Abstract: A system for adjusting the damper force on the suspension system of a bicycle is provided. Sensors are placed on the front shock and rear shock to measure the amplitude of displacement or acceleration in the time domain and generate a zenith position, velocity, force, and work based on the measured values. The system calculates a curve fit approximation curve for the relationships of zenith position versus velocity and uses the approximation curves to generate and display recommended damper settings for the front shock and rear shock. Using the data ensures that the bicycle suspension data is balanced, such that the front shock and rear shock respond similarly to the same event.

Abstract: A balancing vehicle includes a wheel, a bracket, a frame, a shock absorbing member, pedals, a control rod, and a handle. The bracket is fixed to an axle of the wheel. The frame is slidably connected to the bracket through a slider fixedly connected to the bracket, so as to allow the frame to slide relative to the bracket. The shock absorbing member is disposed between the frame and the bracket, and is configured to cushion relative movement between the frame and the bracket. The pedals are fixed to the frame. The control rod is configured to move back and forth in a direction of travel. The balancing vehicle accelerates when the control rod is pushed forward in the traveling direction, and the balancing vehicle decelerates or retreats when the control rod is pulled backward in the traveling direction. The handle is coupled to a top of the control rod.

Abstract: A tube for a bicycle has a body, an indented portion, and a machined hole. The indented portion is radially recessed in the body and has an outer bottom surface, an outer annular surface, and a first round corner being a curved surface smoothly connecting an outer tube surface of the body and the outer annular surface. The machined hole is formed through the outer bottom surface of the indented portion and has an area being less than an area of the outer bottom surface. The indented portion formed around the machined hole distributes stress to prevent cracking occurring from an edge of the machined hole. The structural strength of the tube is increased under a same total weight.

Abstract: A pivot assembly for a cycle linkage suspension is provided that includes first and second members and a pivot. The first and second members include lateral openings extending therethrough and the pivot includes a rod portion that is configured to be disposed within the lateral openings to pivotably couple the first and second members together. The rod portion further includes an opening that extends through an intermediate portion thereof. The pivot assembly can further include a pin configured to be removably inserted at least partially into the opening in the rod portion to thereby restrict lateral movement of the rod portion within the first and second members.

Abstract: A brake module is provided. The brake module includes a first brake lever, a second brake lever, a moveable member, a first cable, a second cable, a first brake unit, a second brake unit, a third cable and a fourth cable. The first cable connects the first brake lever and the moveable member. The second cable connects the second brake lever and the moveable member. The third cable connects the first brake unit and the moveable member. The fourth cable connects the second brake unit and the moveable member. When a lever force is applied to the first cable or the second cable, the third cable applies a first brake force to the first brake unit, the fourth cable applies a second brake force to the second brake unit, and the lever force is smaller than the sum of the first brake force and the second brake force.

Abstract: A control device includes an electronic controller configured to control a transmission device of a human-powered vehicle in accordance with a shifting condition. The electronic controller is configured to monitor a torque applied to the human-powered vehicle upon determining the human-powered vehicle is ridden and driven. The electronic controller is configured to permit a shifting operation of the transmission device in accordance with a peak value of the torque upon determining the shifting condition is satisfied.

Abstract: A bicycle gearshift is operated by imposing on the chain guide a primary displacement in the axial direction with respect to a cogset, to move the chain between the sprockets. Simultaneously with imposing on the primary displacement imposing on the chain guide a secondary displacement in the radial direction with respect to the cogset. The secondary displacement is of a greater size when the primary displacement takes place in the area of the cogset with the larger sprockets whereas it is of a smaller size when the primary displacement takes place in the area of the cogset with the smaller sprockets.

Abstract: A rotation calculating system, comprising: a first optical characteristic acquiring device, configured to acquire optical characteristics for at least one feature of a first target device; and a calculating unit, configured to calculate rotation for a first rotating device based on the optical characteristics of the feature of the first target device. The first rotating device is a wheel, and the first target device is the wheel.

Abstract: A boat includes at least three trim devices positioned aft of the boat's transom. To improve the boat's ability to get on place, each trim device is initially positioned to a deployed position. The speed of the boat is then determined as the boat gains speed. When the speed of the boat exceeds a first predetermined threshold, the first trim device is moved from the deployed position to a non-deployed position. When the speed of the boat exceeds a second predetermined threshold, the second trim device is moved from the deployed position to a non-deployed position. When the speed of the boat exceeds a third predetermined threshold, the third trim device is moved from the deployed position to a non-deployed position. At least one of the first, second, and third predetermined thresholds is different from the other two of the first, second, and third predetermined thresholds.

