Abstract: A bicycle sprocket comprises a sprocket body, a plurality of sprocket teeth, at least one shifting facilitation area, at least one driving facilitation area, and at least one bump portion. The at least one shifting facilitation area is to facilitate at least one of a first shifting operation in which a bicycle chain is shifted from the bicycle sprocket toward a smaller sprocket adjacent to the bicycle sprocket in an axial direction parallel to a rotational center axis of the bicycle sprocket without another sprocket between the bicycle sprocket and the smaller sprocket, and a second shifting operation in which the bicycle chain is shifted from the smaller sprocket toward the bicycle sprocket. The at least one bump portion is provided in the at least one driving facilitation area.

Abstract: A bicycle derailleur comprises a base member adapted to be mounted to a bicycle; a movable member movably coupled to the base member; a chain guide coupled to the movable member through a pivot shaft for rotating around an axis (X); a spring mounted around the axis (X), wherein the spring is configured to bias the chain guide in a selected rotational direction; and a resistance applying unit disposed on the pivot shaft. The resistance applying unit includes a friction unit, a one-way transmission unit, and an adjusting unit. The friction unit includes a plurality of first engaging members and at least one second engaging member, wherein the plurality of first engaging members are axially slidable with respect to the pivot shaft. The adjusting unit adjusts an amount of friction between the plurality of first engaging members and the at least one second engaging member.

Abstract: Systems and methods are presented of operating a seawater system to reduce fouling. The seawater system may be installed in a waterborne vessel. A method comprises establishing suction in a first manifold, drawing seawater through a first manifold port, and discharging seawater through a second manifold simultaneous to drawing fluid through the first manifold port. The first manifold is in fluid communication with a first manifold port defined by a cover assembly. The second manifold is in fluid communication with a second manifold port defined by the cover assembly. The cover assembly is positioned in contact with a body of seawater.

Abstract: A sea anchor includes a textile tube and a resiliently flexible support. The textile tube may include a first end and a second end. The first end may have a rim defining a mouth and the second end may be closed. In various embodiments, the resiliently flexible support is coupled to the first end of the textile tube. The resiliently flexible support, in response to the sea anchor being deployed, may be configured to expand the mouth and retain the mouth open. In various embodiments, the textile tube has a conical shape, with the mouth of the first end being a base of the conical shape and the second end being a point of the conical shape. The resiliently flexible support is a ring coupled to the rim of the first end of the textile tube, according to various embodiments.

Abstract: An apparatus for reliquefaction of boil-off gas for a vessel, comprises: a compression unit for compressing the boil-off gas discharged from the storage tank; and a heat exchanger for heat-exchanging the compressed boil-off gas compressed by the compression unit with the boil-off gas discharged from the storage tank; a first expansion means for dividing the boil-off gas passing through the heat exchanger into at least two flows including a first flow and a second flow, and expanding the divided first flow; a first intercooler for cooling the second flow remaining after the division of the first flow by using the first flow expanded by the expansion means as a refrigerant; and a receiver for receiving a second flow having passed through the first intercooler, in which a downstream pressure of the compression unit is controlled by a flow discharged from the receiver.

Abstract: A foldable seat back includes a base, a back plate and a bracket. The base defines a positioning groove therein. The back plate is pivoted on the base, allowing the back plate to be positioned in at least one folded up state and a folded down state. The bracket has one end pivoted on a rear side of the back plate, and the other end releasably engaged in the positioning groove of the base to sustain the back plate in the folded up state.

Abstract: A recreational floating bar apparatus capable of carrying beverages including liquor bottles and drinking vessels having a floatable base. A liquor bottle rack can extend upward from the floatable base, the liquor bottle rack having at least two compartments, each compartment sized to receive one of the liquor bottles. A plurality of drinking vessel retainers can be positioned on the floatable base about the liquor bottle rack. The plurality of drinking vessel retainers can include a first set of drinking vessel retainers having a first size, and a second set of drinking vessel retainers having a second size. The apparatus can be used to store relatively large amounts of beverages to help reduce the need for a user to exit the water to retrieve more beverages.

