, the functional unit 10, or the functional providing unit 12 of the functional unit 10, can be used as a heat sink for the power unit 20 by utilizing the movement of the wake generated by the rotation of the propeller 110. By using a material with high thermal conductivity, the heat generated inside the power unit 20 is drawn to the outside, increasing the surface area exposed to the outside air. Furthermore, because the airflow around the heat sink is less likely to stagnate due to the wake of the propeller 110, the power unit 20 can be cooled efficiently.

[0057] In particular, power units 20 designed with waterproofing and splashproofing in mind have high airtightness to prevent the ingress of water and dust. In such power units 20, cooling the inside of the power unit 20 is difficult because outside air is not taken into the power unit 20. Therefore, improving cooling performance by enlarging the heat sink is effective.

[0058] Examples of heat sink configurations include pipe-shaped heat pipes, which are commonly used in heat sink mechanisms, and sirocco fan shapes that are designed to avoid obstructing the airflow behind the propeller.

[0059] <Details of the 7th Embodiment> Figures 15 and 16 illustrate a seventh embodiment of the present invention, in which the functional unit 10, or the function-providing unit 12 within the functional unit 10, functions as a rectifier.

[0060] When the propeller 110 of the aircraft 100 rotates, a wake is generated. As illustrated in Figure 15, by providing the functional unit 10, or the functional providing unit 12 of the functional unit 10, as an airflow straightening device on the side where the wake is generated, the generation of wake vortices that would lead to a decrease in flight efficiency is prevented, thereby improving flight efficiency.

[0061] Furthermore, as shown in Figure 16, if the aircraft 100 is a VTOL aircraft, the power unit 20 is used in the forward and backward direction during horizontal flight and other times, except during vertical takeoff and landing and hovering. At this time, the flight efficiency of the aircraft 100 is improved by providing a functional unit 10, or a functional providing unit 12 of the functional unit 10, as an airflow straightening device on the propeller connection side and the opposite side of the propeller connection side of the power unit 20.

[0062] Furthermore, if the functional unit 10, or the function-providing unit 12 within the functional unit 10, has multiple functions, for example, a metal material that acts as a heat sink may be used to create a shape that has a rectifying effect on the underside of the aircraft. In this case, the functional unit 10, or the function-providing unit 12 within the functional unit 10, can serve as a heat sink, a rectifier, and a landing gear. By consolidating functions in this way, it is possible to prevent an increase in air resistance and weight.

[0063] The embodiments described above are merely illustrative to facilitate understanding of the present invention and are not intended to limit its interpretation. The present invention can be modified and improved without departing from its spirit, and it goes without saying that the present invention includes equivalents thereof. [Explanation of Symbols]

[0064] 10 Functional Sections 11 Support part 12 Function provision department 20 Power plant 25 The first space 100 flying objects 110 Propeller 112 First Penetration Space 120 Holding part

Claims

1. A power unit having a first space in which at least one of the upper or lower surfaces is open, A propeller having a first through-space and connected to the power unit, A functional part having a predetermined function and at least a portion of which is located within the internal space formed by the first space and the first through space, An aircraft characterized by the following features.

2. The flying body according to claim 1, The aforementioned functional unit includes a configuration that does not rotate. An aircraft characterized by the following features.

3. An aircraft according to either claim 1 or claim 2, A portion of the functional part protrudes from the first through space of the propeller. An aircraft characterized by the following features.

4. An aircraft according to any one of claims 1 to 3, The first space is a second through-space that penetrates the power unit. An aircraft characterized by the following features.

5. An aircraft according to any one of claims 1 to 4, The aforementioned functional part includes a contact area that comes into contact with the ground during landing. An aircraft characterized by the following features.

6. An aircraft according to any one of claims 1 to 5, A portion of the functional part protrudes from a side of the power unit that is in contact with the propeller, different from the other side. An aircraft characterized by the following features.

7. An aircraft according to any one of claims 1 to 6, The aforementioned functional unit is A support portion located at least a part of the internal space, Includes a function-providing unit connected to the support unit and providing the predetermined function, An aircraft characterized by the following features.

8. The flying body according to claim 7, The aforementioned function-providing unit includes a contact area that comes into contact with the ground during landing, An aircraft characterized by the following features.

9. An aircraft according to either claim 7 or claim 8, The aforementioned function-providing unit includes a propeller guard, An aircraft characterized by the following features.

10. An aircraft according to any one of claims 7 to 9, The aforementioned function-providing unit includes a spraying means, An aircraft characterized by the following features.

11. A power device having a first space in which at least one of the upper or lower surfaces is open, The power unit comprises a functional unit that provides a predetermined function, The functional part includes a configuration in which at least a portion is located in the first space and does not rotate. A power device characterized by the following features.

12. A power device having a first space in which at least one of the upper or lower surfaces is open, The power unit includes a support unit connected to a function-providing unit that provides a predetermined function, The support portion includes a configuration in which at least a portion is located in the first space and does not rotate. A power device characterized by the following features.

13. A power device according to either claim 11 or claim 12, The first space is a through-space that penetrates the power device. A power device characterized by the following features.

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