Flying object and power device

Abstract

The present invention relates to an aircraft and a power unit, wherein the aircraft improves the efficiency and flexibility of the fuselage structure when a functional unit is provided on the fuselage, and the power unit has a structure for improving the efficiency and flexibility. The aircraft and the like include: a power unit having a first space, at least one of the upper and lower surfaces of which is open; a propeller having a first through-space, the propeller being connected to the power unit; and a functional unit having a predetermined function, at least a portion of which is located within an interior 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, the practical application of services using aerial vehicles (hereinafter collectively referred to as "aerial vehicles"), such as drones and unmanned aerial vehicles (UAVs), has continued to grow. This has led to demands for improved performance and efficiency in these vehicles. Furthermore, in practice, various components are sometimes attached to the aircraft body to provide additional functionality. Patent Document 1 discloses an aerial vehicle equipped with landing gear that cushions the impact of landing.

[0003] Prior art literature

[0004] Patent Literature

[0005] Patent Document 1: International Publication No. 2016 / 179827 Summary of the Invention

[0006] Problems to be solved by the invention

[0007] However, the aircraft disclosed in Patent Document 1 employs a method of directly attaching the landing gear support members to the fuselage arms and frames (hereinafter collectively referred to as "holding members") of the fuselage. However, from the perspective of achieving improved fuselage structural efficiency, fewer structural components are desirable. Furthermore, it is desirable to be able to include components with specified functions and components supporting them (hereinafter referred to as "functional portions") without significantly altering the conventional fuselage structure.

[0008] In addition, the propeller of Patent Document 1 is of a pull type, so the motor and propeller (hereinafter collectively referred to as the "rotor unit") are installed on the upper part of the retaining part, and the functional part (landing gear) can be installed on the lower part of the retaining part. However, in the case of a push type propeller, since the rotor is already installed on the lower part of the retaining part, when the functional part is to be installed on the lower part of the retaining part, its configuration will be limited by the rotor. In particular, for the landing gear, it is difficult to adopt a configuration that is highly stable during landing (for example, near the rotor at a position far from the center of the fuselage, etc.). Therefore, considering the situation of the landing gear in particular, it is desirable to adopt a structure that can be used for both pull-type and push-type flying bodies. Moreover, the same is true for other functional parts in that the configuration is limited.

[0009] Therefore, an object of the present invention is to provide a flying object and a power plant having a structure for improving the efficiency and flexibility of the fuselage structure when functional parts are provided on the fuselage.

[0010] Solutions for solving problems

[0011] According to the present invention, a flying body can be provided, characterized in that it comprises: a power unit having a first space, at least one of the upper surface and the lower surface of which is open; a propeller having a first through space, which is connected to the power unit; and a functional part having a prescribed function, at least a part of which is located in an internal space formed by the first space and the first through space.

[0012] According to the present invention, a power device can be provided, which has a first space, at least one of the upper surface and the lower surface of the first space is open, and the power device is characterized in that the power device has a functional part that provides a specified function, at least a part of the functional part is located in the first space, and includes a non-rotating structure.

[0013] According to the present invention, a power device can be provided, which has a first space, at least one of the upper surface and the lower surface of the first space is open, and the power device is characterized in that the power device has a supporting part connected to a function providing part that provides a prescribed function, at least a part of the supporting part is located in the first space, and includes a non-rotating structure.

[0014] Effects of the Invention

[0015] According to the present invention, it is possible to provide a flying body having improved structural efficiency and flexibility, and a power plant having a structure for improving the efficiency and flexibility. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of a power device in an embodiment of the present invention when viewed from above.

[0017] Figure 2 is Figure 1 Schematic diagram of the power unit connected to the propeller and viewed from the side.

[0018] Figure 3 It will Figure 2 Schematic diagram of the power unit exploded and viewed from the side.

[0019] Figure 4 It is a side view of the flying object in the first embodiment of the present invention.

[0020] Figure 5 It is a side view of the flying object in the second embodiment and the third embodiment of the present invention.

[0021] Figure 6It is a schematic diagram showing a power unit in another embodiment of the present invention disassembled and viewed from the side.

