Abstract: A UAV having a fuselage body including a cavity that forms a cargo bay for transporting a payload, and a lower access opening providing an exit for the payload from the cargo bay, the lower access opening including a lower cargo bay door, an actuator positioned in the fuselage body, a linkage assembly connected to the actuator and connected to the lower cargo bay door, wherein the actuator and linkage assembly are operable to open and/or close the lower cargo bay door, wherein a first horn is mounted to the actuator, and wherein the linkage assembly includes a first linkage member having a first end and a second end, the first end of the first linkage member pivotally attached to the first horn and the second end of the first linkage member pivotally attached to the cargo bay door.

Abstract: An aircraft wing structure includes first and second unitary shell structures formed from a fiber-reinforced composite material. Each shell structure includes a partial front spar, a partial rear spar and a wing skin. The partial front spars of each shell structure and the partial rear spars of each shell structure are arranged to overlap to form front and rear spars respectively. A wing box structure is lightweight, strong and durable, with a lower overall part count than has been conventionally achievable. Aircraft systems equipment may be attached to the shell structures prior to, or after, assembly into a wing box.

Abstract: Wing assemblies comprise one or more wing support structures, an inboard-most flap, and one or more flap supports that operatively couple the inboard-most flap to the wing support structure(s). The flap support(s) comprise at least an inboard-most inboard-flap support that is outboard of the inboard edge of the inboard-most flap.

Abstract: Disclosed are electric vertical take-off and landing (eVTOL) aircraft gaming apparatuses and methods. In one embodiment, a video game apparatus comprises a processor, a first inceptor, communicatively coupled to the processor, the first inceptor configured to accept longitudinal and lateral linear movements as manual input and provide corresponding signals to the processor, and a second inceptor, communicatively coupled to the processor, the second inceptor configured to accept longitudinal and lateral linear movements as manual input and provide corresponding signals to the processor, wherein the processor is configured to control a heading of an aircraft in a video game using a signal received from the second inceptor corresponding to lateral linear movement of the second inceptor. Some embodiments may additionally include at least one sensor and a thumb stick for each inceptor.

Abstract: A pedal cartridge for an aircraft. The pedal cartridge is connectable to a pedal mechanism and includes: a pedal. The pedal includes a pedal axle receiving portion configured to receive a pedal axle of the pedal mechanism such that the pedal is rotatably connectable to the pedal axle. The mechanism also includes a first rotation sensor component, the first rotation sensor component configured to interact with a second rotation sensor component of the pedal mechanism to permit rotation of the pedal about the pedal axle to be detected.

Abstract: A control input operable by a user for controlling movement of an aircraft includes a base portion configured for coupling to a support surface, the base portion biased towards a neutral position defined along a central axis and pivotable to a plurality of angular positions relative to the central axis. The control input also includes a grip portion having inputs for controlling movement of the aircraft and pivotally coupled to the base portion, the grip portion pivotable between a first position in which the grip portion extends from the base portion and a second position in which the grip portion is pivoted relative to the base portion. Further, the control input includes a lock mechanism for locking the grip portion in the first position wherein releasing the lock mechanism allows the grip portion to move to the second position.

Abstract: An aircraft brake system includes a supply line for supplying hydraulic fluid to wheel brakes, and an associated return line. Hydraulic fluid is replenished in at least a portion of the return line both before applying a braking force to the one or more wheels of the aircraft during landing, and before an intervening, optional, step if so performed of testing the brake system before landing of the aircraft. Replenishing the hydraulic fluid can be conducted by a control unit automatically and/or in response to a pressure drop in the return line measure by a transducer.

Abstract: A landing gear assembly for a vehicle, such as a helicopter, includes a linkage coupled to the vehicle and configured to reciprocate between a stowed position and a deployed position. A shock strut forms a part of the linkage. The landing gear assembly further includes a side brace having a first end coupled to the linkage and a second end coupled to the vehicle. The side brace provides a driving force that reciprocates the linkage between the stowed and deployed position. The side brace includes an energy attenuation system that dissipates energy when a compressive load on the side brace exceeds a predetermined threshold.

Abstract: An apparatus includes a first component comprising a carbon composite substrate. A high temperature coating is disposed on the surface of the carbon composite substrate. The high temperature coating includes a bond layer of a metal carbide on the surface of the substrate. The apparatus includes a second component, and braze material joining the surface of the first component to the second component. In some examples, a brake assembly may include a rotor having a surface configured to interface with another component of the brake assembly. The brake assembly includes an insert joined to the surface of the rotor without a mechanical fastener, and the insert defines a tough mechanical contact surface configured to protect the rotor.

