Patent Description:
<CIT> discloses a vertical take-off and landing aircraft that generates thrust in a vertical direction with a plurality of rotors. Vertical take-off and landing aircraft are commonly referred to as VTOL aircraft. The VTOL aircraft of <CIT> includes two rotors on each of the left and right sides of the fuselage. A first rotor of the two rotors is attached to a first support member extending forward of the front wing. A second rotor of the two rotors is attached to a second support member extending from the front wing to the rear wing. Furthermore, it is referred to <CIT>.

Preferably, the rotor support structure is easy to assemble and disassemble, and easy to maintain.

An object of the present invention is to solve the above-mentioned problem.

According to an aspect of the first invention, there is provided a rotor support device that is suitable to be provided in an aircraft and to support a rotor configured to generate thrust in a vertical direction, the rotor support device comprising: a mount configured to support the rotor and including a joint portion protruding outward; a connecting member extending in a protruding direction of the joint portion and detachably connected to the joint portion; and a reinforcing member detachably connected to the joint portion and the connecting member in order to reinforce connection between the joint portion and the connecting member, wherein the connecting member includes an end portion connected to the joint portion, and the end portion includes a notch and a protruding portion that is formed by forming the notch, the protruding portion is overlapped with a part of an outer peripheral surface of the joint portion, the part being located on a side of a first direction perpendicular to the protruding direction of the joint portion, and is detachably connected to the joint portion, and the reinforcing member is overlapped with the connecting member and another part of the outer peripheral surface of the joint portion, the another part being located on a side of a second direction opposite to the first direction, and is detachably connected to the joint portion and the connecting member.

According to the present invention, the rotor support structure is easy to assemble and disassemble, and easy to maintain.

<FIG> is an external view of a VTOL aircraft <NUM>. The VTOL aircraft <NUM> is, for example, an electric vertical take-off and landing aircraft, a so-called eVTOL aircraft. The VTOL aircraft <NUM> includes a fuselage <NUM>, a front wing <NUM>, a rear wing <NUM>, two booms <NUM>, eight VTOL rotors <NUM>, and two cruise rotors <NUM>.

The front wing <NUM> is connected to a front portion of the fuselage <NUM>. The front wing <NUM> includes a left wing <NUM> and a right wing 14R. The rear wing <NUM> is connected to a rear portion of the fuselage <NUM>. The rear wing <NUM> includes a left wing <NUM> and a right wing 16R. The front wing <NUM> and the rear wing <NUM> generate lift as the VTOL aircraft <NUM> moves forward.

Each of the two booms <NUM> is a rotor support device that supports four VTOL rotors <NUM>. A boom 18R of the two booms <NUM> is disposed on the right side of the fuselage <NUM>. A boom <NUM> of the two booms <NUM> is disposed on the left side of the fuselage <NUM>. Each boom <NUM> extends in the front-rear direction.

Four VTOL rotors <NUM> are arranged on the boom <NUM> sequentially toward the rear. Similarly, four VTOL rotors <NUM> are arranged on the boom 18R sequentially toward the rear. Each VTOL rotor <NUM> generates thrust in the vertical direction.

Two cruise rotors <NUM> are disposed on the rear wing <NUM> so as to be arranged side by side in the left-right direction. Each cruise rotor <NUM> generates thrust in the horizontal direction.

<FIG> is a left side view of the boom <NUM>. <FIG> is a top view of the boom <NUM>. Note that <FIG> referred to in the above description shows the boom <NUM> with a fairing attached. On the other hand, <FIG> and <FIG> show the boom <NUM> with the fairing removed. <FIG> and <FIG> also show the boom <NUM> with four VTOL rotors <NUM> attached. The structure of the boom 18R is identical to that of the boom <NUM> except that the left and right sides are reversed. Therefore, in this specification, the boom <NUM> will be described, and the description of the boom 18R will be omitted.