[0022] Figure 7 This is a functional block diagram of a flying object in an embodiment of the present invention.

[0023] Figure 8 It is a side view of a flying object in a fourth embodiment of the present invention.

[0024] Figure 9 yes Figure 8 view of a flying body.

[0025] Figure 10 This is a side view showing a conventional flying object equipped with a propeller guard.

[0026] Figure 11 yes Figure 10 view of a flying body.

[0027] Figure 12 It is a side view of a flying object in a fifth embodiment of the present invention.

[0028] Figure 13 This is a side view showing a conventional flying object equipped with a nozzle.

[0029] Figure 14 It is a side view of a flying object in a sixth embodiment of the present invention.

[0030] Figure 15 It is a side view of a flying object in a seventh embodiment of the present invention.

[0031] Figure 16 It is a side view of a flying object in a seventh embodiment of the present invention. DETAILED DESCRIPTION

[0032] The following describes the details of the embodiments of the present invention. The flying object according to the embodiment of the present invention has the following structure.

[0033] [Project 1]

[0034] A flying object, characterized by having:

[0035] A power device having a first space, at least one of an upper surface and a lower surface of the first space being open;

[0036] a propeller having a first through space, the propeller being connected to the power device; and

[0037] The functional portion has a predetermined function, and at least a portion of the functional portion is located in the internal space formed by the first space and the first through space.

[0038] [Project 2]

[0039] The flying object according to item 1 is characterized in that

[0040] The functional portion includes a non-rotating structure.

[0041] [Item 3]

[0042] The flying object according to item 1 or item 2, characterized in that

[0043] A portion of the functional portion protrudes from the first through space of the propeller.

[0044] [Item 4]

[0045] The flying object according to any one of items 1 to 3, characterized in that

[0046] The first space is a second through space that penetrates the power device.

[0047] [Item 5]

[0048] The flying object according to any one of items 1 to 4, characterized in that

[0049] A ground contact portion that contacts the ground during landing is included as the functional portion.

[0050] [Item 6]

[0051] The flying object according to any one of items 1 to 5, characterized in that

[0052] A portion of the functional portion protrudes from a side of the power unit that is different from the side in contact with the propeller.

[0053] [Item 7]

[0054] The flying object according to any one of items 1 to 6, characterized in that

[0055] The functional part includes:

[0056] a support portion, at least a portion of which is located in the interior space; and

[0057] The function providing portion is connected to the support portion and provides the predetermined function.

[0058] [Item 8]

[0059] The flying object according to item 7 is characterized in that

[0060] A ground contact portion that contacts the ground during landing is included as the function providing portion.

[0061] [Item 9]

[0062] The flying object according to item 7 or item 8, characterized in that

[0063] A propeller protection member is included as the function providing portion.

[0064] [Item 10]

[0065] The flying object according to any one of items 7 to 9, characterized in that

[0066] An ejection component is included as the function providing portion.

[0067] [Item 11]

[0068] A power device comprises a first space, at least one of an upper surface and a lower surface of the first space is open,

[0069] The power unit has a functional unit that provides a specified function.

[0070] At least a portion of the functional portion is located in the first space and includes a non-rotating structure.

[0071] [Item 12]

[0072] A power device comprises a first space, at least one of an upper surface and a lower surface of the first space is open,

[0073] The power device includes a support portion connected to a function providing portion that provides a predetermined function.

[0074] At least a portion of the support portion is located in the first space and includes a non-rotating structure.

[0075] [Item 13]

[0076] The power plant according to item 11 or item 12 is characterized in that:

[0077] The first space is a through space that penetrates the power device.

[0078] <Details of the embodiment of the present invention>

[0079] The following describes an aircraft according to an embodiment of the present invention with reference to the accompanying drawings. In the accompanying drawings, identical or similar elements are designated by identical or similar reference numerals and names, and repeated descriptions of identical or similar elements may be omitted in the description of each embodiment. Furthermore, features described in each embodiment may also be applied to other embodiments, as long as they do not conflict with each other.

