Abstract: An inflatable stand-up paddle board (SUP) and a built-in inflation pump are provided. The inflation pump includes a pump body incorporated into a body of the SUP, an inflation assembly, and inflation and deflation valves in communication with an air chamber of the SUP. The body of the SUP includes first and second surfaces and a lateral confining band extending in a circumferential direction of the SUP and covering edges of the first and second surfaces. A mounting space may extend through the air chamber and the inflation pump may be mounted within the mounting space.

Abstract: A recreational sport boat includes a hull, having starboard and port sides and a transom, and a pair of wake-modifying devices positioned aft of the transom. One of the wake-modifying devices is positioned on a port side of the boat's centerline and another of the wake-modifying devices is positioned on a starboard side of the boat's centerline. Each wake-modifying device includes a plate-like member and at least one downturned surface at a trailing portion of the plate-like member. Each wake-modifying device is pivotable between a non-deployed position and a deployed position about a pivot axis that is horizontal or inclined no more than about 35° from horizontal. When a wake-modifying device is in the deployed position, the downturned surface is lower than it is in the non-deployed position so as to be able to modify the boat's wake.

Abstract: One example provides a protective cover for an electric vehicle. The protective cover includes a main body to selectively fit over a body portion of the electric vehicle, including over a charging port of the electric vehicle, and includes an opening extending through the main body, the opening located so as to be proximate to the charging port when the protective cover is installed on the electric vehicle, the opening to receive and enable a charging gun to be disposed at least partially within the protective cover and be inserted into the charging port to thereby enable charging of the electric vehicle without removal of the protective cover.

Abstract: The invention provides an anti-fouling lighting system configured for preventing or reducing biofouling on a fouling surface of an object, by providing an anti-fouling light via an optical medium to said fouling surface, the anti-fouling lighting system comprising: a lighting module comprising a light source configured to generate an anti-fouling light, and said optical medium configured to receive at least part of the anti-fouling light, the optical medium comprising an emission surface configured to provide at least part of said anti-fouling light ; and comprising silicone that includes particles of, for example, silica, glass, or mica, wherein a density of the particles in the silicone increases from within the optical medium towards the emission surface .

Abstract: A collision information providing system provides information about a collision with a marine vessel, and includes a controller configured or programmed to function as a judging unit to judge whether or not there has been a collision of an object with a marine vessel, an information obtaining unit to obtain information about the collision when the judging unit judges that there has been the collision, and a providing unit to provide the information obtained by the information obtaining unit.

Abstract: Disclosed herein is an inflatable watercraft barrier in one example having an inflatable perimeter tube. Also disclosed is a diaphragm sealed to the perimeter tube to form the watercraft barrier between a watercraft and the water in which the watercraft barrier and watercraft float. In one example, a portion of the perimeter tube forms a gate portion which is at least partially selectively deflated so as to be denser than water, and therefore rotates about a gate pivot such that the watercraft may enter the watercraft barrier through the gate portion. Also disclosed is a water pump in fluid communication with the watercraft barrier so as to evacuate water from between the watercraft barrier and the watercraft.

Abstract: An apparatus (100), having: an extension structure (200) configured to be secured to a base structure (400) and to define an extension structure roofline (204); and a side cover assembly (300) having a first portion (304) that is configured to be supported by the extension structure and a second portion (306) that is configured to protrude past the extension structure and thereby not be supported by the extension structure.

Abstract: A survival craft for maritime evacuation of passengers and crew members from a vessel or an offshore facility is disclosed. The survival craft has a hull, predominantly made of non-rigid inflatable tubes and one or more shells, the hull has a length, a width and a centerline, a bow and a stern. The survival craft further comprises a first pair of engine-powered propulsion means arranged at the stern on opposite sides of the centerline, and a second pair of engine-powered propulsion means arranged at the bow on opposite sides of the centerline, each engine-powered propulsion means has a propeller or a water jet, wherein a horizontal angle of each propeller or water jet of each engine-powered propulsion means can be independently set in relation to the centerline.

Abstract: A breathable mask including a breathing tube and a body is provided. The body is connected to the breathing tube so that an interior of the body is in fluid communication with an outside through the breathing tube. The body includes a main frame, a lens, a waterproof skirt, a purge valve and a mouthpiece. The waterproof skirt has a portion embedded in the main frame and a partition to divide the interior of the body into an upper chamber and a lower chamber. The purge valve is disposed at a lower portion of the body and in one-way fluid communication with the lower chamber. The mouthpiece disposed in the lower chamber has a first end and a second end opposite to the first end. The first end is contained in a mouth of the user and the second end is in fluid communication with the purge valve.