The boom <NUM> includes four mounts <NUM> and three connecting pipes <NUM> (connecting members). The four mounts <NUM> include a front mount 24a, a first mount 24b, a second mount 24c, and a rear mount 24d. The three connecting pipes <NUM> include a front pipe 26a, an intermediate pipe 26b, and a rear pipe 26c. The front mount 24a, the front pipe 26a, the first mount 24b, the intermediate pipe 26b, the second mount 24c, the rear pipe 26c, and the rear mount 24d are connected in this order toward the rear.

As shown in <FIG>, when viewed from above, the front pipe 26a extends in a direction rotated clockwise by a predetermined angle with respect to the front-rear direction. The front pipe 26a is connected to the front mount 24a and the first mount 24b. The front end portion of the front pipe 26a and the front mount 24a are permanently connected. The rear end portion of the front pipe 26a and the first mount 24b are permanently connected. Further, the left wing <NUM> of the front wing <NUM> is connected to the front pipe 26a (see <FIG>).

The intermediate pipe 26b extends in the front-rear direction. The intermediate pipe 26b is connected to the first mount 24b and the second mount 24c. The front end portion of the intermediate pipe 26b and the first mount 24b are detachably connected to each other. The rear end portion of the intermediate pipe 26b and the second mount 24c are detachably connected to each other. The structure of connection between the mount <NUM> (the first mount 24b and the second mount 24c) and the intermediate pipe 26b will be described later.

As shown in <FIG>, when viewed from above, the rear pipe 26c extends in a direction rotated counterclockwise by a predetermined angle with respect to the front-rear direction. The rear pipe 26c is connected to the second mount 24c and the rear mount 24d. The front end portion of the rear pipe 26c and the second mount 24c are permanently connected. The rear end portion of the rear pipe 26c and the rear mount 24d are permanently connected. Further, the left wing <NUM> of the rear wing <NUM> is connected to the rear pipe 26c (see <FIG>).

As described above, the four mounts <NUM> and the three connecting pipes <NUM> are alternately connected from the front to the rear. Further, the front pipe 26a is supported by the left wing <NUM> of the front wing <NUM>, and the rear pipe 26c is supported by the left wing <NUM> of the rear wing <NUM>. As a result, the boom <NUM> is fixed in the left direction of the fuselage <NUM>.

<FIG> is an enlarged view of the first mount 24b, the VTOL rotor <NUM>, and the peripheral structure thereof shown in <FIG>. The first mount 24b supports the VTOL rotor <NUM>. The VTOL rotor <NUM> includes a motor <NUM>, a heat sink <NUM>, a gear box <NUM>, a shaft <NUM>, a propeller <NUM>, a variable pitch mechanism <NUM>, a first actuator 44a, and a second actuator 44b. The heat sink <NUM> is attached to the outer periphery of the motor <NUM>. The gear box <NUM> is attached to the upper end portion of the motor <NUM>. The shaft <NUM> extends upward from the gear box <NUM>. The propeller <NUM> is attached to the upper end portion of the shaft <NUM>.

The variable pitch mechanism <NUM> adjusts the pitch of blades <NUM> of the propeller <NUM>. The variable pitch mechanism <NUM> includes a moving member <NUM>. The moving member <NUM> is movable up and down along the shaft <NUM>. The moving member <NUM> is connected to a link mechanism (not shown). The link mechanism changes the pitch of each blade <NUM> according to the movement of the moving member <NUM>. As shown in <FIG>, the moving member <NUM> extends in the extension direction of the boom <NUM> with the shaft <NUM> as the center. The first actuator 44a is connected to the front end portion of the moving member <NUM>. The second actuator 44b is connected to the rear end portion of the moving member <NUM>.

An accommodation hole <NUM>, a first void <NUM>, and a second void <NUM> are formed in the first mount 24b. Further, a front joint portion <NUM> is formed at the front end portion of the first mount 24b, and a rear joint portion <NUM> is formed at the rear end portion of the first mount 24b. Each of the accommodation hole <NUM>, the first void <NUM>, and the second void <NUM> penetrates in the up-down direction.

