JP2021187276A - Flying vehicle - Google Patents

Abstract

To provide a flying vehicle that is able to stably carry a heavy load as a result of stabilizing the center of gravity of an entire machine body even when a plurality of the bodies are connected to obtain a large lifting power.SOLUTION: A flying vehicle includes: a body portion 100; an air flow generation unit 150 that generates an air flow for flying the body portion 100; and a connection mechanism 30 provided on the body portion 100 and capable of connecting the body portions 100. The connection mechanism 30 has: a first connecting portion provided on one body portion 100 to be connected; and a second connecting portion provided on the other body portion 100 to be connected and with which the first connecting portion engages. While the first connecting portion and the second connecting portion are kept engaged with each other, the body portions 100 are vertically connected in a flying state. The air-flow generation unit 150 provided in the upper body portion 100 is connected to the air-flow generation unit 150 provided in the lower body portion 100 such that they do not overlap each other in a vertical direction.SELECTED DRAWING: Figure 1

Description

The present invention relates to an air vehicle.

In recent years, attempts have been made to transport cargo using unmanned aerial vehicles (UAVs) such as drones. However, there may be a limit to the weight of luggage that can be carried by one UAV. Therefore, there is known a collective UAV that connects a plurality of UAVs to increase lift and enables transportation of heavier loads (for example, Patent Document 1).

Japanese Patent No. 6437662

The collective UAV disclosed in Patent Document 1 has a structure in which a plurality of UAVs are connected in a horizontal direction in a flight state. For this reason, it is difficult to obtain a large lift while the center of gravity of the entire aircraft is stabilized, and there is room for improvement in stably transporting a heavy load.

The present invention has been made in view of such a situation, and the center of gravity of the entire aircraft is stable even when a plurality of aircraft are connected in order to obtain a large lift, and as a result, a heavy load is stably transported. The purpose is to provide an airframe that enables.

The flying object of the present invention includes a main body portion, an air flow generating portion for generating an air flow for flying the main body portion, a connecting mechanism provided in the main body portion and capable of connecting the main body portions to each other. The connecting mechanism is provided on a first connecting portion provided on one of the main bodies to be connected and a second connecting portion provided on the other main body to be connected and to which the first connecting portion engages. With a connecting portion, and in a state where the first connecting portion and the second connecting portion are engaged with each other, the main bodies are connected to each other in the vertical direction in a flying state, and the upper main body is connected. The air flow generating portion provided in the portion is connected to the air flow generating portion provided in the lower main body portion so as not to overlap each other in the vertical direction.

According to the present invention, it is possible to provide an airframe in which the center of gravity of the entire airframe is stable even when a plurality of airframes are connected in order to obtain a large lift, and as a result, it is possible to stably carry a heavy load. Can be done.

It is a side view which shows the flight apparatus which connected a plurality of flying objects which concerns on 1st Embodiment of this invention. It is the II direction arrow view of FIG. It is a top view of the flying object which concerns on 1st Embodiment. It is a side view which shows the structure of the connection mechanism which concerns on 1st Embodiment. It is a partial cross-sectional side view which shows the flight apparatus which connected a plurality of flying objects which concerns on 2nd Embodiment of this invention. It is a side sectional view which shows the structure of the flying object which concerns on 2nd Embodiment. It is a bottom view of the flying object which concerns on 2nd Embodiment. It is a top view of the flying object which concerns on 2nd Embodiment. It is a partial cross-sectional side view of a flight apparatus in which a plurality of flying objects according to a modification of the second embodiment are connected. It is a side sectional view which shows the structure of the flying object which concerns on the modification of FIG. It is a bottom view of the flying object which concerns on the reference example which changed the structure of the main body part in 2nd Embodiment.

Hereinafter, embodiments of the present invention will be described with reference to the drawings. The flying object according to the present embodiment is a drone that can fly in an unmanned state without a person on board, and includes a drone capable of autonomous flight and a drone capable of remote control by a person.