Abstract: Apparatus and associated methods relate to using an additive (material deposition) process to incrementally form a closed-cell lattice structure formed as a unitary body in the shape of a marine hull cavity, the unit cells of the closed-cell lattice structure are substantially hollow. In an illustrative example, a method may include (a) forming a closed-cell lattice structure through additive manufacture, the hull cavity material may be bonded to an upper manufactured liner and a lower manufactured liner through lamination or mechanical connection. Unit cells of the closed-cell lattice structure may include hollow voids filled with gases. Providing the additive manufactured closed-cell lattice structure with a unitary body and hollow voids to trap gases may further advantageously promote the buoyancy and reduce the degeneration of a marine hull.

Abstract: Systems and methods are provided for a magnetic coupling shade system for boats. The magnetic coupling shade system comprises a sheet of material that includes magnetic portions coupled with magnets disposed in locations of a boat. The locations of the boat include any of the hull, deck, superstructure, hardtop, or any other suitable surface of the boat. Magnets located on the hull are located within the interior of the hull. The sheet extends from the top to either or both of the port and starboard sides. The sheet can comprise a variety of materials, and may include a window portion for viewing through the sheet. In some embodiments, the window portion comprises an entirety of the sheet with the magnetic portions attached to opposite edges of the window portion. The sheet is configured to be detached from the magnets and either suspended overhead or rolled upward when not in use.

Abstract: A bimini top includes a top member displaceable between an expanded position and a retracted position, a securing panel connected to the top member, and a cover member sized to fit over the top member with the top member in the retracted position. The cover member is contained by the securing panel when not in use.

Abstract: A pole-less cover assembly includes a cover member positionable over a structure and formed of an essentially impermeable material, and an integrated gutter system including a material section coupled with the cover member and formed of a porous material and a gutter disposed below the material section. Among other advantages, the pole-less cover assembly eliminates conventional tent poles required for existing boat covers, thereby reducing cost and facilitating installation.

Abstract: A lateral arm actuator for an extendable awning includes a gas spring with a cylinder and a rod that is displaceable relative to the cylinder, a fitting disposed at a distal end of the rod, and an awning knuckle including a first connector coupled to a cylinder end of the gas spring, a second connector, and a pivot coupled between the first and second connectors. The second connector is pivotable relative to the first connector, and the second connector includes a hook. A cable formed into a continuous loop is positioned over the fitting, along the gas spring, and across the awning knuckle engaging the hook. An extendable awning assembly also incorporates the lateral arm actuator to extend and retract the awning via a motorized roller.

Abstract: A marine array having various embodiments of a modular foil system is disclosed. The modular foil system may be configured to generate lift when towed in a marine environment, and thus used to move, position, and/or depress instrument of the array. The modular foil system may include multiple groups of foil sections, each having an angle of attack that is adjustable relative to other groups of foil sections. For example, each group may be supported by a pair of through cables, and an actuator may adjust a tension in one or both of through cables, thereby alerting the angle of attack. The pair of through cables may converge toward one another at connection points adjacent opposing ends of a given group of foil sections of the modular system. The connection points thus establishing a modular framework to couple the given group to other groups of foils of the system.

Abstract: Boat transfer system (10;110) on a floating vessel (30), comprising at least one deployment frame (14;114) for deployment of a cradle (12), wherein said deployment frame (14;114) is movable in a mainly horizontal direction and the deployment frame (14;114) is equipped with upright guides (18;118) for vertical movement of the cradle (12), and said cradle (12) is connected to a guide system (22;130,132,134) for controlled movement of the cradle (12) in the upright guides (18;118).

Abstract: Device designed to retrofit a marine propulsion system from an old shift interrupt control strategy with a new shift interrupt control strategy to improve shifting performance, reliability, and ease of use. Can also be used on new systems.

Abstract: A life raft system including a life raft assembly including a mounting bracket having a base and an awning, an upper lateral support having a latching mechanism and deployment cable, a lower lateral support comprising a hinge-member, a self-inflatable raft having a housing, an inflator, an inflator cable, and a raft securing cable, and a cover chute. The life raft system is a residential and commercial life saving device for urban and rural area homes as well as commercial building structures that could be at risk to rising flood waters. The device may be mounted to a structure such as a home or building as a precaution. The device provides a family or group of people with the ability to flee to higher ground when disaster occurs, preventing loss of life and offering a safe exit from an affected area.