The accommodation hole <NUM> is located substantially at the center of the first mount 24b in the front-rear direction. The VTOL rotor <NUM> is accommodated in the accommodation hole <NUM>. The first void <NUM> is located between the accommodation hole <NUM> and the front joint portion <NUM>. A first actuator supporting portion 48a for supporting the first actuator 44a is formed in the first void <NUM>. The second void <NUM> is located between the accommodation hole <NUM> and the rear joint portion <NUM>. A second actuator supporting portion 48b for supporting the second actuator 44b is formed in the second void <NUM>.

The front joint portion <NUM> protrudes toward the front pipe 26a located on the front side. The front joint portion <NUM> extends in a direction rotated clockwise by a predetermined angle with respect to the front-rear direction. The front joint portion <NUM> is inserted into the rear end portion of the front pipe 26a. The front joint portion <NUM> and the rear end portion of the front pipe 26a are permanently connected.

The rear joint portion <NUM> protrudes toward the intermediate pipe 26b located on the rear side. The rear joint portion <NUM> extends in the front-rear direction. The rear joint portion <NUM> is connected to the front end portion of the intermediate pipe 26b and a reinforcing member <NUM>. The upper portion of the rear joint portion <NUM> has a rounded shape (for example, an elliptical shape) when viewed from the rear. The lower portion of the rear joint portion <NUM> has a rectangular shape with rounded corners when viewed from the rear.

<FIG> is an exploded perspective view of a connection portion between the first mount 24b and the intermediate pipe 26b. The cross-sectional shape of the intermediate pipe 26b is the same as the cross-sectional shape of the rear joint portion <NUM>. That is, the upper portion of the intermediate pipe 26b has a rounded shape (for example, an elliptical shape) when viewed from the front. The lower portion of the intermediate pipe 26b has a rectangular shape with rounded corners when viewed from the front. A notch <NUM> is formed in the lower portion of the front end portion of the intermediate pipe 26b. As a result, a protruding portion <NUM> is formed at the upper portion of the front end portion of the intermediate pipe 26b.

The protruding portion <NUM> protrudes toward the rear joint portion <NUM> of the first mount 24b. That is, the protruding portion <NUM> protrudes forward. The inner peripheral shape of the protruding portion <NUM> is the same as the outer peripheral shape of the upper portion of the rear joint portion <NUM>. The maximum width (the width in the left-right direction) of the protruding portion <NUM> is equal to or less than the width (the width in the left-right direction) of the notch <NUM>. The length (the length in the front-rear direction) of the protruding portion <NUM> is equal to or less than the length (the length in the protruding direction) of the rear joint portion <NUM>.

As indicated by an arrow A in <FIG>, the protruding portion <NUM> of the intermediate pipe 26b is overlapped with the rear joint portion <NUM> from above (a first direction). As a result, the protruding portion <NUM> comes into contact with the upper part of the outer peripheral surface of the rear joint portion <NUM>. The protruding portion <NUM> and the rear joint portion <NUM> are fastened to each other by a plurality of fastening members such as bolts. In this manner, the protruding portion <NUM> is detachably connected to the rear joint portion <NUM>. In a state in which the protruding portion <NUM> is connected to the rear joint portion <NUM>, the lower portion of the rear joint portion <NUM> is disposed in the notch <NUM>.

The reinforcing member <NUM> is a bent plate member. The cross-sectional shape of the reinforcing member <NUM> is the same as the cross-sectional shape of the lower portion of the rear joint portion <NUM> and the cross-sectional shape of the lower portion of the intermediate pipe 26b. However, the reinforcing member <NUM> is slightly larger than the lower portion of the rear joint portion <NUM> and the lower portion of the intermediate pipe 26b. In other words, the width (the width in the left-right direction) of the reinforcing member <NUM> is slightly larger than the width (the width in the left-right direction) of the rear joint portion <NUM> and the width (the width in the left-right direction) of the intermediate pipe 26b. The length (the length in the front-rear direction) of the reinforcing member <NUM> is, for example, about twice the length (the length in the protruding direction) of the protruding portion <NUM>. However, the length of the reinforcing member <NUM> is not limited to this length. The reinforcing member <NUM> may have any length as long as it overlaps the lower portion of the intermediate pipe 26b and the lower portion of the rear joint portion <NUM> located in the notch <NUM> in a state where the rear joint portion <NUM> and the protruding portion <NUM> of the intermediate pipe 26b are fastened to each other.