Abstract: A device for driving a primary shaft, the device including: a first system including an element for driving movement of a control member along a looped trajectory having two axial components; a second system including an element for pivoting the shaft about its longitudinal axis, actuated by the movement of the member along at least one component of the looped trajectory; a third system including an element for driving movement of the shaft, actuated by the movement of the control member along at least the other component of the looped trajectory, the control member projecting from the plane of the components and engaged with both the driving element for pivoting and for moving of the shaft, the movement of the control member along the looped trajectory generating a pivoting of the shaft in alternating directions and its movement in alternating directions.

Abstract: A canoe end cap that is configured to be secured to either the bow or stern of a canoe wherein a stern embodiment is further configured to have an outboard motor operably coupled thereto. The present invention includes a body wherein the body is manufactured from a durable rigid material. The body includes a top plate member having a first end and a second end wherein the width of the top plate member is greater proximate the first end. The top plate member includes a first lateral edge and a second lateral edge. A first side support member extends downward from the first lateral edge and a second side support member extends downward from the second lateral edge. First side support member and second side support member are adjacent to and parallel with opposing gunwales of the canoe. A motor mount assembly is configured to have a motor secured thereto.

Abstract: The present disclosure improves impact resistance of an electric outboard machine. The electric outboard machine includes an outboard machine body and an attachment. The attachment attaches the outboard machine body to a rear part of a boat. The outboard machine body includes a propeller, an electric motor that drives the propeller, and a controller that controls the motor. The controller is located between the motor and the attachment. If another boat collides with the boat from behind, the controller arranged between the motor and the attachment is easily protected from the impact upon rear-end collision. This can improve impact resistance of the electric outboard machine.

Abstract: A personal watercraft comprises a deck having coupled thereto a hull defining a bottom wall, a rear wall and a water intake extending from the bottom wall to the rear wall, and a jet propulsion system. The jet propulsion system comprises a housing coupled to the rear wall and defining an inlet to receive water from the water intake, a venturi, and an outlet to expel the water, and comprises a rim-driven motor disposed within the housing between the inlet and the venturi. The rim-driven motor defines a center axis and comprises a stator coupled to the housing, a rotor disposed radially inwardly of the stator relative to the center axis, and impeller blades coupled to the rotor and projecting towards the center axis, the rotor and the impeller blades rotatable about the center axis to draw the water via the inlet and expel the water via the outlet.

Abstract: A control handle for controlling an electric drive system of a sailboat is provided. The control handle comprises a handle and a handle shaft, where the control handle is provided with a plurality of engagement positions. A first engagement position is adapted to engage a forward drive mode of the electric drive system, a second engagement position is adapted to engage a reverse drive mode of the electric drive system, a third engagement position is adapted to engage an idle drive mode of the electric drive system, and a fourth engagement position is adapted to engage a hydro energy generation mode of the electric drive system.

Abstract: The invention relates to an energy supply system for a watercraft with a main energy converter that is configured for connection to an electrical system of the watercraft. According to invention, the main energy converter is connected to a DC busbar, and at least one inverter is connected to the DC busbar for supplying a consumer respectively associated with this inverter, and at least one electrical energy storage is connected to the DC busbar. Due to the common use of electrical components, among other things, a significant reduction of the installation space requirements of the energy supply system 100 is realizable for a watercraft.

Abstract: An inertia aerostat having a vacuum compartment and an inertial floating device provided in the vacuum compartment, the inertial floating device comprises a drive shaft, drive devices, recycle and power generation devices and axially symmetric EMD rotation bodies, fixing devices are respectively provided at both ends of the drive shaft, the fixing devices are connected with the vacuum compartment, the drive devices are sleeved over the drive shaft, the axially symmetric EMD rotation bodies are connected with the drive devices via wheel ribs, the recycle and power generation devices are sleeved over the drive devices; by providing the vacuum compartment and the inertial floating device, inertial centrifugal forces generated by high speed rotation of the axially symmetric EMD rotation bodies in a gravitational field can be used as conversion media between kinetic energy and gravitational potential energy so free floating of the aerostat in the gravitational field can be realized.