(First Embodiment)
FIG. 1 is a side view of a flight device 1 in which a plurality of flight bodies 10 according to the first embodiment are connected. FIG. 2 is a view taken along the line II of FIG. 1 (plan view). The flight device 1 includes a plurality of flying objects 10 and a luggage holding unit 50. The terms related to the direction and position such as up / down, horizontal, and vertical in the following description are defined as the direction in which the flying object 10 and the flight device 1 are in a normal horizontal flight.

As shown in FIGS. 1 and 2, the flying object 10 has a main body portion 100 and a plurality of air flow generating portions 150 for flying the main body portion 100. Further, the flying object 10 has a connecting mechanism 30 described later. The flight device 1 is configured by combining the main bodies 100 of each of the four flying objects 10 having the same configuration so as to overlap each other in the vertical direction. The flight device 1 of the present embodiment includes four flight bodies 10, but the number of the flight bodies 10 is not limited, and is an appropriate number depending on conditions such as the weight of the baggage B held in the baggage holding portion 50. Is selected for.

The main body 100 is located at the center of the flying object 10 when viewed in a plan view. The main body 100 of the present embodiment has a disk-shaped shape. The flying object 10 flies in a posture in which the axial direction passing through the center of the main body 100 is along the vertical direction. In the plurality of flying objects 10, the main body portions 100 are stacked concentrically in the vertical direction, and the state thereof is held separably by the connecting mechanism 30. The main body 100 has a built-in control unit (not shown) that controls the flying object 10.

FIG. 3 is a plan view of the flying object 10. As shown in FIG. 3, the main body 100 is provided with a plurality of arm 140s extending radially in a substantially horizontal direction. In this embodiment, four arm portions 140 are provided. One end of each arm portion 140 is connected to the outer peripheral surface of the main body portion 100, and each arm portion 140 is arranged at equal intervals in the circumferential direction with respect to the main body portion 100. When the flying object 10 is viewed in a plan view, the angles θ formed by the pair of adjacent arm portions 140 are equal to 90 °. Therefore, the four arm portions 140 are arranged in a cross shape as a whole.

The plurality of air flow generating units 150 generate an air flow for flying the flying object 10 including the main body unit 100 and the arm unit 140. Each of the plurality of air flow generating portions 150 is arranged at the tip end portion of the arm portion 140. The air flow generation unit 150 of the present embodiment includes a rotary blade 151 and a drive unit 152 that rotationally drives the rotary blade 151. The drive unit 152 rotates the rotor blade 151 by a built-in forward / reverse rotatable motor. The rotation of the rotary blade 151 generates an air flow flowing in a predetermined direction. In the present embodiment, one air flow generating unit 150 is provided for each arm unit 140. Therefore, the flying object 10 has four air flow generators 150. The number of air flow generating units 150 is not limited to four, and the flying object 10 is provided with an appropriate number of, for example, about 3 to 6.

The connecting mechanism 30 connects the main bodies 100 of the vertically adjacent flying bodies 10 in the vertical direction in a flying state, and the air flow generating part 150 of the upper flying body 10 is the lower flying body 10. It is connected to the air flow generating portion 150 of No. 1 in a state where they do not overlap each other in the vertical direction and are displaced in the horizontal direction. As shown in FIGS. 3 and 4, the connecting mechanism 30 includes a first fitting portion 110, a second fitting portion 120, and a locking mechanism 130.

As shown in FIG. 3, the first fitting portion 110 is provided on the lower surface of the main body portion 100. The first fitting portion 110 has a cross-shaped convex portion 111. The cross-shaped protrusions 111 include linear protrusions 112 and 113 that are orthogonal to each other. The ridges 112 and 113 have the same width and height dimensions and intersect each other at the center of the body 100.

The ridges 112 and 113 of the first fitting portion 110 extend so as to connect an intermediate point between a pair of arm portions 140 adjacent to each other in the circumferential direction. Therefore, the ridges 112 and 113 and the arm portion 140 adjacent to the ridges 112 and 113 in the circumferential direction are positioned so as to form an angle of 45 °. The cross-shaped convex portion 111 is arranged with a phase difference of 45 ° with respect to the four arm portions 140 arranged in a cross shape.