[0080] exist Figure 1 and Figure 2 In the embodiment of the present invention, an outer rotor type motor is exemplified as the power unit 20 included in the flying object. The power unit 20 includes, 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 response to the rotation of the power unit 20, generating lift from the lift-generating surface of the propeller 110.

[0081] Furthermore, the structure of the power unit 20 is not limited to this, and any structure may be used as long as it includes the internal space and the functional unit 10 described below. For example, in the case of an inner rotor type motor, a motor having a tubular hollow structure and a hollow shaft may be used, and the through space within the hollow shaft may be used as the first space described below.

[0082] like Figure 1 and Figure 3 As shown in the examples, the power unit 20 has a space 25 (hereinafter referred to as "first space 25") located in the center when viewed from the top. The first space 25 is an opening in at least one of the upper and lower surfaces of the power unit 20, and the functional unit 10 can protrude from the power unit 20. For example, Figure 3 The middle part is a structure in which only the upper surface of the power unit 20 is open. Figure 4 The upper and lower surfaces of the power unit 20 are open. Figure 1 The opening of the first space 25 is located in the center when viewed from above, but this is not limited to the center. The functional portion 10 can be located anywhere as long as it does not interfere with the operation of the propeller 110. Furthermore, the propeller 110 also has a first through-space 112. Here, the space connecting the first space 25 of the power unit 20 and the first through-space 112 of the propeller 110 is referred to as the "inner space." These spaces can be straight, zigzag, or curved; their shapes are not particularly limited.

[0083] The functional unit 10 of the flying object according to the embodiment of the present invention may be configured as follows, for example. Figure 3 As shown, the structure protrudes from the center of the stator 24 in top view, passes through the rotor 22 via the first space 25 and protrudes from the power device 20. In addition, the functional part 10 is configured to also penetrate the propeller 110 and protrude from the propeller 110, for example Figure 4 As shown, the functional unit 10 itself functions as, for example, a landing gear of the flying object 100. Alternatively, for example Figure 5 As shown, the functional portion 10 is composed of a support portion 11 and a function providing portion 12 . At least a portion of the support portion 11 is located in the internal space. The function providing portion 12 is connected to the support portion 11 and is a member that provides a predetermined function (eg, landing gear).

[0084] Figure 6 , a modification of the functional portion 10 possessed by the flying body involved in the embodiment of the present invention is illustrated in FIG. Alternatively, the functional portion 10 may protrude from a structure outside the power unit 20, such as retaining portions 120a and 120b of the flying body (for example, in the case of having a motor mounting portion (not shown), the motor mounting portion is also included), and the retaining portions 120a and 120b are used to retain the rotor portion including the power unit 20 and the propeller 110. In addition, the functional portion 10 may protrude indirectly via a component (not shown) that fixes the functional portion 10. Moreover, these functional portions 10 can be configured to protrude from the power unit 20 and the propeller 110 via the first space of the power unit 20 and the first through space of the propeller 110.

[0085] Furthermore, the functional portion 10 may not contact the rotor 22 of the power unit 20, and at least the support portion 11 may be configured to not rotate, or the functional portion 10 as a whole may be configured to not rotate. Alternatively, in the case of a through shaft, the functional portion 10 may be configured to not contact the power unit 20, or may be configured to be connected to the through shaft using bearings or the like. In this way, the functional portion 10 may be configured to not rotate without being affected by the rotation of the power unit 20. Furthermore, these methods are merely simplified examples, and necessary components may be appropriately added.

[0086] In this way, by utilizing the internal space of the power plant 20 and propeller 110, it is possible to easily incorporate the functional unit 10 having the desired function without significantly changing the conventional airframe structure. Furthermore, whether the propeller 110 is a pull or push type, the functional unit 10 can be arranged using the space above and below the rotor blade, thus presenting no particular limitations on its placement.

[0087] Furthermore, the functional unit 10 can have various functions, such as landing gear, lighting, antenna, propeller guard, injection unit (nozzle), radiator, fairing, wheel, aerodynamic parts, and a member for supporting a carried object.