Abstract: A surfboard includes a core covered with a laminate and having curved perforations in the deck area and the tail area of the surfboard, in order to prevent air blisters from forming between the core and laminate. The curved perforations are deformable under pressure to minimize the opening of the perforations to inhibit liquid from entering and maximizing under zero pressure to allow the maximum amount of trapped liquid and gasses from escaping. The core is formed from an extruded closed-cell polystyrene foam block that has been shaped by restraining it against a shaped form using shaped restraining tools and straps, and heating it; and by cutting using a hot wire. The core is laminated with FIBERGLAS® and epoxy resin, and the perforations are formed using a perforating tool that has a planar or curved working surface and one or more heated needles extending perpendicularly from the working surface.

Abstract: A hull cleaning system is disclosed that comprises a below-waterline hull cleaning head arranged to clean an underwater portion of a hull in-situ, a location determining system arranged to produce location information indicative of the location of the hull cleaning head relative to the hull, and a hub facility remotely located relative to the hull cleaning head. The hub facility is arranged to store the location information, and the system is arranged to send the location information to the hub facility for storage at the hub facility so as to thereby provide a record at the hub facility of clean portions of the hull that have been cleaned by the hull cleaning head and fouled portions of the hull that have not yet been cleaned by the hull cleaning head. The system is also arranged to provide on-line access to the location information stored at the hub facility so as to thereby enable cleaning to continue at a subsequent time using the stored location information.

Abstract: A small watercraft launch comprises a watercraft receiving area defined by a bottom member and side walls. At least one of the side walls defines a port to enable access to the watercraft receiving area (and to a watercraft positioned in the therein). A plurality of aligned notches extending downwardly from the top surface of the side walls on opposite sides of the port which are sized to receive an oar/paddle shaft to allow a boater to pull the small watercraft forward along the small watercraft launch. Lastly, the small watercraft launch has a connecting portion at a bottom of the outer surface of at least one of the launch side walls configured to connect the small watercraft launch to a dock member.

Abstract: A life raft includes a base and an inflatable canopy. The base has a first side and a second side and the inflatable canopy is coupled to the first side of the base and configured to inflate and extend across the first side of the base to form a first chamber defined between the first side of the base and the inflatable canopy. The inflatable canopy is configured to inflate in response to deploying the life raft. Inflation of the inflatable canopy enables the life raft to self-right. In various embodiments, the base includes an inflatable border tube defining a first inflatable volume. The inflatable canopy may define a second inflatable volume and the first inflatable volume may be in fluidic communication with the second inflatable volume.

Abstract: The present invention relates to a life jacket based on a fuel cell that can store hydrogen fuel in it. Particularly, the present invention provides a fuel cell based life jacket that can utilize electricity, heat and water generated during the operation of a fuel cell as a power source of a life extension tool and a personal location beacon. The fuel cell based life jacket of the present invention comprises a fuel cell unit for supplying electricity, a hydrogen fuel supply unit for storing and supplying the hydrogen fuel required for the fuel cell unit to generate electricity, a signal output unit for transmitting a signal using the electricity generated by the fuel cell unit, and a heat generating unit for recovering and transferring the heat generated in the fuel cell unit, wherein the hydrogen fuel supply unit generates hydrogen by using a hydrogen generation composition.

Abstract: Disclosed are an improved nozzle for an unmanned underwater vehicle (UUV), and a method for operating the same. The nozzle includes a first rigid member operatively coupled to a UUV steering mechanism. The nozzle also has a second rigid member, coupled to the first rigid member by a flexible bellows according to a configurable operating angle. The nozzle does not extend beyond a bounding surface when stored but does when deployed. Water traversing the first rigid member and contacting the second rigid member produces a reactive force according to the configurable operating angle. Simultaneous and independent control of the volume of fluid traversing several such nozzles in the UUV, and their respective orientations and operating angles, permits automatic station-keeping or navigation according to another guidance objective.

Abstract: A vessel hull for an inboard-powered marine vessel includes a hull body having a hull bottom that includes a contoured pod mounting surface positioned longitudinally between a central keel and a stern of the hull body. The contoured pod mounting surface has a planar mounting face, for mounting a propulsor pod, and a transition face each positioned between peripheral edges of the pod mounting surface. The transition face slopes forwardly and downwardly from the planar mounting face to the central keel and follows a contour defining a sine wave pattern.

Abstract: A wingsail includes a wing body, a wing axle having an axis, and at least one trim plate supported on a side surface of the wing body, the trim plate to control a rotational movement of the wing body about an axis of the wing axle.