The second fitting portion 120 is provided on the upper surface of the main body portion 100. The second fitting portion 120 has a cross-shaped groove portion 121. The cross-shaped groove portion 121 includes linear grooves 122 and 123 that are orthogonal to each other. The grooves 122 and 123 intersect each other at the center of the main body 100. The grooves 122 and 123 have a width dimension and a height dimension that fit into the protrusions 112 and 113 of the first fitting portion 110.

The grooves 122 and 123 of the second fitting portion 120 extend so as to connect a pair of arm portions 140 facing each other at a position of 180 ° in the circumferential direction angle. Each arm portion 140 is arranged on an extension of the grooves 122 and 123. The cross-shaped groove portion 121 is arranged in phase with the four arm portions 140 arranged in a cross shape.

In the flying object 10, the cross-shaped convex portion 111 of the first fitting portion 110 in the upper main body portion 100 fits into the cross-shaped groove portion 121 of the second fitting portion 120 in the lower main body portion 100. Will be combined. As a result, the upper main body 100 and the lower main body 100 are positioned horizontally and circumferentially with respect to the other side, and are concentrically overlapped with each other. The lock mechanism 130 detachably connects the upper and lower main body portions 100 that overlap each other to each other.

As shown in FIG. 4, the lock mechanism 130 includes a latch 131 provided in the main body 100 and an engaging portion 135. In the lock mechanism 130, the latch 131 of the upper main body 100 is engaged with the engaging portion 135 of the lower main body 100, and the upper and lower main bodies 100 are detachably connected to each other.

The latch 131 has a base end portion 132 and a tip end portion 133. The latch 131 is supported by the lower end portion of the outer peripheral portion of the main body portion 100 so that the base end portion 132 can rotate in the direction of the arrows M1-M2 via the rotation shaft 139. The tip portion 133 of the latch 131 extends downward from the main body portion 100. The latch 131 is always urged by an elastic member (not shown) so as to face the arrow M1 direction (the lower surface direction of the main body 100). As such an elastic member, for example, a torsion coil spring that is wound around a rotating shaft 139 and mounted is applied. The tip portion 133 of the latch 131 is formed with a claw portion 134 that engages with the engaging portion 135.

The engaging portion 135 is formed at the upper end portion of the outer peripheral portion of the main body portion 100. The engaging portion 135 has an inclined surface 136 on which the claw portion 134 of the latch 131 rides on, and a stepped portion 137 below the inclined surface 136.

The latch 131 and the engaging portion 135 have the first fitting portion 110 and the second fitting portion 120 fitted to each other, and the upper and lower main body portions 100 are overlapped with each other, and the latch 131 and the engaging portion 135 can be engaged with each other in the circumferential direction. It is placed in the position of. When the upper and lower main body portions 100 are overlapped in this way, the latch 131 enters the lower side of the step portion 137 after the claw portion 134 rides on the inclined surface 136 of the engaging portion 135, and the claw portion 134 becomes the engaging portion 135. Elastically engage. The latch 131 can be rotated in the direction of the arrow M2 to disengage the claw portion 134 with the engaging portion 135, and the upper and lower main body portions 100 can be separated vertically. To rotate the latch 131 in the M2 direction, for example, the base end 132 of the latch 131 may be pushed toward the inside of the main body 100 (right side in FIG. 4), or the tip 133 may be grasped and pulled outward. It is possible by the operation of.

FIG. 2 illustrates the location of the locking mechanism 130 including the latch 131 and the engaging portion 135. As described above, it is preferable that the lock mechanisms 130 are arranged at a plurality of locations (4 locations in FIG. 2) at equal intervals in the circumferential direction of the main body portion 100.