[0088] The function providing portion 12 may also be a structure that can be connected to the support portion 11 as a variety of accessories, depending on the requirements, and can be replaced. When configured to be replaceable, it is desirable that the mounting portion of the support portion 11 be standardized to facilitate the replacement of various types of accessories. The accessory connection structure of the mounting portion can be easily replaced by using a known connection method such as a connector or bolts.

[0089] Furthermore, the functional unit 10 can operate independently of the rotation of the power unit 20, and thus can be rotated or swung as desired using a servo or motor provided separately from the power unit 20. This allows, for example, the direction of the nozzle to be changed, or the angle of the aerodynamic component to be altered.

[0090] <Structure of Flying Object 100>

[0091] Figure 4 The flying object 100 exemplified in the examples includes at least elements such as a propeller 110 and a power unit 20 for flight, and is preferably equipped with energy (eg, a secondary battery, a fuel cell, a fossil fuel, etc.) for operating these elements.

[0092] Furthermore, the illustrated flying object 100 is simplified for ease of explanation of the structure of the present invention, and detailed structures such as a control unit are not shown.

[0093] The flying object 100 can be traveling in the direction indicated by the arrow D (-Y direction) in the figure. Furthermore, in the following description, terms are sometimes used in a differentiated manner according to the following definitions. Front-to-back direction: +Y direction and -Y direction; Up-to-down direction (or vertical direction): +Z direction and -Z direction; Left-to-right direction (or horizontal direction): +X direction and -X direction; Travel direction (forward): -Y direction; Reverse direction (back): +Y direction; Ascending direction (upward): +Z direction; Descending direction (downward): -Z direction.

[0094] 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 propulsion for the aircraft 100 to take off from its departure point, move, and land at its destination. Furthermore, the propellers 110a and 110b can rotate clockwise, stop, and rotate counterclockwise.

[0095] The propeller 110 of the flying object 100 of the present invention has one or more blades. It can also be any number of blades (rotors) (for example, 1, 2, 3, 4, or more blades). In addition, the shape of the blade can be any shape such as a flat shape, a curved shape, a twisted shape, a conical shape, or a combination of these shapes. Moreover, the shape of the blade can be changed (for example, telescopic, folded, bent, etc.). The blade can be symmetrical (having the same upper and lower surfaces) or asymmetrical (having upper and lower surfaces of different shapes). In order to generate dynamic aerodynamic forces (for example, lift, thrust) when the wing, wing or blade moves in the air, the blade can be formed into a suitable geometric shape. The geometric shape of the blade can be appropriately selected to increase lift and thrust, reduce drag, etc. to optimize the dynamic aerodynamic characteristics of the blade.

[0096] Furthermore, the propellers of the flying object 100 of the present invention may have a fixed pitch, a variable pitch, or a combination of fixed and variable pitches, but are not limited thereto.

[0097] The power device 20 is a device that rotates the propeller 110. For example, the driving unit can include an electric motor or an engine, etc. The blades can be driven by the motor to rotate around the rotation axis of the motor (for example, the long axis of the motor).

[0098] The blades can all rotate in the same direction or independently. Some of the blades can rotate in one direction, while others rotate in another direction. The blades can all rotate at the same speed or 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 (e.g., speed, direction of movement, etc.).

[0099] The flying object 100 is controlled by a flight controller, a proportional controller, etc., which determines the rotation speed and flight angle of each motor according to wind speed and wind direction.

[0100] The flying object 100 can perform autonomous flight following a path set in advance or during flight, or can perform flight controlled by a proportional controller.

[0101] <Functional Block Diagram of Aircraft 100>

[0102] Figure 7 FIG. 1 shows a functional block diagram of the flying object 100. Figure 7 The functional blocks are a minimum reference structure. The flight controller is a so-called processing unit. The processing unit can have one or more processors such as a programmable processor (for example, a central processing unit (CPU)). The processing unit has a memory not shown in the figure and can access the memory. In order to perform one or more steps, the memory stores logical rules, codes, and / or program instructions executable by the processing unit. Alternatively, the memory includes, for example, a detachable medium such as an SD card, a random access memory (RAM), or an external storage device. Alternatively, the data obtained from the camera or sensor is directly transmitted and stored in the memory. For example, still image and motion image data captured by a camera or the like are recorded in a built-in memory or an external memory.