As indicated by an arrow B in <FIG>, the reinforcing member <NUM> is overlapped with the rear joint portion <NUM> and the intermediate pipe 26b from below (a second direction). As a result, the reinforcing member <NUM> comes into contact with the lower part of the outer peripheral surface of the rear joint portion <NUM> and the lower part of the outer peripheral surface of the intermediate pipe 26b. The reinforcing member <NUM> and the rear joint portion <NUM> are fastened to each other by a plurality of fastening members such as bolts. Further, the reinforcing member <NUM> and the intermediate pipe 26b are fastened to each other by a plurality of fastening members such as bolts. In this manner, the reinforcing member <NUM> is detachably connected to the rear joint portion <NUM> and the intermediate pipe 26b.

As described above, the front end portion of the intermediate pipe 26b and the rear joint portion <NUM> of the first mount 24b are connected to each other. The structure of the rear end portion of the intermediate pipe 26b is identical to the structure of the front end portion of the intermediate pipe 26b except that the front and rear sides are reversed. In addition, the structure of the second mount 24c is identical to the structure of the first mount 24b except that the front and rear sides are reversed. Accordingly, the rear end portion of the intermediate pipe 26b and the front joint portion (not shown) of the second mount 24c are connected in the same manner as the front end portion of the intermediate pipe 26b and the rear joint portion <NUM> of the first mount 24b.

The assembly process of the boom <NUM> is performed, for example, in the following procedure. First, the front pipe 26a to which the front mount 24a and the first mount 24b are connected is connected to the front wing <NUM>. Further, the rear pipe 26c to which the second mount 24c and the rear mount 24d are connected is connected to the rear wing <NUM>. In this manner, the front pipe 26a and the rear pipe 26c are connected to the fuselage in advance. Therefore, each of the first mount 24b and the second mount 24c is positioned.

In this state, the protruding portion <NUM> of the front end portion of the intermediate pipe 26b is overlapped with the rear joint portion <NUM> of the first mount 24b from above. The intermediate pipe 26b and the first mount 24b are fastened to each other by a plurality of fastening members. Next, the reinforcing member <NUM> is overlapped with the rear joint portion <NUM> of the first mount 24b and the intermediate pipe 26b from below. The reinforcing member <NUM> and the first mount 24b are fastened to each other by a plurality of fastening members. Further, the reinforcing member <NUM> and the intermediate pipe 26b are fastened to each other by a plurality of fastening members. Thus, the intermediate pipe 26b is connected to the first mount 24b. Similarly, the intermediate pipe 26b is also connected to the second mount 24c. As a result, the basic part of the boom <NUM> is completed.

In the maintenance of the boom <NUM>, the boom <NUM> is disassembled. The process of disassembling the boom <NUM> is performed in the reverse order of the process of assembling the boom <NUM>.

The protruding portion <NUM> of the intermediate pipe 26b may be overlapped with the rear joint portion <NUM> from a direction other than above (for example, from the left direction). Accordingly, the reinforcing member <NUM> may be overlapped with the rear joint portion <NUM> and the intermediate pipe 26b from a direction other than below (for example, from the right direction). However, for the following reason, it is preferable that the protruding portion <NUM> of the intermediate pipe 26b is overlapped with the rear joint portion <NUM> from above. That is, in the attaching and detaching process of the reinforcing member <NUM>, the intermediate pipe 26b is supported by the first mount 24b and the second mount 24c. Therefore, according to the above-described configuration, a device for supporting the intermediate pipe 26b is not required in the attaching and detaching process of the reinforcing member <NUM>.