Abstract: A vessel power supply system for a vessel including a propulsion device that includes an engine and a generator driven by the engine to generate electricity, includes a first battery that supplies power to the propulsion device, a second battery that supplies power to accessories of the vessel, a first open circuit voltage sensor that detects an open circuit voltage of the first battery, a second open circuit voltage sensor that detects an open circuit voltage of the second battery, and a switch that is turned on/off to open and close a current path between the first battery and the second battery.

Abstract: A system for maintaining a marine vessel in a body of water at a selected position and orientation includes a global positioning system that determines a global position and heading of the vessel and a proximity sensor that determines a relative position and bearing of the vessel with respect to an object near the vessel. A controller operable in a station keeping mode is in signal communication with the GPS and the proximity sensor. The controller chooses between using global position and heading data from the GPS and relative position and bearing data from the proximity sensor to determine if the vessel has moved from the selected position and orientation. The controller calculates thrust commands required to return the vessel to the selected position and orientation and outputs the thrust commands to a marine propulsion system, which uses the thrust commands to reposition the vessel.

Abstract: Disclosed herein is a method of repairing damage to a fuselage barrel, having a one-piece construction, of an aircraft. The method includes determining at least a first virtual splice line and a second virtual splice line along the fuselage barrel in a direction parallel to a longitudinal axis of the fuselage barrel. The method also includes detecting damage in a first section of the fuselage barrel between the first virtual splice line and the second virtual splice line. The method further includes cutting through the fuselage barrel along the first virtual splice line and the second virtual splice line to physically separate the first section from a main section of the fuselage barrel. The method also includes removing the first section from the main section of the fuselage barrel, and splicing a new section to the main section of the fuselage barrel in place of the first section.

Abstract: An unmanned aerial vehicle includes a fuselage and an arm coupled to the fuselage. The arm includes a first segment, a second segment, and a connecting assembly coupling and locking the first segment and the second segment to each other. The connecting assembly includes a first connecting member and a second connecting member. The first connecting member is rotatably coupled to one of the first segment or the second segment. The second connecting member is coupled to another one of the first segment or the second segment. The first connecting member is rotatable relative to the arm and engages with the second connecting member to lock the first segment and the second segment.

Abstract: An illuminating sidewall system for an internal cabin of a vehicle includes a sidewall panel including at least one window, and a lighting assembly mounted in relation to the sidewall panel above the window(s). The lighting assembly is configured to emit light onto the sidewall panel over the window(s).

Abstract: An illuminating sidewall system for an internal cabin of a vehicle includes a sidewall panel including a lateral segment connected to a ceiling segment, and at least one window. At least one lighting assembly includes a first portion secured to the lateral segment and a second portion secured to the ceiling segment. The lighting assembl(ies) is configured to emit light onto interior surfaces of one or both of the lateral segment and/or the ceiling segment.

Abstract: An aircraft portion includes a fuselage oriented in a longitudinal direction, an airfoil made up of at least one pair of wings arranged on either side of the fuselage in a transverse direction orthogonal to the longitudinal direction, and an airfoil-fuselage junction fairing at the interface between the airfoil and the fuselage. The junction fairing has, in a vertical plane, a lower profile and, in a horizontal plane, a horizontal profile at the junction of the outer surface of the junction fairing with the convex side of each wing. The horizontal profile and/or the lower profile successively has, in the longitudinal direction, a convex front segment, a concave intermediate segment, and a convex rear segment.

Abstract: An actuation unit (15) for actuating a foldable wing tip portion (9) of a wing (3) for an aircraft (1). The actuation unit (15) includes a track (25) configured to be mounted to a fixed wing (5), a carriage (27) configured to engage the track (25) for guided movement along the track (25), and configured to be coupled to a drive unit (31) for driving the carriage (27) along the track (25), and a link (29) configured to be coupled to the carriage (27) and configured to be coupled to a foldable wing tip portion (9).

Abstract: An example of an aerial vehicle includes a rudder removably connected to the aerial vehicle by a twist lock mechanism. The twist lock mechanism is biased in a locked position by an elastic member.

Abstract: The invention relates to an assembly for an aircraft comprising an aircraft wall in which a routing slit is formed, a drive shaft of a bearing surface that passes through the slit while remaining free to move along the slit, and a seal to seal this slit. According to the invention, the seal is formed in two parts, comprising a lower seal part and an upper seal part arranged facing each other on opposite sides of the slit, each of the two parts comprising a lip forming contact tracks between which the drive shaft is squeezed and moves while deforming them during a phase in which the bearing surface is moved, these lips being in the shape of rabbit ears so that they can wind around the shaft so as to limit parasite opening spaces, and to prevent misalignment.