Abstract: A system for controlling a marine vessel comprises an input device for inputting an operator command, a sensor which senses and signals an engine function variable or a vessel dynamic variable, and a first structural element and a second structural element. The first structural element and the second structural element each control speed or direction of motion of the marine vessel, and the first structural element and the second structural element each affect the marine vessel dynamic variable. There is a controller which receives the operator command and the engine function variable or the vessel dynamic variable. The controller moves the first structural element and the second structural element based on the engine function variable or the vessel dynamic variable, after receiving the single operator command.

Abstract: An airship dynamic adaptive harness is provided to stabilize airships and particularly a tethered aerostat in high winds and atmospheric changes. A novel adaptive device accommodates the supply of a lift gas and simultaneously controls opposing cables in a tethered harness with a cascade control system that provides an immediate and particularly the dynamic control of roll, yaw and particularly the pitch of the aerostat in response to real time environmental flight conditions and impart stability to the airship in high winds using a stability zone geometric suspension control system and enhance the duration of in flight missions. A lifting gas replenishment system and particularly a ground based lifting gas replenishment system adds long duration deployment to the dynamic adaptability to high wind conditions for long term deployment.

Abstract: In an example, a structural frame is described. The structural frame includes a hub and a plurality of truss members. The hub includes a plurality of hub slots around a perimeter of the hub. The plurality of truss members are configured to couple with the hub and each other. Each truss member is a monolithic structure including: (i) a body extending from a first end of the truss member to a second end of the truss member, (ii) a truss fastener at the first end and configured to couple with a respective one of the plurality of the hub slots of the hub, (iii) a truss slot at the second end and configured to couple to the truss fastener of another one of the plurality of truss members, and (iv) one or more retainers extending along the body between the first end and the second end.

Abstract: A frame (1) for fuselage shells of an aircraft, the fuselage comprising a skin (3) and stringers (4), the frame (1) including: a plurality of sections (5), the sections (5) being separated by intermediate gaps corresponding to the position of the stringers (4) in the fuselage, each section (5) having a multi-cell configuration constituted by several modular elements (6) of composite material arranged in longitudinal direction, and a continuous inner cap (7) on top of the sections (5) and the intermediate gaps.

Abstract: An aircraft windshield wiper control system includes an aircraft weather radar system mounted in an aircraft and that detects precipitation in a travel path of an aircraft and an integrated avionics module that receives aircraft weather information from the aircraft weather radar system. The system also includes an aircraft wiper blade motor, a wiper blade motor driver and a wiper control module that receives aircraft weather information from the integrated avionics module and generates a wiper control signal, based on the received information that controls operation of the wiper blade motor drive to cause motion of the aircraft wiper blade motor.

Abstract: A privacy door assembly for installation in an aircraft relative to a flight deck door of the aircraft includes a door frame having a first post and a second post, where the second post comprises a latch recess. The privacy door comprises a latch positioned on an edge of the privacy door and arranged to engage the latch recess when the privacy door is in a closed position within the door frame. An access door is positioned in the privacy door, where the access door is rotatable from a closed position to an open position in a forward direction. A first mechanical door handle system including a mechanical combination lock is positioned on an aft side of the privacy door and coupled to the latch, and a second mechanical door handle system is positioned on a forward side of the privacy door and coupled to the latch.

Abstract: An aircraft includes an aircraft body including a longitudinal axis and a wing box extending through the aircraft body. The aircraft also includes an attachment assembly coupled to the aircraft body and to the wing box. The attachment assembly includes a first attachment member coupled to the aircraft body and a second attachment member coupled to the wing box. The second attachment member is configured to couple to the first attachment member. The attachment assembly also includes a plurality of fasteners extending through the first attachment member and the second attachment member such that the plurality of fasteners are loaded in shear during a wing loading condition.

Abstract: An aircraft (1) has at least one main wing (2) and at least one boom fuselage (3). The main wing has an aerofoil section having a leading edge (20), a trailing edge (21), a chord length extending between the leading edge and the trailing edge, a centre of lift (Lw), a flexural centre and a centre of mass. The centre of lift, the flexural centre and the centre of mass are located all within a region at most 4% of the chord length.