Abstract: An electrically operated window shade system includes a frame that is mounted on the outer side of the inner wall of an aircraft cabin. A cassette is mounted in the frame and includes one or more motors and drive systems and one or two shade elements that are moved between raised and lowered positions under electric control. A user can operated the electric controls to adjust the amount of light coming through the window, as desired.

Abstract: A wing-box structure for an aircraft is disclosed having an upper cover, a lower cover, longitudinal forward and rearward spars, and a plurality of transverse ribs. One of the transverse ribs is retained by a pair of opposed captive features disposed on an interior side of either the forward and rearward spars or the upper and lower covers. The rib is bonded rib to the forward and rearward spars and/or the upper and lower covers at a location where the rib is retained.

Abstract: A rotary wing aircraft has a nacelle, at least one rotor provided with at least one blade, a braking device to stop the rotation of the rotor, an emergency parachute provided with a canopy and with a rope, a rocket to start the extraction of the canopy from the nacelle, two operating devices to operate the braking device and the rocket, respectively, and a single actuator device to operate both the operating devices.

Abstract: An aerodynamic device includes a main aerodynamic body having a leading edge and a trailing edge, a flight control surface coupled to the main aerodynamic body near the trailing edge of the main aerodynamic body, and a rotating body coupled to the flight control surface. The rotating body is rotatable relative to the flight control surface between a stowed position and a deployed position to define a gap. The rotating body is rotated toward the main aerodynamic body while in the stowed position to close the gap. The rotating body is rotated away from the main aerodynamic body while in the deployed position to widen the gap. The gap adjusts an airflow flowing between the main aerodynamic body and the flight control surface.

Abstract: An aerodynamic device includes a main aerodynamic body having a leading edge and a trailing edge, a flight control surface coupled to the main aerodynamic body near the trailing edge of the main aerodynamic body, and a translating body coupled to the flight control surface. The translating body is moveable relative to the flight control surface between a sealed position and a retracted position to define a gap. The translating body is extended toward the main aerodynamic body while in the sealed position to close the gap. The translating body is retracted away from the main aerodynamic body while in the retracted position to widen the gap. The gap adjusts an airflow flowing between the main aerodynamic body and the flight control surface.

Abstract: A ram air turbine (RAT) assembly includes a turbine having at least one turbine blade that rotates about a turbine driveshaft, a lower gear box coupled to the driveshaft, a generator/pump housing and a strut connected between the lower gear box and the generator/pump housing. The assembly also includes a damping element connected to one of the strut and the lower gear box. The damping element includes an actuator including an extendable member and a mass element connected to the extendable member and that can be moved by the extendable member from a retracted position to an extended position, wherein the mass element is closer to the actuator when in the retracted position than when in the extended position.

Abstract: Apparatuses and systems are provided herein for unducted propulsion systems. The system includes a forward housing for high efficiency for high subsonic sustained flight. A plurality of blades are affixed to the forward housing, wherein the forward housing defines a flowpath curve extending from the forward-most end of the forward housing through the axial extent of a forward blade root. The flowpath curve is described by an axial direction parallel to an axis of rotation and a radius from the axis of rotation. The flowpath curve includes a first point having a first radius where the radius reaches a maximum forward of the forward blade root and a second point aft of the first point having a second radius where the radius stops decreasing. The ratio of the first radius to the second radius is greater than or equal to 1.029.

Abstract: A piloting device for piloting an aircraft includes a piloting member suitable for being actuated by a pilot, a mechanism for mounting and guiding in rotation the piloting member about at least one rotation axis with respect to a frame, at least one force sensor connected between the piloting member. The mechanism includes at least one sensing element configured to produce a signal upon deformation indicative of a force applied to the piloting member. The force sensor comprises at least one pair of bearing surfaces. The device also includes at least one pair of stops configured to limit the angular amplitude of rotation of the piloting member with respect to the frame on abutment of the at least one pair of bearing surfaces with at least one pair of stops. The stops or at least one of the bearing surfaces comprises a compliant material.

Abstract: A method for the control of a vertical take-off and landing (VTOL) aircraft which reduces the acoustic profile of the rotary airfoil in hover for VTOL applications. The rotary airfoil incurs an efficiency penalty in order to improve the acoustic performance during hover. The aircraft operates the rotary airfoils of the propeller during hover in the hover angle of attack range, and the aircraft operates the rotary airfoils during forward flight in the forward angle of attack range.