Abstract: A propulsion system assembly includes a propeller and a motor configured to drive the propeller to rotate. The propeller includes one of a first body and a second body. The motor comprises the other one of the first body and the second body. The propulsion system assembly also includes a locking mechanism configured to detachably connecting the first body and the second body. The locking mechanism includes a locking member and a position limiting lock catch. The locking member is configured to lock the first body and the second body. The locking member includes locking parts located at at least two sides of the locking member. When the locking parts of the locking member rotate to a locking position, the position limiting lock catch is mounted to a side of the locking parts, to restrain the locking member from rotating relative to the first body.

Abstract: A propeller blade spanning radially from a root to a tip and spanning axially from a leading edge to a trailing edge spaced from the leading edge forming an airfoil therebetween where a sweep line can be defined as a spline fitted through points which are positioned along the chord line. The propeller blade having at least one spline defining the leading edge or trailing edge.

Abstract: Mitigating whirl flutter in a tiltrotor aircraft includes providing at least one control surface supported for movement relative to a pylon attached to the aircraft's wing; providing an actuator for moving the control surface relative to the pylon; providing at least one sensor system to sense at least one deformation mode of the wing tip; providing a control system having one or more inputs and one or more output signals; using an electrical signal relating to deformation of the wing tip to serve at least as the basis for at least one of the inputs to the control system; determining at least one output signal of the control system based at least in part on the electrical signal relating to deformation; and controlling the actuator based at least in part on the output signal of the control system to move the control surface so as to counteract the deformation.

Abstract: A gimbal having a split design, which can be used in an assembly for actuating an aerodynamic high lift device, is described. The gimbal enables a rotating load path when a force is transferred from the actuator to the high lift device via the gimbal. In particular, the split design can include two receivers which can be coupled to posts extending from a nut. The nut can be secured to a shaft which receives a force generated by the actuator. In one embodiment, the actuator can rotate the shaft to cause the gimbal to translate along the shaft. The split design provides a more compact form factor and is lighter in weight than traditional gimbal designs.

Abstract: Example active flow control systems and methods for aircraft are described herein. An example active flow control system includes a plurality of nozzles arranged in an array across a surface of an aircraft. The nozzles are oriented to eject air across the surface to reduce airflow separation. The active flow control system also includes an air source coupled to the nozzles and a controller to activate the nozzles to eject air from the air source in sequence from outboard to inboard and then from inboard to outboard to create a wave of air moving from outboard to inboard and then from inboard to outboard across the surface.

Abstract: The invention relates to a wing with two winglets (9-12) and a respective airplane. An upstream winglet (9, 11) broadens a region of inclined airflow and a downstream winglet (10, 12) produces a thrust contribution therein.

Abstract: An aircraft emergency landing stability system includes an aircraft, including a fuselage and landing gear, and a blister projecting downwardly from a fuselage-underside surface of the fuselage proximate to a nose of the fuselage. The blister locates a secondary contact surface of the aircraft forward of a center of gravity of the aircraft to mitigate a nose-down pitching moment of the aircraft created in response to contact with a landing surface during an emergency landing.

Abstract: A controller for a hydraulic braking system for an aircraft is disclosed. The hydraulic braking system includes a first accumulator and a second accumulator, the controller configured to: receive first signals including first pressure data from a first pressure transducer associated with the first accumulator, receive second signals including second pressure data from a second pressure transducer associated with the second accumulator, monitor the received first and second signals to determine whether a predetermined condition has been met, and issue a warning indicating a loss of integrity of the hydraulic braking system in response to a determination that one or more predetermined conditions has been met. A hydraulic braking system for an aircraft and method to determine the integrity of a hydraulic braking system are also disclosed.

Abstract: An aspect provides a skid landing gear assembly including a cross member disposed between a first skid tube and a second skid tube, and a tension cable member configured to be disposed in the cross member; wherein the tension cable member resists outward deflection of at least a portion of the skid landing gear assembly when a downward load is applied to the skid landing gear assembly. In other aspects, there are methods of avoiding ground resonance in a skid landing gear assembly, methods of assembling a skid landing gear assembly, methods of operating a helicopter with a skid landing gear assembly, and methods of improving the service life of a skid landing gear assembly.