[0103] The processing unit includes a control component configured to control the state of the rotary-wing aircraft. For example, the control component controls the propulsion mechanism (such as the power unit 20, etc.) of the rotary-wing aircraft in order to adjust the spatial configuration, speed, and / or acceleration of the rotary-wing aircraft having six degrees of freedom (translational motion (Japanese: 並進運動) x, y, z, and rotational motion θx, θy, θz). The control component can control at least one of the states of the mounting part and the sensor devices.

[0104] The processing unit can communicate with the transmitting and receiving unit, which is configured to transmit data to and / or receive data from one or more external devices (such as a terminal, a display device, or other remote controllers). The transmitting and receiving unit can use any suitable communication component such as wired communication or wireless communication. For example, the transmitting and receiving unit can use at least one of a local area network (LAN), a wide area network (WAN), infrared, wireless, WiFi, a peer-to-peer (P2P) network, a telecommunications network, cloud communication, etc. The transmitting and receiving unit can transmit and / or receive at least one of the data acquired by the sensor, the processing result generated by the processing unit, specified control data, user commands from the terminal or remote controller, etc.

[0105] The sensor devices according to the present embodiment may include an inertial sensor (an acceleration sensor, a gyro sensor), a GPS sensor, a proximity sensor (such as lidar), or a vision-graphic sensor (such as a camera).

[0106] <Details of the First Embodiment>

[0107] Figure 4 As the first embodiment of the present invention, the structure in the case where the functional unit 10 functions as a landing gear is illustrated.

[0108] As described above, in the flying object 100 that performs vertical takeoff and landing, when the flying object 100 contacts the landing surface, it is stable if the interval between the landing gears is wide. Thus, a setting position of the landing gear that can obtain a wide interval without extending the holding part 120, etc. is, for example, near the lower side of the rotor. However, especially when the propeller 110 is a pusher type, in order to prevent the landing gear from contacting the propeller 110, it is necessary to set the landing gear avoiding the propeller rotation plane. Therefore, when avoiding toward the center side of the fuselage, the interval of the landing gear is narrowed; when avoiding toward the outer side of the fuselage, the holding part 120 needs to be extended in order to connect the landing gears. Thus, in the conventional structure, especially when the propeller 110 is a pusher type, it is difficult to balance improving landing stability and improving fuselage efficiency.

[0109] Thus, in Figure 4In the first embodiment shown, the functional part 10 utilizes the internal space formed by the first space 25 of the power unit 20 and the first through space 112 of the propeller 110, and a landing gear can be set under the power unit 20 even in the flying body 100 where the propeller 110 is a propulsion type.

[0110] The landing gear includes a ground contact portion that contacts the ground, and may also include a shock absorber or the like that cushions the impact during landing or when placing the flying object.

[0111] Thus, even when the propeller 110 is of a pusher type, it is possible to achieve both improved landing stability and improved fuselage efficiency.

[0112] Furthermore, in aircraft design, based on the expected loads, the power unit 20 and the retaining portions 120a and 120b connected to the propeller 110 are generally required to be securely mounted. Therefore, particularly when the functional unit 10 is a landing gear, the landing gear, which bears the load during landing, can be mounted in the same or adjacent location as the power unit 20, etc. This allows for the concentration of secure locations, thereby minimizing weight increases and distributing the center of gravity.

[0113] <Details of Second Embodiment>

[0114] Figure 5 In the second embodiment of the present invention, a configuration in which the function providing portion 12 of the functional portion 10 functions as a landing gear is exemplified.

[0115] like Figure 5 As shown in the example, in the aircraft 100 using the traction-type propeller 110, when the landing gear is provided near the lower portion of the rotor and the holding portions 120a and 120b as in the conventional case, the arrangement is not limited by the propeller 110. 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, the landing gear can be provided with a simpler structure. Figure 5 As illustrated, the functional portion 10 is composed of a support portion 11 protruding from the power unit 20 and a function providing portion 12 connected to the support portion 11 and providing a function as a landing gear.