Abstract: Disclosed is an autopilot system for a helicopter, the helicopter having: a cyclic and a collective that are physically coupled to helicopter actuators that control cyclic and collective pitch of main rotor blades of the helicopter and anti-torque pedals that are physically coupled to helicopter actuators that control the pitch of tail rotor blades of the helicopter; and at least one servomechanism configured to amplify force applied by the pilot to the cyclic, collective and/or anti-torque pedals; wherein the autopilot system comprises an autopilot actuator configured to: in an autopilot mode, control direction or orientation of the helicopter by applying force to a control link that is physically coupled to one of the helicopter actuators; and in a manual mode, provide stability or control augmentation by applying a force on one of the cyclic, the collective or one or both of the anti-torque pedals to influence the pilot's inputs to urge the helicopter away from a particular flight condition dependent on mo

Abstract: A no-back brake includes a torque tube and a brake. The brake is configured to be axially displaced in response to a force to prevent the torque tube from rotating. The brake includes a rotor that is concentric with the torque tube and that is fixed to the torque tube so that the rotor rotates with the torque tube. The brake includes a stator that is concentrically mounted on the torque tube so that the torque tube is rotatable relative to the stator. The brake includes a friction device located between the rotor and the stator. The friction device is configured to form a frictional coupling between the rotor and the stator that opposes relative rotational motion between the rotor and the stator when the brake is axially displaced. The frictional device includes a composite material.

Abstract: A system includes an electrically-actuated clutch arranged to selectively connect a shaft to a motor shaft. Ratchets brake the shaft against rotation in either direction when the output is not within either of the predetermined ranges. Thus, when the motor shaft is connected, via the clutch, to the shaft, the ratchets may act as a brake on the motor shaft.

Abstract: A first Flight Control system configuration, and the method to obtain such first configuration, has controllers of effector actuation able to receive commands directly from at least three Flight Control Computers (FCCs). A second Flight Control system configuration, and the method to obtain such second configuration, has retransmitters (RTX) that receive commands from the three FCCs and then retransmit to the controllers of effector actuation. A third Flight Control system configuration, and the method to obtain such third configuration, is a hybrid configuration.

Abstract: A monocopter includes a housing and a propeller connected to a shaft. The shaft is connected to a main motor that is fixed to the housing (e.g., mounted within the housing) such that upon operation of the main motor, the shaft rotates and the propeller rotates. A first counterweight is interfaced to a shaft of a first motor that is interfaced to the housing and a second counterweight is interfaced to a shaft of a second motor that is also interfaced to the housing such that the shaft of the first motor is in a plane that is perpendicular to the shaft of the second motor (e.g., the shafts are at right angles to each other). The main motor, the first motor and the second motor are controlled (e.g., using artificial intelligence) to enable stable flight of the monocopter.

Abstract: Embodiments disclosed herein relate to electroaerodynamic (EAD) thrusters for use in thrust generation. An EAD thruster may include one or more ion sources, one or more ion collectors, and one or more airfoils. In some embodiments, the one or more of the one or more ion sources and/or ion collectors may be integrated into a surface of the one or more airfoils. The EAD thruster arrangement may also include multiple EAD stages in some embodiments.

Abstract: A landing gear including an outer cylinder, a shock strut assembly, and a passive shrink mechanism. The outer cylinder is coupled to a frame of an aircraft about a trunnion axis of rotation. The shock strut assembly is coupled to the outer cylinder for reciprocation along a longitudinal axis of the outer cylinder. The passive shrink mechanism includes: a first shrink link member coupled to the outer cylinder, a second shrink link member coupling the first shrink link member to the shock strut assembly, a crank member coupled to the outer cylinder, a first connecting link coupling the crank member to a walking beam of a landing gear retract mechanism, and a second connecting link coupling the crank member to the first shrink link member. The passive shrink mechanism is passively extended and shortened through actuation of the landing gear retract mechanism with deployment and retraction of the landing gear.

Abstract: A landing gear actuation system is disclosed herein. The landing gear actuation system includes an attachment point integral to a movable member, a flexible pull member having a first end coupled to the attachment point, and a motor configured to move the flexible pull member, wherein the movement of the flexible pull member moves the attachment point and the movable member.

Abstract: Disclosed is a ground movement system for a helicopter having a fuselage and rotor blades fixed to the top of the fuselage, the ground movement system comprising at least three wheels secured below the fuselage of the helicopter, the wheels being retractable during flight; a motor positioned in the hub or on the undercarriage leg of each of at least two of the wheels, wherein each motor is operable to rotate the wheel in forward and backward directions; wherein each motor allows the wheel to rotate freely when unpowered; at least one user interface operable to receive user input commands to control the speed and direction of travel of the helicopter using the ground movement system; and a control arrangement to provide control signals to each of the motors based on the user input commands.