Abstract: An aerial vehicle system including a vertical takeoff and landing apparatus, a wing assembly removably coupled to the vertical takeoff and landing apparatus, and a rotor guard interchangeable with the wing assembly and removably coupleable to the vertical takeoff and landing apparatus. The vertical takeoff and landing apparatus can include a frame, a control module carried by the frame, and a plurality of thrust assemblies carried by the frame.

Abstract: A mast lockout system for a tiltrotor aircraft having a proprotor assembly. The system includes a mast coupled to and rotatable with the proprotor assembly. A proprotor gearbox having a proprotor gearbox housing is operable to transmit torque and rotation energy to the mast. A lock assembly has first and second lock members. The first lock member is coupled to and rotatable with the mast. The second lock member is coupled to the proprotor gearbox housing. The lock assembly has a first position in which the first and second lock members are disengaged, thereby allowing rotation of the proprotor assembly. The lock assembly has a second position in which the first and second lock members are engaged, thereby preventing rotation of the proprotor assembly. The lock assembly is actuatable between the first and second positions.

Abstract: A rotorcraft including a main rotor, flight controls connected to the main rotor the main rotor, a plurality of engines connected to the main rotor and operable to drive the main rotor, a main rotor revolutions per minute (RPM) sensor, and a monitoring system operable to determine an engine failure of the plurality of engines. The monitoring system is further operable to engage an automated autorotation entry assist process in response to at least determining the engine failure and according to the measured main rotor RPM, where the automated autorotation entry assist process comprises the monitoring system generating one or more rotor RPM related commands according to at least a target main rotor RPM and the measured main rotor RPM, where the automated autorotation entry assist process further comprises controlling the one or more flight controls according to the one or more rotor RPM related commands.

Abstract: A mast lockout system for a tiltrotor aircraft having a proprotor assembly. The system includes a mast coupled to and rotatable with the proprotor assembly. A proprotor gearbox having a proprotor gearbox housing is configured to transmit torque and rotation energy to the mast. A lock assembly has first and second lock members. The first lock member is coupled to the mast between first and second mast bearings and configured to rotate with the mast. The second lock member is coupled to the proprotor gearbox housing. The lock assembly has a first position in which the first and second lock members are disengaged, thereby allowing rotation of the mast. The lock assembly has a second position in which the first and second lock members are engaged, thereby preventing rotation of the mast. The lock assembly is actuatable between the first and second positions.

Abstract: The exemplary embodiments herein provide a tether for use with an airborne device, where the tether contains an elongate member having a first end for attaching to a ground attachment point and an opposing second end for attaching to the airborne device where the elongate member has a cross-sectional area which varies across the member. In some embodiments, the tether contains one or more electrically conductive elements, an optional strength element, insulation separating any adjacent electrically conductive elements, and a jacket which surrounds and protects each of the tether components.

Abstract: This disclosure relates generally to drones, and more particularly to method and system for performing inspection and maintenance tasks of three-dimensional structures (3D) using drones. In one embodiment, a method for performing a task with respect to a 3D structure is disclosed. The method includes receiving a simulated 3D view of the 3D structure. The simulated 3D view comprises a hierarchy of augmented views to different degrees. The method further includes configuring one or more paths for performing a task on the 3D structure based on the hierarchy of augmented views, historical data on substantially similar tasks, and a capability of the at least one drone. The method further includes learning maneuverability and operations with respect to the one or more paths and the task based on the historical data on substantially similar tasks, and effecting performance of the task based on the learning through the at least one drone.

Abstract: A flight device including a device main body and a plurality of lift force providing modules is provided. The lift force providing modules are connected to the device main body. Each of the lift force providing modules includes two propellers, and each of the propellers rotates to lift the device main body. Two propellers of each of the lift force providing modules may rotate around the same rotation axis. The flight device has an enhanced lift force and good efficiency in lifting, and the flight device has a reduced device volume and improved flight reliability.

Abstract: A technique is introduced for autonomous landing by an aerial vehicle. In some embodiments, the introduced technique includes processing a sensor data such as images captured by onboard cameras to generate a ground map comprising multiple cells. A suitable footprint, comprising a subset of the multiple cells in the ground map that satisfy one or more landing criteria, is selected and control commands are generated to cause the aerial vehicle to autonomously land on an area corresponding to the footprint. In some embodiments, the introduced technique involves a geometric smart landing process to select a relatively flat area on the ground for landing. In some embodiments, the introduced technique involves a semantic smart landing process where semantic information regarding detected objects is incorporated into the ground map.