Abstract: An aircraft brake control system for controlling antiskid braking of an aircraft wheel is disclosed including a control assembly having a mode controller which sets the mode of operation of an antiskid brake calculator, configured to set a first mode, when an input of the indication of a brake energy supply configuration indicates a first brake energy supply being used, in which the antiskid brake calculator applies a first restriction level on a rise rate of the antiskid brake command, and a second mode, when the input 305 indicates a second brake energy supply being used, in which the antiskid brake calculator applies a second, lower, restriction level on a rise rate of the antiskid brake command.

Abstract: A main fitting includes an elongate piston and a cylinder configured to slidingly receive the piston. A first end of the piston extends from a first end of the cylinder, and a second end of the piston extends from a second end of the cylinder. The first end of the cylinder comprises a bearing surface engaging the piston to limit translation of the piston relative to the cylinder to a longitudinal direction.

Abstract: A compound vertical takeoff and landing aircraft includes a fuselage with a modular payload configuration for passenger, cargo, or medical transport functions; contra-rotating main rotors mounted on an upper side of the fuselage and driven by at least one motor; and a plurality of tiltable thrusters mounted respectively at a forward section and at an aft section of the fuselage, each tiltable thruster being powered by one or more separate motors. The motors driving the contra-rotating main rotors and the tiltable thrusters may all be electric. The tiltable thrusters may be ducted or unducted and may each be provided with one or more control surfaces at an aft end. Battery modules may be located underneath a floor of the fuselage and may be arranged in one or more groups of batteries so as to so as to facilitate removal and replacement of the batteries.

Abstract: A blade comprising a blade root extended by an aerodynamic intermediate part that extends up to a free end. The blade root comprises a one-piece attachment body made from composite materials, that is hollow and has a casing that defines an empty internal space, the attachment body incorporating: a pitch attachment configured to be traversed by a pitch link rod connected to a pitch lever, the attachment body incorporating a leading edge attachment configured to be traversed by a leading edge link rod connected to a first drag damper, a trailing edge attachment configured to be traversed by a trailing edge link rod configured to be connected to a second drag damper, and a connection attachment configured to be traversed by at least one connecting rod connected to a first reinforcement of a stratified spherical stop.

Abstract: A rotor blade configured to be installed on a rotary wing aircraft includes a spar including an inboard portion extending from a root of the rotor blade to a first spanwise position of the rotor blade and an outboard portion meeting the inboard portion at the first spanwise position. The rotor blade further includes an upper skin and a lower skin coupled the outboard portion of the spar. The first spanwise position is defined by a most inboard point at which the upper and lower skins are coupled to the spar. The inboard portion includes a top layer, a bottom layer, and an inner cavity. The top layer has a substantially constant first thickness and the bottom layer has a substantially constant second thickness, and the distance between an outer surface of the top layer and an outer surface of the bottom layer is substantially constant.

Abstract: A rotorcraft with at least one main rotor and a fuselage, comprising: a tail boom connected to the fuselage, the tail boom extending from the fuselage toward a duct-type portion; a shroud provided at the duct-type portion and forming a transverse duct; at least one ducted tail rotor rotatably arranged in the transverse duct, wherein the at least one ducted tail rotor comprises a plurality of rotor blades mounted to a rotatable rotor hub; and a stator with a gearbox fairing mounted to the shroud for supporting the rotatable rotor hub in the transverse duct, wherein the stator comprises at least one rotatable stator blade connecting the gearbox fairing to the shroud.

Abstract: A rotorcraft with at least one main rotor and a fuselage, comprising: a tail boom connected to the fuselage, the tail boom extending in a longitudinal direction from the fuselage toward a duct-type portion; a shroud provided at the duct-type portion and forming a transverse duct comprising a circumferential direction and a longitudinal extension oriented at least essentially perpendicular to the circumferential direction and the longitudinal direction of the tail boom; and at least one ducted tail rotor rotatably arranged in the transverse duct; wherein the shroud comprises a first section connected to the tail boom and a second section spaced apart from the tail boom and diametrically opposed to the first section, the first section comprising an airfoil-like aerodynamic profile.