Abstract: Disclosed is an electrically powered, reaction-drive type rotorcraft. Thrust generators on the outer portion of each rotor blade cause the rotors to spin and generate lift, and additionally, may be controlled to produce variable amounts of thrust as the rotor blades rotate through different sectors around a generally non-rotating fuselage such that net lateral forces are produced to control the position and velocity of the vehicle. The rotorcraft may also employ aerodynamic surfaces on each rotor blade whose parts or entire structure can be moved to produce net lateral and vertical forces for control of position and velocity of the vehicle. The rotorcraft, which may be operationally carbon-neutral, stores its electrical energy in batteries and other optional energy storage methods, and may harvest solar energy using arrays of photovoltaic cells disposed on its upper surfaces. Vehicle sizes may range from small Uncrewed Air vehicle Systems to large crewed aircraft.

Abstract: A rotary wing aircraft includes a single main rotor hub configured to receive a rotor blade. The rotor blade includes a blade root, a blade tip, and a blade body. The blade body includes a leading edge and a trailing edge and defines a feathering axis. The leading edge and the trailing edge each include a first portion and a second portion that extend toward a first direction and a second portion, respectively. At a given radial location along the feathering axis, a local twist angle changes from a positive value to a negative value, a chord length decreases in value, a distance between the trailing edge and the feathering axis decreases in value, and the first portion of the leading edge extends toward the first direction. The rotor blade assembly also includes a trailing edge assembly having a trailing edge flap configured to be selectively deployed by an actuator.

Abstract: A rotor blade assembly for a rotary wing aircraft includes a main rotor blade body comprising an upper blade skin, a lower blade skin, an inboard end, an outboard end, and a trailing edge. The rotor blade assembly further includes a trailing edge actuator assembly. The trailing edge actuator assembly includes an upper actuator skin and a lower actuator skin defining a cavity and a trailing edge flap, a control panel disposed in the cavity and coupled to one of the upper actuator skin or the lower actuator skin and one or more actuators disposed in the cavity and configured to apply force to the control panel to cause the trailing edge flap to deflect. The trailing edge actuator assembly is coupled to the trailing edge of the main rotor blade body.

Abstract: A coaxial rotor system includes a center mast non-rotatably disposed at and extending from a helicopter. A rotation axis extends along the center mast. An inner mast is disposed along the center mast and is rotatable about the rotation axis in a first direction. A portion of the inner mast extends above an end of the center mast. An outer mast circumscribes the center mast and is rotatable about the rotation axis in an opposite second direction. The center mast extends above an end of the outer mast. An upper rotor blade assembly is rotatable with the inner mast. A lower rotor blade assembly is rotatable with the outer mast. A control system disposed at the center mast between the upper and lower rotor blade assemblies is operable to adjust pitch of a plurality of upper rotor blades and to adjust pitch of a plurality of lower rotor blades.

Abstract: An aircraft capable of VTOL and forward flight is fitted with a side body articulating propulsion system on the port and starboard sides of the fuselage. The side body articulating propulsion system has plural sets of port and starboard propulsor units controlled for synchronized rotation. The propulsor sets are supported in a triangular airframe designed to support the propulsor units equally spaced apart from one another along a propulsor slope that is angled about 30-60 degrees from horizontal. Synchronized rotation of the propulsor sets is accomplished by an articulation controller, which may be a parallelogram linkage and linear actuator. A port nacelle surrounds the port propulsor units and a starboard nacelle surrounds the starboard propulsor units. A cargo cavity is accessed through the aft end of the airframe. The airframe can be lengthened in the fore direction by attaching an ante-module and/or in the aft direction by an expansion module.

Abstract: According to at least one exemplary embodiment, a method, system and apparatus for an aircraft may be shown and described. An exemplary embodiment may be an autonomous aircraft which can vertically takeoff and land (VTOL). The VTOL aircraft may have a modular pod which carries a removable payload. The entire VTOL aircraft may be portable. An exemplary embodiment may fit into a standard sized freight container. A propulsion system may be based on distributed electric propulsion. An exemplary embodiment may implement variable pitch propellers and collective pitch variation.