In a state where the cross-shaped first fitting portion 110 and the second fitting portion 120 are fitted to each other and the upper and lower main body portions 100 are overlapped with each other, the air of the upper flying object 10 is as shown in FIG. The flow generation unit 150 and the air flow generation unit 150 of the lower flying object 10 do not overlap each other in the vertical direction and are displaced in the horizontal direction. In the present embodiment, each air flow generating portion 150 of the lower flying body 10 is arranged at an intermediate point between a pair of adjacent air flow generating portions 150 of the upper flying body 10. That is, the flying objects 10 adjacent to each other in the vertical direction are in a state in which the wake regions of the air flow generating portions 150 in the flying objects 10 do not overlap each other in the vertical direction and are displaced in the horizontal direction.

In the flying object 10, the first fitting portion 110 of the upper main body portion 100 is fitted to the second fitting portion 120 of the lower main body portion 100, and the latch 131 of the upper main body portion 100 is fitted. Is engaged with the engaging portion 135 of the lower main body portion 100, so that the four flying objects 10 are connected in the vertical direction. In the present embodiment, the first fitting portion 110 and the latch 131 form a first connecting portion, and the second fitting portion 120 and the engaging portion 135 form a second connecting portion.

In a state where the four flying objects 10 are overlapped and connected in the vertical direction, the air flow generating part 150 of the first flying object 10 and the third flying object 10 from the top are arranged in the same phase with each other, and these flights With respect to the body 10, the second flying object 10 from the top and the air flow generating portion 150 of the fourth flying object 10 are arranged with a phase difference of 45 °. In FIGS. 1 and 2, the arm portion 140 and the air flow generating portion 150 of the uppermost flying object 10 are referred to as 140A and 150A, respectively, and the arm portion 140 and the air flow generating portion 150 of the second flying object 10 from the top are added. Are added as 140B and 150B, respectively, to indicate a phase difference of 45 °.

As shown in FIG. 1, the luggage holding portion 50 is provided in the main body portion 100 of the flying object 10 arranged at the lowermost portion. The luggage holding portion 50 includes a gate-shaped gripping frame 51 that is detachably attached to the lower surface of the main body portion 100. The luggage holding portion 50 grips the luggage B on the gripping frame 51 and holds the luggage B in a transportable manner. The gripping frame 51 functions as a grounding leg when the luggage B is not gripped.

In the flight device 1, each drive unit 152 of the air flow generation unit 150 is individually controlled by a control device built in the main body unit 100 of each flight body 10, whereby the flight state such as ascent, descent, and turn can be controlled. Be controlled. Each main body 100 further incorporates various sensors such as a camera for detecting the flight state, a gyro sensor for attitude control, an acceleration sensor, and an altitude sensor. Information detected by these sensors is input to the control device built in the main body 100, and based on the information, the control device makes a flight including takeoff and landing of the flight device 1 including the plurality of flying objects 10. State is controlled. When the flight device 1 is remotely controlled, the main body 100 is provided with a communication device or the like for receiving operation information.

According to the flying object 10 of the present embodiment having the above configuration, the following effects are obtained.
The flying object 10 according to the present embodiment is provided in the main body 100, the air flow generating section 150 for generating the air flow for flying the main body 100, and the main body 100, and the main bodies 100 can be connected to each other. The connecting mechanism 30 is provided with a first connecting portion (first fitting portion 110 and latch 131) provided on one of the main body portions 100 to be connected, and the other connecting mechanism 30 is connected to the first connecting portion (first fitting portion 110 and latch 131). It has a second connecting portion (second fitting portion 120 and engaging portion 135) provided on the main body 100 and to which the first connecting portion engages, and has a first connecting portion and a second connecting portion. The main bodies 100 are connected to each other in the vertical direction in a state of being engaged with the connecting portion, and the air flow generating portion 150 provided in the upper main body 100 is provided in the lower main body 100. It is connected to the air flow generating portion 150 to be generated so as not to overlap each other in the vertical direction.

As a result, a large lift can be obtained by connecting a plurality of flying objects 10 and combining them as a flight device 1. Since the plurality of flying objects 10 are connected in the vertical direction, the center of gravity of the entire body is stabilized, and as a result, it is possible to stably carry a heavy load. Further, since the air flow generating section 150 provided in the upper main body 100 does not overlap with the air flow generating section 150 provided in the lower main body 100 in the vertical direction, the plurality of flying objects 10 are vertically arranged. Even though they are arranged in an overlapping manner, the turbulence of the wake of the air flow generating portion 150 is suppressed, and stable flight is possible.