[0116] <Details of the Third Embodiment>

[0117] Figure 5 In the third embodiment of the present invention, a configuration in which the function providing unit 12 of the functional unit 10 functions as a lighting device (eg, LED) or an antenna device is exemplified.

[0118] like Figure 5As shown in the example, even in the case of an aircraft 100 using a traction propeller 110, the functional unit 10 can be provided above the rotor unit. More specifically, a lighting device or an antenna device can be provided above the rotor unit as the functional unit 12. Figure 5 The illustrated configuration depicts an aircraft 100 employing a traction-type propeller 110, but an aircraft 100 employing a pusher-type propeller 110 is also possible. Furthermore, the functional unit 10 is not limited to being located on the connection side of the propeller 110; it can also be located above or below a pusher-type aircraft, above or below a traction-type aircraft, or above and below both a pusher-type and a traction-type aircraft. This can reduce the number of structural components, minimize the increase in fuselage weight, and enhance configuration flexibility, thereby improving the efficiency of the aircraft.

[0119] <Details of the Fourth Embodiment>

[0120] Figure 8 and Figure 9 Herein, as a fourth embodiment of the present invention, a configuration in which the functional portion 10 or the function providing portion 12 in the functional portion 10 functions as a propeller protector is exemplified.

[0121] During the installation of the propeller guard, the installation can be performed from the upper surface of the aircraft 100. Figure 10 and Figure 11 Compared with installation from the side or installation from below, it is easier to perform installation and removal work of the propeller guard when the flying object 100 is landed.

[0122] and, Figure 8 and Figure 9 The illustrated structure uses the functional unit 10 on an aircraft 100 with a traction-type propeller 110. However, the functional unit 10 can also be used on an aircraft 100 with a pusher-type propeller 110. Furthermore, the functional unit 10 is not limited to being located on the connection side of the propeller 110; it can also be used in any configuration, such as above or below a pusher-type aircraft, above or below a traction-type aircraft, or above and below both a pusher-type and a traction-type aircraft. This can reduce the number of structural components, minimize weight increases, and enhance configuration flexibility, thereby improving the efficiency of the aircraft.

[0123] <Details of Fifth Embodiment>

[0124] Figure 12 In the fifth embodiment of the present invention, a configuration in which the functional portion 10 or the function providing portion 12 in the functional portion 10 functions as an ejection member is exemplified.

[0125] Functional part 10 is a conduit or hose for circulating specified liquid or powder, and can also be used as required, such as Figure 12 As shown in the example, a conduit or the like is used as part of the structure of the support portion 11, and a spraying component (nozzle) connected to the conduit or the like for spraying, atomizing, and injecting is used as the function providing portion 12. The functional portion 10 or the function providing portion 12 in the functional portion 10 is set on the lower side of the flying body 100, thereby achieving the following effect: the wake of the propeller 110 is used to blow the liquid, powder, or particles strongly toward the object, or to scatter them farther.

[0126] In the existing multi-axis pesticide sprayer, when utilizing the same effect, as Figure 13 As shown, separate ducts for circulating liquids, powders, and granules are provided externally from the holding portions 120a and 120b of the flying object. In the functional portion 10 according to the present invention, compared to the flying object 100 in which separate ducts are provided externally, the provision of ducts for circulating liquids, powders, and granules within the holding portions 120a and 120b of the flying object reduces air resistance during flight.

[0127] and, Figure 12 The structure shown is an aircraft 100 using a traction-type propeller 110, but it is also possible to use an aircraft 100 using a pusher-type propeller 110 instead. However, the structure is not limited to the structure in which the functional portion 10 is provided on the connection side of the propeller 110. It can also be used in any structure such as a structure in which the functional portion 10 is provided above or below a propulsion-type aircraft, above or below a traction-type aircraft, or above and below both propulsion-type and traction-type aircraft. This can reduce the increase in airframe weight by reducing the number of structural components, increase configuration flexibility, and thus improve the efficiency of the aircraft. In addition, when the jet direction is the same as the flow direction of the propeller wake as described above, it is expected that the effects of the propeller wake can be effectively utilized.