Abstract: An aerial vehicle is programmed or configured to respond to reports of events or conditions within spaces of a facility. The aerial vehicle travels to a location of a reported event or condition and captures data using onboard sensors. The aerial vehicle independently determines whether the reported event or condition is occurring, or is otherwise properly addressed by resources that are available at the location, using images or other data captured by the onboard sensors. Alternatively, the aerial vehicle transmits a request for additional resources to be provided at the location, where necessary. A map of the location generated based on images or other data captured by the onboard sensors may be utilized for any purpose, such as to make one or more recommendations of products that are appropriate for use at the facility.

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: A response system may be provided. The response system may include an autonomous drone. The drone may include a processor, a memory in communication with the processor, and a drone sensor. The processor may be programmed to receive the deployment request from a security system, navigate to the one or more zones of the coverage area included in the deployment request, collect drone sensor data of the one or more zones of the coverage area using the at least one drone sensor, determine that an incident has occurred, and/or transmit the collected drone sensor data and incident verification to the security system, wherein, in response to receiving the collected drone sensor data and incident verification, the security system is configured to generate a command for responding to the incident.

Abstract: A blended wing body aircraft includes a body section having an aerodynamic lifting surface. The body section includes an upper body and a lower body. The blended wing body aircraft also includes a plurality of blended wing sections further defining the body section. The blended wing body aircraft includes one or more grooves in the body section. The one or more grooves extend from the upper body towards the lower body. The blended wing body aircraft further includes one or more open-fan engines mounted at least partially within the one or more grooves. The one or more open-fan engines ingest a portion of a boundary layer of the blended wing body aircraft.

Abstract: There is provided a flight vehicle including: a wing unit; a battery that is arranged in the wing unit; an air intake unit that is formed at a position corresponding to the battery on a front side of the wing unit; a heat sink unit that is arranged for the battery and cools the battery by air which flows in from the air intake unit and that includes a ventilation unit having a shape widening from the front side toward a rear side; and an exhaust unit that is formed at a position corresponding to the battery on the rear side of the wing unit and that exhausts air which flows out from the heat sink unit.

Abstract: An aeronautical conveying and release device, actuated by a cartridge, includes a housing provided in a body having a recess having an open end and a bottom, a cartridge adapter configured to close the recess and forming a chamber capable of housing the cartridge, an indicator movably mounted between first and second positions. The cartridge adapter includes a bolt configured to be screwed into the housing so that in the presence of the cartridge, the bolt can be screwed to a first depth where the bolt abuts against the cartridge, the cartridge being in abutment against the bottom of the recess, and in the absence of a cartridge, the bolt can be screwed to a second depth, greater than the first, and the bolt at the first depth prohibits the first position for the indicator, while the bolt at the second depth leaves the indicator free to move.

Abstract: A payload coupling apparatus is provided including a housing, wherein the housing is adapted for attachment to a first end of a tether, a slot extending downwardly from an outer surface of the housing towards a center of the housing thereby forming a lower lip on the housing beneath the slot, and wherein the slot is adapted to receive a handle of a payload.

Abstract: An aircraft including a support structure, an outer skin connected to the support structure, a first port extending through the outer skin and defining a first break in the support structure. The aircraft also includes a first receptacle attached to the support structure proximate the first port and defining a first opening, a ball-mounted sensor assembly received in the first receptacle and extending downward from the outer skin, a second port extending through the outer skin and defining a second break in the support structure, a second receptacle attached to the support structure proximate the second port and defining a second opening. A method of retrofitting an aircraft to accommodate a ball-mounted sensor assembly and a payload is also disclosed.

Abstract: A tie down for a cargo handling system may comprise a carriage. the carriage may include a first sidewall surface, a second sidewall surface opposite the first sidewall surface, a first surface extending from the first sidewall surface to the second sidewall surface, and a second surface opposite the first surface. A first rail interface pin may be configured to extend from the first sidewall surface. A second rail interface pin may be configured to extend from the second sidewall surface. A seat fitting channel may be formed in the carriage and may extend between the first sidewall surface and the second sidewall surface.

Abstract: A passenger seat and a row of passenger seats of a type wherein each seat includes a seatback for locating amenities for use by an aft-seated passenger. The seatback includes a video monitor positioned in an upper portion of the seatback, a first seatback pocket positioned below the video monitor, and a second seatback pocket positioned below the first seatback pocket. Each of the first and second seatback pockets includes a member configured to move apart from the seatback to facilitate access to a bottom of the respective seatback pocket. In embodiments, the first and second seatback pockets are positioned in respective first and second recesses formed in the seatback.