In the flying object 10 according to the present embodiment, in the connecting mechanism 30, the main body portions 100 are connected to each other, the air flow generating portion 15 provided in the upper main body portion 100 is provided, and the air flow generating portion 150 is provided in the lower main body portion 100. It is connected in a state where it is displaced in the horizontal direction.

As a result, it is possible to surely obtain a state in which the air flow generating portion 150 provided in the upper main body 100 does not overlap with each other in the vertical direction with respect to the air flow generating portion 150 provided in the lower main body 100.

In the present embodiment, the flying object 10 arranged at the lowermost part of the flight device 1 includes a cargo holding portion 50 capable of holding the cargo B. As a result, the cargo B can be reliably held and transported.

In the flying object 10 according to the present embodiment, the first connecting portion includes the first fitting portion 110 provided in the main body portion 100, and the second connecting portion is provided in the main body portion 100 and is the first. A second fitting portion 120 that fits into the fitting portion 110 and positions the relative positions of the main body portions 100 connected to each other in the horizontal direction is included. As a result, the air flow generating portions 150 can be easily and smoothly connected in a state where the air flow generating portions 150 do not overlap in the vertical direction and are displaced in the horizontal direction by combining the flying objects 10 adjacent to each other in the vertical direction.

In the flying object 10 according to the present embodiment, the first connecting portion includes the latch 131, and the second connecting portion includes the engaging portion 135 with which the latch 131 is detachably engaged. As a result, the upper and lower main body portions 100 can be reliably and smoothly connected, and the main body portions 100 can be easily separated.

The flying object 10 according to the present embodiment has a plurality (four) arm portions 140 extending horizontally radially from the main body portion 100, and the air flow generating portion 150 is a rotary wing 151 that generates an air flow by rotation. The rotary blade 151 is arranged at the tip end portion of the arm portion 140.

As a result, the air flow generating portions 150 of the flying objects 10 adjacent to each other in the vertical direction can be arranged so as to be separated in the horizontal direction as much as possible so as not to overlap in the vertical direction, and the turbulence of the wake of the air flow generating portion 150 can be arranged. The inhibitory effect can be further enhanced.

In the flying object 10 according to the present embodiment, the arm portions 140 are arranged at equal intervals in the circumferential direction with respect to the main body portion 100, so that the angle θ formed by the pair of adjacent arm portions 140 is 90 °. When the flight device 1 in which the four main body portions 100 are connected in the vertical direction is viewed in a plan view, the angle formed by the pair of arm portions 140 appearing to be adjacent to each other in the circumferential direction is 1 / 2θ, that is, 45 °. Is.

As a result, it is possible to arrange all the airflow generating parts 150 of the airflow generating parts 10 adjacent to each other in the vertical direction in the largest and evenly separated state in the circumferential direction, and the wake of the airflow generating part 150. Disturbance can be effectively suppressed.

(Second Embodiment)
Next, a second embodiment of the present invention will be described with reference to FIGS. 5 to 8. In the following description, components having the same functions as those of the first embodiment are designated by the same reference numerals, and the description thereof may be omitted or simplified to mainly focus on the differences from the first embodiment. explain.

In the flight device 2 shown in FIG. 5, three flying objects 20 according to the second embodiment are stacked and connected in the vertical direction. The flying object 20 according to the second embodiment includes a main body portion 200, a connecting mechanism 70 for connecting the flying objects 20 adjacent to each other in the vertical direction, and four arm portions 140 extending substantially horizontally from the main body portion 200. , An air flow generating portion 150 provided at each tip of the arm portion 140. The four air flow generators 150 of each of the flying objects 20 are arranged at equal intervals in the circumferential direction.