[0128] <Details of Sixth Embodiment>

[0129] Figure 14 1 and 2 , as a sixth embodiment of the present invention, a configuration in which the functional unit 10 or the function providing unit 12 in the functional unit 10 functions as a heat sink is exemplified.

[0130] like Figure 14As illustrated, by utilizing the wake motion generated by the rotation of the propeller 110, the functional unit 10 or the function providing unit 12 within the functional unit 10 can be configured as a heat sink for the power unit 20. By using a material with high thermal conductivity to draw heat generated within the power unit 20 to the outside, not only is the area exposed to the outside air easily increased, but the wake of the propeller 110 also prevents airflow from stagnating near the heat sink, thereby efficiently cooling the power unit 20.

[0131] In particular, power unit 20, designed to be waterproof and drip-proof, requires high airtightness to prevent the ingress of water and dust. Since outside air is not drawn into power unit 20, such power unit 20 is difficult to cool internally. Therefore, enlarging the radiator is effective in improving cooling performance.

[0132] Furthermore, examples of the heat sink structure include a pipe-shaped structure called a heat pipe used in a known heat sink mechanism and a multi-blade fan structure designed to avoid obstructing the airflow of the propeller wake.

[0133] <Details of Seventh Embodiment>

[0134] Figure 15 and Figure 16 1 and 2 , as a seventh embodiment of the present invention, a configuration in which the functional unit 10 or the function providing unit 12 in the functional unit 10 functions as a rectifier is exemplified.

[0135] When the propeller 110 of the flying object 100 rotates, a wake is generated. Figure 15 As illustrated, by arranging the functional unit 10 or the function providing unit 12 in the functional unit 10 as an airflow straightening device on the side where the wake is generated, it is possible to prevent the wake from generating vortices that would reduce flight efficiency, thereby improving flight efficiency.

[0136] In addition, if Figure 16 As shown, if the aircraft 100 is a vertical takeoff and landing aircraft, the power unit 20 is used in the forward and backward directions during horizontal flight, other than during vertical takeoff and landing or hovering. In this case, the functional unit 10 or the function providing unit 12 within the functional unit 10 is provided on the propeller connection side and the opposite side of the propeller connection side of the power unit 20, serving as an airflow straightening device, thereby improving the flight efficiency of the aircraft 100.

[0137] Furthermore, if the functional unit 10 or the function-providing unit 12 within it has multiple functions, for example, a metal material acting as a heat sink can be used below the fuselage to create a shape that has a rectifying effect. In this case, the functional unit 10 or the function-providing unit 12 within it can simultaneously serve as a heat sink, a rectifying device, and a landing gear. This integration of functions can prevent increases in air resistance and weight.

[0138] The above embodiments are merely examples for easy understanding of the present invention and should not be construed as limiting the present invention. Of course, the present invention can be modified and improved without departing from the spirit thereof, and the present invention also includes equivalents thereof.

[0139] Description of Reference Numerals

[0140] 10: Functional part; 11: Support part; 12: Function providing part; 20: Power device; 25: First space; 100: Flying body; 110: Propeller; 112: First through space; 120: Holding part.

Claims

1. A flying object, characterized in that: have: A power device having a first space, at least one of an upper surface and a lower surface of the first space being open; a propeller having a first through space, the propeller being connected to the power device; a pair of holding portions for holding the power unit and the propeller on one side in the vertical direction; as well as Functional parts, which have prescribed functions and include a ground contact part that comes into contact with the ground during landing, At least a portion of the ground portion is located in an inner space formed by the first space and the first through space. The grounding portion includes an end portion that protrudes from the first space and is provided on the one side of the pair of holding portions so as to face the pair of holding portions across the power unit and the propeller in the vertical direction.

2. The flying object according to claim 1, wherein: The functional portion includes a non-rotating structure.

3. The flying object according to claim 1, wherein: A portion of the functional portion protrudes from the first through space of the propeller.

4. The flying object according to claim 1, wherein: The first space is a second through space that penetrates the power device.

5. The flying object according to any one of claims 1 to 4, characterized in that A portion of the functional portion protrudes from a side of the power unit that is different from the side in contact with the propeller.

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