Abstract: A section of an aircraft wing including a leading edge of the aircraft wing. A leading edge part of the section includes ribs; and a skin fixedly attached to the ribs to form a spanwise series of adjacent cells. Each cell includes an enclosed volume bounded by the skin at the leading edge and a pair of the ribs. At least one cell of the series of adjacent cells is a dry cell include a mounting point for mounting a leading edge high-lift device support apparatus in the dry cell. The skin at the leading edge provides a primary load path for carrying at least some of a spanwise primary load experienced by the section when in use on an aircraft.

Abstract: A spar assembly for an aircraft wing extends between an upper cover and a lower cover and includes linkages spaced consecutively along the length of the spar assembly, each linkage extending from an upper pivot, to a lower pivot, thereby joining upper and lower attachment structures of the spar assembly together. Each linkage includes a pair of fixed-length links pivotably connected at one end about a center pivot and pivotably connected at respective other ends. The spar assembly includes a drive bar connected to the center pivot of each of the linkages, and an actuator arranged to move the drive bar along the length of the spar assembly. When the actuator moves the drive bar along the length of the spar structure, the links in each pair of links are rotated relative to each other about the center pivot, thereby moving the upper and lower covers and warping the wing.

Abstract: An aircraft component includes a main body and at least one lug extending from the main body. The lug is formed of a composite component, a sleeve, and a filler component. The sleeve has a through hole extending along a longitudinal axis. The composite component includes continuous fibers embedded in a matrix. The sleeve is at a distance from the main body. The composite component extends from the main body around at least a section of the outer circumferential surface of the sleeve and back to the main body. The continuous fibers of the composite component extend from the main body around the section of the outer circumferential surface of the sleeve and back to the main body. An intermediate space is between the sleeve and the main body and is delimited by the sleeve and the composite component. The filler component is within the intermediate space.

Abstract: A low-noise multi-propeller system includes at least two propellers, each propeller including at least two blades. The propellers rotate in a first direction and define an angular phase relative to one another. A drive system corotates the propellers at substantially equal rotational rates in the first direction. The propellers are substantially phase-locked at a predefined relative phase offset that reduces the overall sound power of the fundamental tone at a blade passage frequency.

Abstract: An UAV according to an embodiment may include housing, a tactile sensor disposed on at least a partial surface of the housing, at least one motor, a propeller connected the at least one motor, and a processor electrically connected to the tactile sensor and the at least one motor and controlling the at least one motor. Moreover, various embodiment grasped through the disclosure are possible.

Abstract: There is disclosed an engine assembly, including an internal combustion engine having a housing and a coolant circuitry in heat exchange relationship with the housing. A porous surface is configured for defining a portion of an external surface of an aircraft. Apertures are defined through the porous surface. The housing of the internal combustion engine is in heat exchange relationship with the porous surface for heating the porous surface. An air conduit has an inlet fluidly connected to a boundary layer region outside the engine assembly and adjacent the porous surface via the apertures of the porous surface. The air conduit is in heat exchange relationship with the coolant circuitry. A forced air system is fluidly connected to the inlet of the air conduit and is operable to draw an airflow from the inlet and inside the air conduit. A method of operating the engine assembly is disclosed.

Abstract: The skin grooves provide a methodology in directing the flow of fluid on multiple types of vehicles and objects. The grooves within the skin allow the fluid to be directed. The grooves work similarly to a water slide. The groove within the water slide directs the water accordingly. By utilizing the same method of directing the flow of fluid on an aircraft, landcraft, spacecraft, and watercraft related vehicles or propelled/projectile objects, it provides limitations to drag.

Abstract: A landing gear system includes a landing gear collar and a strut assembly supported by the landing gear collar. The strut assembly includes a piston that is adjustable between a fully extended position and a fully compress position. The landing gear system further includes a rotary encoder and a controller. The rotary encoder rotates in response adjusting the piston and to outputs a data value in response to its rotation. The controller is in signal communication with the rotary encoder and determines a stroke of the piston based on the data value output from the rotary encoder.

Abstract: An aircraft motor includes a bearing assembly including a first plurality of rotor alignment magnets; a magnet support structure fixedly mounted on a shaft of the motor in a spaced apart relation to the bearing assembly, the magnet support structure including a second plurality of rotor alignment magnets such that when the vertical thrust engine is disengaged, attraction between the first and second rotor alignment magnets causes the magnet support structure to rotate relative to the bearing assembly to an alignment position defined by the relative placement of north and south poles of the first and second plurality of rotor alignment magnets.