As shown in FIG. 6, in the main body 200 of each flying object 20, a convex portion 210 protruding downward in a conical shape is formed on the lower surface side, and a concave portion 220 having a conical dent downward is formed on the upper surface side. It has a concave (mortar-shaped) vertical cross-sectional shape. In the present embodiment, the convex portion 210 on the lower surface side constitutes the first fitting portion, and the concave portion 220 on the upper surface side constitutes the second fitting portion. In the flying objects 20 arranged vertically, the convex portion 210 of the upper main body portion 200 is fitted into the concave portion 220 of the lower main body portion 200. As a result, the upper main body 200 and the lower main body 200 are positioned horizontally with respect to each other, and are concentrically overlapped with each other.

The connecting mechanism 70 connects the main bodies 200 of the vertically adjacent flying bodies 20 in the vertical direction in a flying state, and the air flow generating part 150 of the upper flying body 20 is the lower flying body 20. It is connected to the air flow generating portion 150 of No. 1 in a state where they do not overlap each other in the vertical direction and are displaced in the horizontal direction. The connecting mechanism 70 has the convex portion 210 and the concave portion 220, and a plurality of locking mechanisms 230.

As shown in FIG. 6, each of the plurality of locking mechanisms 230 includes a hole portion 231 provided in the main body portion 200 and an actuator 235. As shown in FIG. 5, in the lock mechanism 230, the actuator 235 of the lower main body 200 is inserted into the plurality of holes 231 of the upper main body 200, and the upper and lower main bodies 200 are detachably connected to each other. .. In the present embodiment, there are four lock mechanisms 230 including a hole portion 231 and an actuator 235 as a set.

As shown in FIGS. 6 and 7, the four hole portions 231 are blind holes that extend radially in the horizontal direction and open to the lower surface of the main body portion 200 (the lower surface of the convex portion 210). FIG. 7 is a bottom view of the flying object 20. As shown in FIG. 7, each of the four hole portions 231 is formed at an intermediate position between a pair of arm portions 140 adjacent to each other in the circumferential direction. When the flying object 20 is viewed in a plan view, each hole portion 231 and each arm portion 140 are arranged so as to form an angle of 45 °. That is, the four hole portions 231 are arranged with a phase difference of 45 ° with respect to the four arm portions 140 arranged in a cross shape.

The actuator 235 of this embodiment is composed of a solenoid or the like including a plunger 236. As shown in FIGS. 6 and 8, the four plungers 236 extend horizontally radially. The four plungers 236 are provided so as to be able to advance and retreat so as to project into the recess 220 toward the center of the main body 200. Each of the four actuators 235 is accommodated in an actuator accommodating hole 237 formed in the main body 200, and the plunger 236 projects into the recess 220 during operation. As shown in FIG. 8, when the flying object 20 is viewed in a plan view, each actuator 235 is arranged so as to form a straight line with each of the four arm portions 140. That is, the four actuators 235 are arranged in phase with the four arm portions 140 arranged in a cross shape.

As shown in FIGS. 6 and 8, on the upper surface of the main body 200 (inner surface of the recess 220), a plurality of rollers 240 that rotate along a horizontal plane with a rotation axis in the vertical direction are arranged. The roller 240 is, for example, a rubber roller, which is a driven roller rotatably supported by the main body 200. The main body 200 of the present embodiment includes four rollers 240, each of which is arranged at an intermediate point between a pair of actuators 235 adjacent in the circumferential direction. A part of the outer peripheral surface of the roller 240 protrudes into the recess 220, and the lower surface of the upper main body portion 200 is configured to be placed on the protruding outer peripheral surface of the rollers 240. The upper main body 200 is arranged so as to be overlapped with the lower main body 200 via four rollers 240, and the upper and lower main body 200 can be relatively rotated by the driven rotation of the roller 240.

When the upper main body 200 is rotated via the roller 240 in a state where the upper and lower main bodies 200 are overlapped with each other, for example, when the upper main body 200 is rotated, the holes 231 of the upper main body 200 and the actuators 235 of the lower main body 200 are formed. The circumferential positions of the plungers 236 coincide with each other, and the plunger 236 can be freely inserted into the hole 231 at that position. By inserting each plunger 236 into each hole portion 231, the upper and lower main body portions 200 are concentrically connected as shown in FIG.