The number of the mounts <NUM> may not be four. Further, the number of the connecting pipes <NUM> may not be three. For example, the number of the mounts <NUM> may be five, and the number of the connecting pipes <NUM> may be four. Further, the shape of the boom <NUM> may not be a shape extending from the front end portion to the rear end portion. For example, the shape of the boom <NUM> may be annular. In any embodiment, the connecting pipe <NUM> that is not fixed to the fuselage may be attachable to and detachable from the mount <NUM>.

In order to connect the first mount 24b and the second mount 24c with an ordinary pipe, it is necessary to push open the first mount 24b and the second mount 24c to insert the pipe therein. However, the first mount 24b and the second mount 24c are fixed to the fuselage. For this reason, it is not possible to push open the first mount 24b and the second mount 24c.

In the present embodiment, the intermediate pipe 26b is overlapped with the first mount 24b from above, and the reinforcing member <NUM> is overlapped with the first mount 24b and the intermediate pipe 26b from below, whereby the intermediate pipe 26b and the first mount 24b are connected to each other. The intermediate pipe 26b and the second mount 24c are connected to each other in the same manner. Further, the intermediate pipe 26b is attachable to and detachable from the first mount 24b and the second mount 24c. One reinforcing member <NUM> is attachable to and detachable from the first mount 24b and the intermediate pipe 26b. Another reinforcing member <NUM> is attachable to and detachable from the second mount 24c and the intermediate pipe 26b. In the present embodiment, it is not necessary to push open the first mount 24b and the second mount 24c. Therefore, according to the present embodiment, the rotor support structure is easy to assemble and disassemble, and easy to maintain.

Note that there is a model in which the first mount 24b and the second mount 24c can be pushed open. In the case of such a model, the first mount 24b and the intermediate pipe 26b may be connected to each other in the following procedure, for example.

The intermediate pipe 26b is disposed in a direction in which the rear joint portion <NUM> of the first mount 24b extends when viewed from above. Further, the intermediate pipe 26b is disposed such that the notch <NUM> of the front end portion thereof and the upper portion of the first mount 24b overlap each other when viewed from the left side. From this state, the intermediate pipe 26b is moved toward the first mount 24b. Then, the notch <NUM> of the front end portion of the intermediate pipe 26b comes into contact with the upper portion of the first mount 24b. The intermediate pipe 26b is then moved downward. As a result, the protruding portion <NUM> of the front end portion of the intermediate pipe 26b is overlapped with the rear joint portion <NUM> of the first mount 24b from above. The subsequent procedure is the same as that described above. By the above-described procedure, the positioning of the intermediate pipe 26b with respect to the first mount 24b is facilitated.

The inventions that can be grasped from the above embodiments will be described below.

According to an aspect of the first invention, provided is the rotor support device (<NUM>, <NUM>, 18R) that is provided in the aircraft (<NUM>) and supports the rotor (<NUM>) configured to generate thrust in the vertical direction, the rotor support device including: the mount (<NUM>, 24b, 24c) configured to support the rotor and including the joint portion (<NUM>, <NUM>) protruding outward; the connecting member (<NUM>, 26b) extending in the protruding direction of the joint portion and detachably connected to the joint portion; and the reinforcing member (<NUM>) detachably connected to the joint portion and the connecting member in order to reinforce the connection between the joint portion and the connecting member, wherein the connecting member includes the end portion connected to the joint portion, and the end portion includes the notch (<NUM>) and the protruding portion (<NUM>) that is formed by forming the notch, the protruding portion is overlapped with a part of the outer peripheral surface of the joint portion, the part being located on the side of the first direction perpendicular to the protruding direction of the joint portion, and is detachably connected to the joint portion, and the reinforcing member is overlapped with the connecting member and another part of the outer peripheral surface of the joint portion, the another part being located on the side of the second direction opposite to the first direction, and is detachably connected to the joint portion and the connecting member.

According to the above configuration, the rotor support structure is easy to assemble and disassemble, and easy to maintain.