Abstract: A seaplane float propulsion system that is configured to provide maneuverability and directional movement of a seaplane subsequent the engine and propeller being deactivated. The present invention includes a first float member and a second float member wherein the first float member includes a first propulsion assembly mounted therein and the second float member includes a second propulsion assembly mounted therein. The first propulsion assembly and second propulsion assembly are identically constructed. The propulsion assemblies are independently controlled so as to provide both directional and rotational movement of the seaplane to which the present invention is operably installed. The propulsion assemblies include elements that are operable to intake and direct water flow in order to create the desired movement of the seaplane in which the seaplane float propulsion system is installed. The propulsion assemblies include an intake element that provides ideal fluid and aero dynamics.

Abstract: An aerial vehicle including a main body having a leading edge. An inlet is recessed aft from the leading edge. Forward protrusions extend from the main body on opposite sides of the inlet. An outlet nozzle is proximate to an aft end. The inlet is in fluid communication with the outlet nozzle. Wings extend from the main body.

Abstract: A system for repositioning rails in a cargo bay of an aircraft. The system includes a base configured to be coupled to a structure in the cargo bay and having a first side and a second side. The system further includes a cradle for receiving a rail for restricting movement of a unit load device (ULD) in at least one direction, the cradle configured to position the rail between a first position and a second position in which the rail is closer to the second side of the base than when the rail is in the second position.

Abstract: The present invention relates to a power management and distribution device (4) for powering a personal electronic device via a direct current outlet unit (6a; 6b; 6i) at a passenger seat in an airplane cabin, the power management and distribution device (4) comprising: a first interface (12) for receiving electrical supply power (10); a second interface (14) for supplying electrical supply power (10) received at said first interface (12) to another power management and distribution device (4i); a third interface (16) for supplying electrical supply power (10) received at said first interface (12) to the direct current outlet unit (6a; 6b; 6i) for the personal electronic device; a further interface (15; 17) for supplying electrical supply power (10) received at said first interface (12) to either an inflight entertainment screen (17a; 17b; 17i) or an alternating current outlet (5a; 5b; 5i) at the passenger seat; a power measurement device (82, 80; 85) configured to measure the electrical outlet power (20) dra

Abstract: A spreader for a passenger seat includes a body having a forward end and an aft end. The body defines at least one roller support rail monolithic with the body and between the forward end and the aft end. The spreader includes a non-uniform thickness along a length of the body between the forward end and the aft end.

Abstract: A cabin pressure control system comprising an automatic motor controller (AMC); and a manual motor controller (MMC) that comprises a motor configured to regulate cabin pressure; a cabin pressure sensor configured to determine a first set of cabin pressure data; a differential pressure sensor comprising first and second ports, the first port configured to obtain a second set of cabin pressure data and the second port configured to obtain a first set of ambient pressure data; processing circuitry coupled to the cabin pressure sensor and to the differential pressure sensor, the processing circuitry configured to receive the first set of cabin pressure data; determine a first set of differential pressure data, the first set of differential pressure data relating the second set of cabin pressure data with the first set of ambient pressure data; disable the AMC; and control the motor to regulate the cabin pressure.

Abstract: An airplane mainly extending along an axis between a nose group and a tail group is provided. The airplane has a fuselage extending axially between the nose group and the tail group and having a fuselage wall internally defining a fuselage housing, wings extending transversely to the axis from the fuselage, and at least one passenger pod having a pod wall defining a pressurized passenger housing in which passengers are accommodable. The at least one passenger pod is removably housable in the fuselage housing. The airplane is configurable in an operating configuration, suitable for allowing flight of the airplane, in which the at least one passenger pod is housed in the fuselage housing and an emergency configuration, in which, with the airplane in flight, the at least one passenger pod is ejected from the fuselage housing.

Abstract: A coupling system is configured to secure one or more struts to a wing of an aircraft. The coupling system includes one or more splice straps that secure the one or more struts to the wing. A method for securing one or more struts to a wing of an aircraft includes securing, by one or more splice straps, the one or more struts to the wing.

Abstract: Exhaust systems having adjustable nozzles and related methods are disclosed. An example exhaust system includes a nozzle. A portion of the nozzle is moveable from a first position to a second position to change an angle of convergence of the nozzle. The example exhaust system includes an exit area. The portion of the nozzle is at least partially disposed in the exit area. An opening is defined between the exit area and the portion of the nozzle disposed in the exit area. A size of the opening is to change in response to movement of the portion of the nozzle.