In this way, the convex portion 210 is fitted into the concave portion 220, the plunger 236 of each actuator 235 is inserted into each hole portion 231 and the main body portion 200 is connected in the vertical direction. In the second embodiment, the convex portion 210 and the plurality of hole portions 231 form the first connecting portion, and the concave portion 220 and the actuator 235 form the second connecting portion.

In the second embodiment, in the three flying objects 20 connected in the vertical direction by the connecting mechanism 70, the four air flow generating portions 150 possessed by each of the uppermost and lowermost flying objects 20 overlap in the vertical direction. .. The four air flow generating parts 150 of the middle flying body 20 sandwiched between the uppermost flying body 20 and the lowermost flying body 20 are circumferentially oriented with respect to the air flow generating parts 150 of the upper and lower flying bodies 20. They are arranged out of alignment with a phase difference of 45 °. That is, due to the connecting mechanism 70, the wake regions of the airflow generating portions 150 in the vertically adjacent flying bodies 20 do not overlap each other in the vertical direction and are displaced in the horizontal direction.

According to the flight body 20 according to the second embodiment, a large lift can be obtained by connecting a plurality of flight bodies 20 and combining them as the flight device 2. Since the plurality of flying objects 20 are connected in the vertical direction, the center of gravity of the entire airframe is stabilized, and as a result, it is possible to stably carry a heavy load. Further, since the air flow generating portion 150 provided in the upper main body portion 200 does not overlap with each other in the vertical direction and is displaced in the horizontal direction with respect to the air flow generating portion 150 provided in the lower main body portion 200, there are a plurality of portions. Even though the flying objects 20 are arranged so as to be stacked in the vertical direction, the turbulence of the wake of the air flow generating portion 150 is suppressed, and the flight can be stably performed.

In the flying object 20 according to the second embodiment, the main body portion 200 has a substantially concave vertical cross-sectional shape in which a convex portion 210 protruding downward is formed on the lower surface side and a concave portion 220 is formed downward on the upper surface side. The convex portion 210 is used as the first fitting portion, and the concave portion 220 is used as the second fitting portion.

By stacking the main body 200 in a concave shape (mortar shape) in this way, the spread in the radial direction is suppressed, the center of gravity can be positioned more in the center, and more stable flight is possible. It becomes. Further, the main body portion 200 can be arranged concentrically in the vertical direction by a simple operation of fitting the lower convex portion 210 into the upper concave portion 220.

In the flying object 20 according to the second embodiment, the first connecting portion includes a plurality of hole portions 231 and the second connecting portion is a plurality of freely inserted into each of the plurality of hole portions 231. Includes actuator 235. As a result, the upper and lower main body portions 200 can be reliably and smoothly connected, and the main body portions 200 can be easily separated.

(Modification example)
9 and 10 show a modification of the second embodiment. In this modification, the roller 242 is used instead of the roller 240. The roller 242 adopted in this modification is arranged on the lower surface of the main body 200 on the convex portion 210 side so as to rotate along the vertical plane with the horizontal direction as the rotation axis. As for the roller 240, for example, four rollers 240 are provided like the roller 240, and the rollers 240 are arranged at equal intervals in the circumferential direction. In this modification, the upper main body 200 is arranged so as to be overlapped with the lower main body 200 via each roller 242, and the upper and lower main body 200 can be relatively rotated by the driven rotation of the roller 242.

(Reference example)
FIG. 11 shows a reference example in which the peripheral groove 250 is formed in place of the hole 231 into which the plunger 236 of the actuator 235 is inserted in the second embodiment. In this reference example, the plunger 236 is inserted into the peripheral groove 250 formed on the lower surface of the convex portion 210 of the main body portion 200. The peripheral groove 250 is formed in an annular shape over the entire circumference of the main body portion 200. By changing to the peripheral groove 250 as the hole into which the plunger 236 is inserted, the plunger 236 of the actuator 235 can be inserted at an arbitrary position in the circumferential direction. As a result, the circumferential position of the air flow generation unit 150 can be arranged at an arbitrary position, and the degree of freedom in the arrangement of the air flow generation unit 150 can be obtained.