Abstract: Provided is a quiet redundant urban rotorcraft, commonly known as urban air mobility eVTOL. The quiet redundant urban rotorcraft is designed to perform vertical takeoff and landings powered by two independent electric lifting motors. The lifting force is distributed among counter-rotating, co-axial main multi-bladed rotors and several smaller rotors distributed around the vehicle which provide attitude control during hover and low speed flight. The quiet redundant urban rotorcraft is capable to fly at relatively high horizontal speed by using a dedicated horizontal thrust propeller driven by an electric motor, turbine or internal combustion engine. In high speed flight, the main rotors turn freely, the control electric motors turn off and the attitude control is provided by aerodynamic fixed and moving surfaces. The quiet redundant urban rotorcraft has a low noise footprint and multiple redundancy for safety, while at the same time having a compact configuration for operating area restrictions.

Abstract: A ducted fan drone has a plurality of bent tube propulsors that enshroud rotating fan blades in a manner the eliminates contact with the blades during operation, thereby allowing drone operation in confined areas without risk of injury to people, animals, objects, or the drone itself by incidental contact with the rotating fan blades. The bent tube propulsors have an air passage, an air inlet into the air passage, and an air exit out of the air passage. The air passage has an upwardly bent portion relative to a longitudinal axis of the ducted fan drone, a downwardly bent portion relative to the longitudinal axis, and horizontal section extending between the upwardly and downwardly bent portions. A fan propulsor is disposed within the air passage of each bent tube propulsor at a position along the horizontal section.

Abstract: An aircraft has an airframe including first and second wings with first and second pylons extending therebetween forming a closed wing. A distributed propulsion system attached to the airframe includes a plurality of propulsion assemblies that are independently controlled by a flight control system. A pod assembly is coupled to the airframe such that, in a VTOL flight mode, the first wing and at least two of the propulsion assemblies are forward of the pod assembly, the second wing and at least two of the propulsion assemblies are aft of the pod assembly and the pylons are lateral of the pod assembly. In addition, in a forward flight mode, the first wing and at least two of the propulsion assemblies are below the pod assembly, the second wing and at least two of the propulsion assemblies are above the pod assembly and the pylons are lateral of the pod assembly.

Abstract: A counter-attack unmanned aerial vehicle (UAV), for aerial neutralization of a detected target aerial vehicle, comprises a flight body and a flight control system to intercept the detected target aerial vehicle, and comprises an aerial vehicle capture countermeasure (e.g., a net) operable to capture the detected target aerial vehicle. The aerial vehicle capture countermeasure can comprise a net deployable from the counter-attack UAV, and a captured target aerial vehicle can be delivered to a particular location. A system for aerial neutralization of a detected target aerial vehicle comprises an aerial vehicle detection system comprising at least one detection sensor operable to detect the target aerial vehicle, and operable to provide command data (including location data) to at least one counter-attack UAV for neutralization of the target aerial vehicle. The counter-attack UAV and systems may be autonomously operated. Associated systems and methods are provided.

Abstract: A system for neutralization of a target aerial vehicle comprises one or more counter-attack unmanned aerial vehicles (UAVs) and an aerial vehicle capture countermeasure tethering the counter-attack UAV(s) to a structure or ground. The counter-attack UAV(s) are operable to capture and neutralize the target aerial vehicle with the aerial vehicle capture countermeasure (e.g., a net). The system can comprise an on-board aerial vehicle detection system, and/or an external aerial vehicle detection system each having at least one sensor configured to detect the target aerial vehicle while in flight. The counter-attack UAV(s) and the associated detection systems may be autonomously operated for detecting and neutralizing a target aerial vehicle. The aerial vehicle capture countermeasure can be moved from a stowed position to a deployed position in response to coordinated flight of the counter-attack UAV(s). Associated methods and systems are provided.

Abstract: A system for detecting and neutralizing a target aerial vehicle comprises a counter-attack unmanned aerial vehicle (UAV) comprising a flight body and a flight control system supported about the flight body operable to facilitate flight of the UAV, and an aerial vehicle countermeasure supported by the flight body. The system can comprise an aerial vehicle detection system comprising at least one detection sensor operable to detect a target aerial vehicle while in-flight, and operable to provide command data to the counter-attack UAV to facilitate interception of the target aerial vehicle by the counter-attack UAV. Upon interception of the target aerial vehicle, the counter-attack UAV is operable to disrupt operation of the detected target aerial vehicle with the aerial vehicle capture countermeasure, thereby neutralizing the target aerial vehicle. The counter-attack UAV and systems may be autonomously operated. Associated systems and methods are provided.