In the above aspect, the protruding portion may be overlapped with an upper part of the outer peripheral surface of the joint portion and detachably connected to the joint portion, and the reinforcing member may be overlapped with the connecting member and a lower part of the outer peripheral surface of the joint portion and detachably connected to the joint portion and the connecting member.

According to the above configuration, a device for supporting the connecting member is not required in the attaching and detaching process of the reinforcing member.

In the above aspect, the connecting member may be a pipe.

In the above aspect, the rotor support device may further include the first mount (24b) and the second mount (24c) as the mount, and the first reinforcing member and the second reinforcing member as the reinforcing member, the first mount may support the first rotor as the rotor, the second mount may support the second rotor as the rotor, the notch and the protruding portion may be formed at each of the first end portion and the second end portion of the connecting member, the first end portion of the connecting member and the first reinforcing member may be fastened to the joint portion of the first mount, and the second end portion of the connecting member and the second reinforcing member may be fastened to the joint portion of the second mount.

In the above aspect, the rotor support device may further include the second connecting member (26a, 26c) permanently coupled to the mount and connected to the wing (<NUM>, <NUM>) of the aircraft.

In the above aspect, the rotor support device may further include the fixed mount (24a, 24d) configured to support a rotor different from the rotor and permanently coupled to the second connecting member.

In the above aspect, the mount may include the void (<NUM>, <NUM>) penetrating in the up-down direction.

In the above aspect, the rotor support device may further include the actuator (44a, 44b) configured to change the pitch of each blade (<NUM>) of the rotor, and the actuator supporting portion (48a, 48b) configured to support the actuator and disposed inside the void.

Provided is the rotor support device (<NUM>, <NUM>, 18R) that is provided in the aircraft (<NUM>) and supports the rotor (<NUM>) configured to generate thrust in the vertical direction, the rotor support device including: the mount (<NUM>, 24b, 24c) configured to support the rotor and including the joint portion (<NUM>, <NUM>) protruding outward; the connecting member (<NUM>, 26b) extending in the protruding direction of the joint portion and detachably connected to the joint portion; and the reinforcing member (<NUM>) detachably connected to the joint portion and the connecting member in order to reinforce the connection between the joint portion and the connecting member, wherein the connecting member includes the end portion connected to the joint portion, and the end portion includes the notch (<NUM>) and the protruding portion (<NUM>) that is formed by forming the notch, the protruding portion is overlapped with the joint portion from the first direction perpendicular to the protruding direction of the joint portion, and is detachably connected to the joint portion, and the reinforcing member is overlapped with the joint portion and the connecting member from the second direction that is opposite to the first direction, and is detachably connected to the joint portion and the connecting member.

Claim 1:
A rotor support device (<NUM>) that is suitable to be provided in an aircraft (<NUM>) and to support a rotor (<NUM>) configured to generate thrust in a vertical direction, the rotor support device (<NUM>) comprising:
a mount (<NUM>) configured to support the rotor and including a joint portion (<NUM>, <NUM>) protruding outward;
a connecting member (<NUM>) extending in a protruding direction of the joint portion and detachably connected to the joint portion; and
a reinforcing member (<NUM>) detachably connected to the joint portion and the connecting member (<NUM>) in order to reinforce connection between the joint portion and the connecting member (<NUM>),
wherein the connecting member (<NUM>) includes an end portion connected to the joint portion, characterised in that the end portion includes a notch (<NUM>) and a protruding portion (<NUM>) that is formed by forming the notch (<NUM>),
the protruding portion (<NUM>) is overlapped with a part of an outer peripheral surface of the joint portion, the part being located on a side of a first direction perpendicular to the protruding direction of the joint portion, and is detachably connected to the joint portion, and
the reinforcing member is overlapped with the connecting member (<NUM>) and another part of the outer peripheral surface of the joint portion, the another part being located on a side of a second direction opposite to the first direction, and is detachably connected to the joint portion and the connecting member (<NUM>).