Abstract: Using battery monitoring and unmanned aerial vehicle (UAV) management, a method and system provide persistent airborne surveillance for intelligence, surveillance, and reconnaissance (ISR) systems supported by UAVs within an airborne surveillance pattern (ASP). In one embodiment, a UAV operating in the ASP with degraded battery charge is autonomously swapped with a UAV having a fully-charged battery to provide persistent aerial surveillance for an extended duration over that of a single UAV.

Abstract: In some embodiments, systems, apparatuses and methods are provided to enhance delivery of packages. Some embodiments provide an unmanned delivery system comprising: a rotational drive shaft; a crane motor cooperated with the drive shaft that is rotated by the crane motor; a first crane system with a first cord fixed with the first crane system, wherein the first crane system is configured to cooperate with the drive shaft to control the first crane system in controlling the spooling and retraction of the first cord; a control circuit coupled with the crane motor; and a stop switch electrically coupled with the control circuit and positioned to be contacted by a package release hanger secured with the first cord when the first cord is retracted to a first threshold; wherein the control circuit is configured to stop the crane motor in response to receiving a signal from the stop switch.

Abstract: In some embodiments, systems, apparatuses and methods are provided to enhance delivery of packages and/or cargo through the use of unmanned delivery vehicle. In some embodiments, a mechanical package release system is provided that comprises: a package release hanger configured to couple with and suspend from an unmanned delivery vehicle; and one or more tension supports each configured to secure with a package and to releasably couple with the package release hanger wherein a decrease of at least a threshold amount of a force being applied by the weight of the package on the one or more tension supports induces a mechanical release of the coupling between the one or more tension supports and the package release hanger resulting in a release of the package from the unmanned delivery vehicle.

Abstract: This disclosure describes an aerial vehicle, such as an unmanned aerial vehicle (“UAV”), which includes a plurality of maneuverability propulsion mechanisms that enable the aerial vehicle to move in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll). The aerial vehicle may also include a lifting propulsion mechanism that operates to generate a force sufficient to maintain the aerial vehicle at an altitude.

Abstract: An assembly comprising a drone (1) and at least one releasable load (37) mounted on the drone, the drone comprising an on-board data processing system, the releasable load (37) comprising at least one sensor delivering a piece of information that can be used to ascertain the path of same and actuators for controlling flight control surfaces allowing it to be oriented as it falls, being linked to the drone (1) by an optical fibre (70), the load and the drone being arranged to exchange information via the optical fibre while the load is falling, the load transmitting data originating from said at least one sensor and the drone transmitting data for controlling the actuators, established taking into account that received from the load, in order to guide the load towards a predefined target.

Abstract: An illuminating ceiling system for an internal cabin of a vehicle includes a plurality of ceiling panels. Each of the ceiling panels includes a lighting, assembly secured to a first portion that overlaps a second portion of adjacent one of the ceiling panels. The lighting assembly is configured to emit light into the internal cabin.

Abstract: An oxygen mask container assembly that includes a container that defines a container interior and includes a container opening, an oxygen mask assembly disposed in the container interior, a mask ejector in operative communication with the mask assembly, a cover assembly that is movable between a closed position where the cover assembly covers the container opening and an open position where the mask can be ejected through the container opening and from the container interior, and a latch assembly. The oxygen mask assembly includes a mask and a lanyard. The cover assembly includes a light assembly therein that is configured to shine light below the cover assembly. The latch assembly is configured to move the cover assembly between the closed position and the open position.

Abstract: In order to make available a space-saving sanitary unit having a toilet which offers improved user convenience to persons with restricted mobility, a cabin module for an aircraft is described which has a sanitary unit. The sanitary unit has a toilet cubicle with a toilet. The toilet cubicle is formed by four side walls and the toilet is arranged on a first side wall. A first access door is arranged in a second side wall, which extends transversely to the first side wall and adjoins the first side wall. A surface which is designed to at least partially accommodate a wheelchair is provided as an option within the toilet cubicle. The cabin module is configured to be installed with the second side wall transversely to a direction of flight. The first side wall 18a is aligned with an external wall in the installed state.