Abstract: A system for neutralizing target aerial vehicles comprises a projectile launching mechanism that launches a projectile that supports a counter-attack unmanned aerial vehicle (UAV) having an aerial vehicle countermeasure. The counter-attack UAV can be folded in the projectile, and operable to unfold when separated from the projectile. The system comprises an aerial vehicle detection system comprising a detection sensor that detects a target aerial vehicle. Upon detection, the projectile launching mechanisms launches the projectile, and the counter-attack UAV is thereafter separated from the projectile to operate in flight to neutralize the detected target aerial vehicle with the aerial vehicle countermeasure. The projectile launching mechanism can comprise a movable platform comprising a plurality of projectiles and counter-attack UAVs, and can comprise a detection sensor to detect target aerial vehicles.

Abstract: A system for aerial neutralization of a detected target aerial vehicle comprises a plurality of counter-attack unmanned aerial vehicles (UAVs), and an aerial vehicle capture countermeasure coupling together the plurality of counter-attack UAVs, to intercept and capture a detected target aerial vehicle in a coordinated manner. The system comprises an aerial vehicle detection system comprising at least one detection sensor operable to detect the target aerial vehicle, and operable to provide command data to at least one counter-attack UAV for tracking and neutralizing the target aerial vehicle. The counter-attack UAVs and a net can be deployed from a movable base station, and the net can be carried in a low-drag configuration until the counter-attack UAVs operate to deploy or open the net. The counter-attack UAVs and systems may be autonomously operated. Associated systems and methods are provided.

Abstract: An aircraft based object acquisition system includes an airframe capable of flight. The system includes one or more sensors configured to identify a physical characteristic of an object or an environment. An object acquisition mechanism is coupled to the airframe and configured to manipulate and secure the object to the airframe. A ground based movement system may be configured to position the airframe such that the object is accessible to the object acquisition mechanism. A processor is communicatively configured to control operation of the ground based movement system to approach the object based at least in part on information from the one or more sensors, and to control the object acquisition mechanism to pick up the object based at least in part on information from the one or more sensors.

Abstract: Disclosed is a drone configured for multiple uses. The drone may include a body and a sensor configured to be attached to the body. Further, the drone may include a plurality of arms configured to be attached to the body. Further, a first end of an arm of the plurality of arms may be attached to the body at a first movable joint. Further, the arm may include a first part connected to the first movable joint. Further, the arm may include a second part attached to the first part at a second movable joint. Further, the arm may include a powered rotor including a shaft configured to provide rotatory motion. Further, the powered rotor may be attached to one or more of the first part and the second part. Further, the drone may include a plurality of propeller blades attached to the shaft.

Abstract: An unmanned aerial vehicle (“UAV”) includes an aircraft body and a rotor assembly mounted on the aircraft body. The UAV also includes a barometer disposed external to the aircraft body and separated from the rotor assembly at a predetermined distance.

Abstract: The present technology is directed to a remotely controlled aircraft that can be transported without the risk of damaging certain components, such as the arms and/or propellers. In one non-limiting example, the remotely controlled aircraft technology described herein provides a housing that allows the arms of the remotely controlled aircraft to extend and/or retract through openings in the housing. When retracted, the arms and propellers are protected within an area of the structure of the housing, and when extended, the arms and propellers are operable to make the remotely controlled aircraft fly.

Abstract: A flight control method for controlling an aircraft includes obtaining wind information of an operation region during a spread operation performed by the aircraft. The flight control method also includes controlling a flight location of the aircraft based on the wind information and an allowable deviation of the spread region in the spread operation.

Abstract: A storage and preparation system for food or beverages employs a galley cart with a plurality of compartments. A container receivable in one of the plurality of compartments. The container has an identifier. A sensor is in each of said plurality of compartments and is adapted to read the identifier. An environmental system responsive to the sensor is associated with each of said plurality of compartments.

Abstract: The present invention relates to a vehicle seat assembly, particularly but not exclusively to an aircraft seat assembly, comprising a first and a second seat secured together. Each of the first and second seats has a seat portion and a backrest with each seat portion extending forwardly from a respective backrest, wherein the backrest of the first seat is positioned forwardly and to the side of the backrest of the second seat. The present invention seeks to address the limitations of accommodating passengers in adjacent seats in a row of seats comprising two or more seats.