Although the embodiments of the present invention have been described above, the present invention is not limited to the above-described embodiments, and modifications, improvements, and the like to the extent that the object of the present invention can be achieved are included in the present invention. ..

For example, the arm portion 140 may be configured to have a variable length. Thereby, in addition to shifting the air flow generating section 150 in the circumferential direction, the structure for preventing the air flow generating section 150 from overlapping in the vertical direction can be obtained by extending the arm section 140 and shifting it outward in the radial direction. can.

As described above, the number of arm portions 140 in which the air flow generating portion 150 is provided at the tip portion is not limited to four, and may be provided with about 3 to 6. For example, when three arm portions 140 are arranged at equal intervals in the circumferential direction and a plurality of main body portions 100 (or 200) are stacked and connected in the vertical direction, they appear to be adjacent to each other in a plan view. The angle formed by the pair of arm portions 140 can be evenly set to 60 °.

10, 20 Flying object 30, 70 Coupling mechanism 50 Luggage holding part 100, 200 Main body part 110 First fitting part (first connecting part)
120 Second fitting part (second connecting part)
131 Latch (first connection)
135 Engaging part (second connecting part)
140 Arm part 150 Air flow generation part 151 Rotor blade 210 Convex part (first fitting part, first connecting part)
220 recess (second fitting part, second connecting part)
231 hole (first connecting part)
235 Actuator (second connecting part)
B luggage

Claims (10)

With the main body
An air flow generating part that generates an air flow for flying the main body, and an air flow generating part.
It is provided with a connecting mechanism provided on the main body and enables the main bodies to be connected to each other.
The connecting mechanism includes a first connecting portion provided on one of the main bodies to be connected and a second connecting portion provided on the other main body to be connected and to which the first connecting portion engages. In a state where the first connecting portion and the second connecting portion are engaged with each other, the main body portions are connected in the vertical direction in a flying state and are provided on the upper main body portion. A flying object in which the air flow generating portion is connected to the air flow generating portion provided in the lower main body portion so as not to overlap each other in the vertical direction. The connecting mechanism connects the main bodies in a state in which the air flow generating portion provided on the upper main body is horizontally displaced from the air flow generating portion provided on the lower main body. The air vehicle according to claim 1. The flying object according to claim 1 or 2, further comprising a luggage holding unit capable of holding luggage. The first connecting portion includes a first fitting portion provided on the main body portion.
The second connecting portion is provided in the main body portion, and is fitted to the first fitting portion to position the relative positions of the main bodies to be connected in the horizontal direction. The flying object according to any one of claims 1 to 3. The main body portion has a substantially concave vertical cross-sectional shape in which a convex portion protruding downward is formed on the lower surface side and a concave portion is formed downward on the upper surface side, and the convex portion is the first fitting. The flying object according to claim 4, wherein the recess on the upper surface side is a portion, and the recess is the second fitting portion. The first connecting portion includes a latch and includes a latch.
The flying object according to any one of claims 1 to 5, wherein the second connecting portion includes an engaging portion with which the latch is detachably engaged. The first connecting portion includes a hole portion and includes a hole portion.
The flying object according to any one of claims 1 to 5, wherein the second connecting portion includes an actuator that is freely inserted into the hole portion. Further having a plurality of arm portions extending substantially horizontally from the main body portion,
The air flow generator includes a rotary blade that generates an air flow by rotation.
The flying object according to any one of claims 1 to 7, wherein the rotor blade is arranged at the tip end portion of the arm portion. By arranging the arm portions at equal intervals in the circumferential direction with respect to the main body portion, the angles θ formed by the pair of adjacent arm portions are equal.
The flying object according to claim 8, wherein the angle formed by the pair of arm portions that appear to be adjacent to each other is 1 / 2θ when the main body portions connected in the vertical direction are viewed in a plan view. The flying object according to claim 8 or 9, wherein the arm portion is configured to have a variable length.

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