Abstract: A rotor support device includes: a mount supporting a rotor and including a joint portion protruding outward; a connecting member; and a reinforcing member. The connecting member includes an end portion connected to the joint portion and including a notch and a protruding portion formed by forming the notch. The protruding portion is overlapped with a part of the outer peripheral surface of the joint portion located on the side of a first direction perpendicular to the protruding direction of the joint portion, and is detachably connected to the joint portion. The reinforcing member is overlapped with the connecting member and another part of the outer peripheral surface of the joint portion located on the side of a second direction opposite to the first direction, and is detachably connected to the joint portion and the connecting member.

Abstract: A thrust generating device includes a propeller unit including a propeller and a duct covering the periphery of the propeller. The duct includes a cylinder disposed around the propeller, a hub disposed inside the cylinder, and a plurality of duct stators extending radially from the hub to the cylinder. The hub and each of the duct stators are disposed rearward of the propeller.

Abstract: Four or more rotors installed on an aircraft include: a pair of first rotors that are left/right symmetrically arranged in front of a front wing about a position overlapping the central axis of a fuselage in plan view; and a pair of second rotors that are left/right symmetrically arranged between the front wing and a rear wing about a position overlapping the central axis of the fuselage in a plan view. The distance between the fuselage and the second rotors in the width direction is longer than the distance between the fuselage and the first rotors in the width direction.

Abstract: In a front view of this aircraft, there is an over-lap portion where at least a part of a fuselage and at least a part of two cruising rotors overlap, and a rear portion of the fuselage has an inclined surface which is displaced downward from upward progressing from the front to the rear, such that the area of the overlap portion gradually becomes smaller progressing from the front to the rear.

Abstract: Disclosed herein, inter alia, are compositions and methods for efficient transfer and analyses of cellular material, tissue samples, such as tissue sections, using carrier substrates.

Abstract: Provided is a multicopter providing a high level of freedom in compact design, and consuming a relatively small amount of energy. The multicopter (10) includes a machine body (12), an N number of first lift generators (30) arranged on a first concentric circle (C1) centered substantially around a gravitational center (G) of the machine body (12) and in a front part and a rear part of the machine body in a bilateral symmetry, and an M number of second lift generators (70) arranged on a second concentric circle (C2) centered substantially around the gravitational center (G) of the machine body (12) and having a larger diameter than the first concentric circle (C1), and in a front part and a rear part of the machine body (12) on a central axial line (X) extending in a fore and aft direction of the machine body (12), N being greater than M.

Abstract: An aircraft includes a fuselage, a wing disposed above the fuselage, a pylon connecting the wing to the fuselage, and a plurality of internal combustion engines housed in the fuselage. The pylon vertically traverses the fuselage and is fixed to an upper portion and a lower portion of the fuselage. Among the plurality of internal combustion engines, a first internal combustion engine and a second internal combustion engine are disposed bilaterally symmetrically about the pylon and are fixed to the pylon.

Abstract: A ducted fan device provides enhanced containment capability resulting from a Fan Blade Out (FBO) event. The fan device includes an annular fan shroud (52) and an electric motor disposed at the center driving at least one fan blade (58, 64). The fan shroud (52) has a multilayer structure including a fiber layer (74) and a resin layer (70, 72). The shroud has an opposing section (A) that opposes a tip of at least one of the fan blades (58, 64) and a non-opposing section (B) that does not oppose the tips of the fan blades (58, 64). The opposing and non-opposing sections are arranged in the axial direction. In the non-opposing section (B), the fiber layer (74) is impregnated with part of resin forming the resin layer (70, 72). In the opposing section (A), the fiber layer (74) is not impregnated with the resin forming the resin layer (70, 72).

Abstract: Disclosed herein, inter alia, are phase protective reagent flow orders and methods useful for improving sequencing efficiency.

Abstract: Disclosed herein, inter alia, are compositions and methods for efficient transfer and analyses of cellular material, tissue samples, such as tissue sections, using carrier substrates.

Abstract: An aircraft includes a fuselage, a wing disposed above the fuselage, a pylon connecting the wing to the fuselage, and a plurality of internal combustion engines housed in the fuselage. The pylon vertically traverses the fuselage and is fixed to an upper portion and a lower portion of the fuselage. Among the plurality of internal combustion engines, a first internal combustion engine and a second internal combustion engine are disposed bilaterally symmetrically about the pylon and are fixed to the pylon.

Abstract: A storage system for a flying object is equipped with a landing portion having a landing surface on which the flying object can land, and a storage main body for storing the flying object that has landed on the landing surface. The storage main body includes opening and closing portions that cover the landing surface. The storage system is further equipped with retaining mechanisms adapted to retain the flying object in a state of having landed on the landing surface from a direction perpendicular to the landing surface.

Abstract: To enhance the containment capability of a ducted fan device at the time of FBO without hindering the weight reduction thereof, in a ducted fan device including a fan shroud (52) having an annular shape in plan view and an electric fan disposed at a center of the fan shroud (52) and having a fan blade (58, 64), the fan shroud (52) has a multilayer structure including a fiber layer (74) and a resin layer (70, 72), and has an opposing section (A) including a part that opposes a tip of the fan blade (58, 64) and a non-opposing section (B) that does not oppose the tips of the fan blade (58, 64), the opposing section and the non-opposing section being arranged in an axial direction, wherein in the non-opposing section (B), the fiber layer (74) is impregnated with part of resin forming the resin layer (70, 72), and in the opposing section (A), the fiber layer (74) is not impregnated with the resin forming the resin layer (70, 72).

Abstract: The swing arm for the saddle riding vehicle that supports a wheel in a swingable manner includes a swing arm main body made of a fiber reinforced resin. The swing arm main body is formed to be hollow, and an embedded member of a material different from the fiber reinforced resin is embedded in such a manner as to make solid at least part of the hollow portion of the swing arm main body.

Abstract: An aerial spraying apparatus (unmanned aerial vehicle system) includes one or more drones (unmanned aerial vehicles), and a station on the ground that is connected by wire to at least one of the one or more drones. Each of the one or more drones is equipped with a drone side cable connected to the station or another drone, and a drone side cable mechanism that performs paying out or pulling in of the drone side cable.

Abstract: A swing arm for a saddle riding vehicle which includes a pivot section connected to a vehicle body, and a wheel support section configured to support a rear wheel and which is capable of swinging around the pivot section, includes a swing arm main body made of a fiber reinforced resin, in which the swing arm main body includes a pivot-side opening configured to open an end on a side of the pivot section, and a rear end opening configured to open an end on a side of the wheel support section, and is formed in a hollow shape continuous from the pivot-side opening to the rear end opening.

Abstract: Provided is a multicopter providing a high level of freedom in compact design, and consuming a relatively small amount of energy. The multicopter (10) includes a machine body (12), an N number of first lift generators (30) arranged on a first concentric circle (C1) centered substantially around a gravitational center (G) of the machine body (12) and in a front part and a rear part of the machine body in a bilateral symmetry, and an M number of second lift generators (70) arranged on a second concentric circle (C2) centered substantially around the gravitational center (G) of the machine body (12) and having a larger diameter than the first concentric circle (C1), and in a front part and a rear part of the machine body (12) on a central axial line (X) extending in a fore and aft direction of the machine body (12), N being greater than M.