Abstract: A gear pump is described with at least two intermeshing gearwheels which are each rotationally fixedly connected to a shaft and separate a suction side from a delivery side. The shafts are mounted in a housing. One of the shafts can be brought into active connection with a drive unit and the other of the shafts can be brought into active connection with a pressure-control device which is to be driven by the drive unit via the two shafts. Furthermore, a drive device with the gear pump is proposed for setting an angle of attack of propeller blades of an adjustable-pitch propeller. In addition, an adjustable-pitch propeller having the drive device is described.

Abstract: Systems and methods are disclosed for lighting a vehicle. A system includes a plurality of lights disposed on a vertical take-off and landing (VTOL) vehicle configured to turn on and off, change color, and/or change intensity. The system further includes a controller configured to determine a lighting scheme for the plurality of lights, the lighting scheme including a setting for the plurality of lights, the setting including one or more of turning the plurality of lights on or off, setting a color of the plurality of lights, and setting an intensity of the plurality of lights, determine a location in or associated with the VTOL vehicle, wherein the lighting scheme is configured to guide a person to the location, and transmit a signal to the one or more lights to execute the lighting scheme to guide the person to the determined location.

Abstract: An integrated urban air mobility system includes: an air taxi including a boarding capsule adapted to allow a passenger to board or alight from the boarding capsule in a boarding/alighting area, and an aircraft adapted to dock with the boarding capsule and flying in an airway; and a vertiport having an outer wall defining an interior space, the interior space including an air taxi movement space in which the air taxi moves, a boarding capsule movement space in which the boarding capsule moves, and an aircraft movement space in which the aircraft moves.

Abstract: Systems and methods for interlining checked bags between two unaffiliated airlines. The traveler may purchase the interlining service and be assured that the checked bags associated with that service will be automatically transferred from their first flight to their next flight. The traveler does not have to collect the checked bag, and then re-check it onto the second flight, which may allow a traveler to say with in the security zone of the airport, where permitted by airport flow.

Abstract: A device for creating a stiffened region on an outer structure of an aircraft for subsequently providing a service access if required is disclosed having an outer structure, a reinforcing plate which is mounted in a predetermined installation region on an inner side of the outer structure and forms a contact surface between the reinforcing plate and the outer structure. The reinforcing plate has a through-opening along the surface normal of the contact surface, and a connecting material which connects the reinforcing plate to the outer structure in an edge region of the contact surface by substance-to-substance bonding and/or by interlocking engagement.

Abstract: Methods and apparatus for Real-time Satellite Imaging System (10) are disclosed. More particularly, one embodiment of the present invention an imaging sensor (14) on a geostationary satellite having one or more co-collimated telescopes (18). The telescopes (18) illuminate focal planes (22) which are sparsely populated with focal plane arrays (24). The focal plane arrays (24) record the entire observable Earth hemisphere at one time, at least once every ten seconds.

Abstract: A surveillance satellite that has detected a significant high luminance generates launch sensing data indicating a launch time point corresponding to a detection time point, a launch coordinate value expressing a position at which the significant high luminance was detected, and a line-of-sight vector at the detection time point and containing surveillance data at the detection time point and transmits the launch sensing data. A communication satellite that passes through a point in a communication range with respect to the surveillance satellite to transmit the launch sensing data receives the launch sensing data and transmits the launch sensing data to remaining communication satellites via a satellite communication network.

Abstract: The present invention discloses a method for autonomous mission planning of Carbon Satellite, which triggers autonomous mission planning for the satellite when it detects the satellite switching from a shadow area to a light area, comprising: determining planning time sequence, wherein the planning time sequence comprise several time nodes; and then, for each time node, carrying out a prediction of the ground attributes of the sub-satellite point, and setting observation arc segment according to the prediction result; and finally, determining the load power-on-off time sequence according to the observation arc segment.

Abstract: A vehicle including a sealed container, a propulsion system with an intake and an exhaust affixed to an interior of the sealed container, an exhaust stream emitted from the exhaust, a thrust corridor within the sealed configured to channel the exhaust stream, and a return corridor configured to channel an intake stream into the intake of the propulsion system wherein the exhaust stream transforms into the intake stream after traveling a sufficient distance within the sealed container and the exhaust stream and intake stream generate a pressure differential within the sealed container wherein the pressure differential is sufficient to result in a movement of the vehicle relative to the vehicle's surroundings.

Abstract: The cabin conditioning system can include a cabin air loop, a refrigerant loop, and a set of thermal rejection components. The system can optionally include a phase-change fluid loop. However, the cabin conditioning system can additionally or alternatively include any other suitable set of components. The cabin conditioning system functions to condition a cabin interior (and/or an air volume therein) of a vehicle, such as an atmospheric and/or space-flight capsule. Additionally or alternatively, the system can function to reject heat from the vehicle interior and/or vehicle power systems (e.g., avionics components thereof). Additionally or alternatively, the system can function to maintain the humidity of air within the cabin interior. However, the cabin conditioning system can include any other suitable components.

Abstract: A radiator structure for a satellite is provided. A first radiator panel adapted to be positioned on a first side of a central body, and a second radiator panel adapted to be positioned on a second side of the central body. Other implementations include a third radiator panel positioned on a third side of the central body. The apparatus also includes at least one heat pipe embedded between a first face and a second face of each radiator panel and extending from the first radiator panel through the first radiator panel and through the second radiator panel. The heat pipe structurally supports the first radiator panel and the second radiator panel relative to the intermediate radiator panel. A method of manufacturing a radiator structure is also provided.

Abstract: A launch pad system includes a fuel vent port provided in a launch vehicle, a launch pad fuel tank provided outside the launch vehicle to store fuel, a fuel recovery line connecting the fuel vent port and the launch pad fuel tank such that the fuel is transferred therethrough, and a fuel transfer unit provided on the fuel recovery line to transfer the fuel, wherein the fuel may be recovered from the launch vehicle to the launch pad fuel tank.

Abstract: A drone integrated control device that controls a drone by unifying respective components on one board includes a flight control unit including a plurality of sensors and configured to control a path and a flight attitude of the drone, a motor control unit configured to control a rotation speed of at least one motor mounted to perform movements and takeoffs of the drone, a communication unit configured to transmit and receive control signals input to and output from the respective components included in the drone integrated control device, and a power supply unit configured to supply power to the respective components included in the drone integrated control device to operate the respective components.

Abstract: Described herein are unmanned aerial vehicles (UAVs), systems, and methods for capturing panoramic images using cameras onboard a UAV. For example, an embodiment pertains to a UAV including a flight control system, a propulsion system operatively coupled with the flight control system, and an image system comprising navigational cameras and a gimbal camera. The image system is configured to capture a first set of images of a scene using the navigational cameras, stitch the first set of images together to create a first panoramic image of the scene, identify a flight plan for capturing a second set of images with which to create a second panoramic image of the scene using the gimbal camera, capture the second set of images of the scene using the gimbal camera, and stitch the second set of images together to create the second panoramic image.

Abstract: A UAV including a wing attached to a fuselage body, a rotatable cargo bay in the fuselage body, the cargo bay having an entrance for receiving the payload, an actuator in the fuselage body operable to rotate the cargo bay about a pivot axis into a first position where the entrance of the cargo bay is positioned above the fuselage body to allow for entry of the payload into the cargo bay, and the cargo bay extends through an opening in an upper surface of the fuselage body, rotatable into a second position where the entrance of the cargo bay is positioned within the fuselage body during transport; and rotatable into a third position where the entrance of the cargo bay is positioned below the fuselage body to allow for exiting of the payload, and the cargo bay extends through an opening in a lower surface of the fuselage body.

Abstract: A vertical take-off and landing aircraft includes a primary rotor unit having a rotor axis, an upper rotor system, and a lower rotor system. The upper rotor system includes an upper swashplate configured to translate along the rotor axis and not configured to tilt relative to the rotor axis and a pair of top blades configured to rotate about the rotor axis. Translation of the upper swashplate causes a pitch of each of the top blades to change equally. The lower rotor system includes a lower swashplate configured to translate along the rotor axis and not configured to tilt relative to the rotor axis and a pair of bottom blades configured to rotate about the rotor axis. Translation of the lower swashplate causes a pitch of each of the bottom blades to change equally. The aircraft further includes a plurality of secondary rotors each having fixed-pitch rotor blades.

Abstract: A system, a method, and a computer program product may be provided for charging an unmanned aerial vehicle (UAV). The system may include a memory configured to store computer executable instructions and a processor configured to execute the computer executable instructions to obtain a set of UAV attributes and location information associated with an UAV, identify a plurality of electric power lines in proximity of the UAV based on the location information, obtain a set of electric power line attributes for the plurality of electric power lines, and identify one or more electric power lines from the plurality of electric power lines based on the set of UAV attributes, the set of electric power line attributes and a trained first machine learning model. The processor is configured to direct the UAV to the identified one or more electric power lines for charging the UAV.

Abstract: An autonomous vehicle (AV) delivery system is configured to deliver a payload or package in a rural and/or urban environment. The AV delivery system includes a first autonomous vehicle (AV). The first AV is configured to travel between a payload receiving location and a payload drop location. The AV delivery system further includes a second autonomous vehicle (AV) coupled to the first AV. The second AV is coupled to a payload and configured to travel between the first AV and a designated drop target adjacent to a ground or receiving surface at the payload drop location.

Abstract: A storage station for unmanned vertical take-off and landing (VTOL) aircrafts includes a storage case (110) for accommodating an unmanned VTOL aircraft therein, a first coupling member (120) having one end pivotably coupled to an inner upper surface of the storage case and the other end protruding out of the storage case by a pivoting operation, and a second coupling member (130) provided at the other end of the first coupling member, in which one end of a main body of the unmanned VTOL aircraft is coupled to the second coupling member, and the second coupling member is rotatable about a rotation axis in a longitudinal direction of the first coupling member, whereby it is possible to provide an advantageous effect of simultaneously storing and charging multiple drones on sides, and it is particularly possible to provide an advantageous effect of charging and storing a large number of drones used in swarm flight technology, which has recently become increasingly useful.

Abstract: Provided is a capsule for mounting a drone. The capsule for mounting a drone includes a body having a first space for accommodating a drone and a second space provided to surround at least a portion of the first space, a base portion provided in the first space so that a drone is mounted, and a valve provided in the body to open or close the second space so that external fluid is introduced into the second space.

Abstract: An apparatus for securing a cap on a cylindrical container includes: a stage including a receiving region for separately receiving a cap and a container; and an elevator movable upwardly away from the stage and downwardly toward the stage. The elevator includes: a carrier disposed over the stage; a capturing member on the carrier and configured to capture the cap; and at least one extendable member extending from the carrier, the at least one extendable member movable from a home position with the extendable member above a center of the cap and an engagement position with the extendable member engaging the center of the cap and urging the center of the cap downwardly relative to an outer sidewall of the cap.

Abstract: In an example embodiment, an apparatus for making pouch products includes a conveyor system. The conveyor system includes a first receiving location along a path of the conveyor system, and a dosing location along the path of the conveyor system. The apparatus also includes a first material dispensing station configured to transfer a first material to the first receiving location. The first material includes a first elastic layer and a first support layer. The first material dispensing station includes a dispenser roller configured to hold a roll of the first material, a plurality of rollers configured to convey the first material from the dispenser roller to the first receiving location, and a stripper plate configured remove at least a portion of the first support layer from a portion of the first elastic layer.

Abstract: The present application relates to apparatus for stretch wrapping goods with stretch wrap film including: a film roll carriage for dispensing at least one band of film from at least one stretch wrap film roll core, a roping mechanism for roping the at least one band of film by edging at least one lateral side edge of the film, a pre-stretcher for pre-stretching the film by passing the roped film through a pre-stretcher, a stretch wrap carousel for wrapping the roped and pre-stretched film around the goods, wherein the at least one band of film is passed through the roping mechanism prior to the pre-stretcher.

Abstract: A binding machine includes: a wire feeding portion configured to feed a plurality of wires; a curl forming portion configured to constitute a looped feeding path for winding the plurality of wires fed by the wire feeding portion around a binding object; and a binding portion configured to twist the plurality of wires wound around the binding object. The curl forming portion includes: a curl guide configured to curl the plurality of wires fed by the wire feeding portion; and a leading guide configured to lead the plurality of wires curled by the curl guide to the binding portion. The curl guide is configured to allow the plurality of wires to pass therethrough while being arranged in a radial direction of the looped feeding path.

Abstract: A binding machine includes: an accommodating portion configured to accommodate a wire; a wire feeding portion configured to feed the wire accommodated in the accommodating portion; a curl forming portion configured to constitute an annular feeding path for winding the wire fed by the wire feeding portion around an object to be bound; and a binding portion configured to twist the wire wound around the object to be bound. The curl forming portion includes a curl guide configured to curl the wire fed by the wire feeding portion, and a leading guide configured to lead the wire curled by the curl guide to the binding portion. The accommodating portion is disposed to be offset in one direction with respect to the curl guide. The curl guide is configured to feed out the wire toward the one direction.