Abstract: A vehicle includes an internal cabin, a plurality of stowage bin assemblies within the internal cabin, a plurality of passenger service units (PSUs) within the internal cabin, and an emergency oxygen system within the internal cabin. The plurality of stowage bin assemblies are uncoupled (for example, separate and distinct) from one or both of the plurality of PSUs or the emergency oxygen system. In an example, the plurality of stowage bin assemblies are uncoupled from the emergency oxygen system. In another example, the plurality of stowage bin assemblies are uncoupled from the plurality of PSUs. In another example, the plurality of stowage bin assemblies are uncoupled from both the plurality of PSUs and the emergency oxygen system.

Abstract: A mission pod configured to be carried by a UAV or other aerial vehicle and accompanying systems and methods to allow the unattended accomplishment of diverse mission types is described. The mission pod having means for communication between the pod and UAV, mechanisms for removably attaching the pod to, and detaching the pod from, the UAV without the intervention of ground crew, mechanisms for facilitating power, fuel, and/or data transfer between the pod and UAV, means for securing various mission components within the pod, and pod configurations supporting various sensing modalities and other mission requirements.

Abstract: A stowage bin lighting assembly for mounting to an internal cabin of a vehicle includes a chassis having a plate extending longitudinally between ends. The chassis supports light mount pedestals, wire standoffs, and at least one valance support above the upper surface. The stowage bin lighting assembly includes a light mounted to the light mount pedestals positioned above the plate by the light mount pedestals for providing lighting from the stowage bin assembly to the internal cabin of the vehicle. The stowage bin lighting assembly includes a wire electrically connected to the light to supply power to the light and coupled to at least one of the wire standoffs to control a position of the wire relative to the plate. The stowage bin lighting assembly includes a valance coupled to the valance mount pedestals configured to be coupled to the stowage bin assembly by the valance support.

Abstract: Example moveable mounting structures and methods are described. In one implementation, an unmanned aerial vehicle (UAV) includes a body and a moveable mounting structure coupled to the body. The moveable mounting structure can move between a stowed position and a deployed position without interfering with a payload carried by the UAV. A camera is mounted to the moveable mounting structure.

Abstract: A stowage and removal system for an accommodation space for storing rollable containers in a vehicle is provided. It preferably has a rail system in the floor region of the accommodation space, on which rail system a transfer plate is movable, which transfer plate can assume a storage position and an insertion and removal position for the container. The storage position of the container is provided with its rear wall in the region of the rear wall of the accommodation space. The insertion and removal position is provided in the region of an insertion opening, arranged oppositely in relation to the rear wall, for the insertion and removal of a container into the accommodation space.

Abstract: An aircraft includes a fuselage defining a cabin region and a crown region. The aircraft also includes a duct disposed within the fuselage. The duct is coupled to one or more drying air vents disposed in the crown region and coupled to one or more cabin vents disposed with the cabin region. The one or more drying air vents are configured to output drying air, received via the duct, into the crown region, and the one or more cabin vents are configured to output conditioned air, received via the duct, into the cabin region. The aircraft further includes one or more valves coupled to the duct and configured to, in a first valve position, route airflow within the duct to the one or more drying air vents and configured to, in a second valve position, route the airflow within the duct to the one or more cabin vents.

Abstract: Example methods and systems for isolating and alleviating load in an aircraft are described, comprising providing a sliding joint between a seat track and a flight deck floor panel. The sliding joint comprises a lug comprising a first end and a second end opposite the first end, wherein the first end is adapted to attach to the seat track and the second end comprises an elongate aperture, and a clevis comprising an oblate shaped slider bushing that is coupled to the lug.

Abstract: A raceway system and method within an internal cabin of an aircraft include a plurality of routing modules that are coupled together. Each of the plurality of routing modules includes a main housing that routes one or more transferring components to one or more monuments within the internal cabin. A raceway system and method for an aircraft includes a transferring component attachment system that includes a plurality of transferring component support struts, and one or more transferring components coupled to the plurality of transferring component support struts.

Abstract: Embodiments for aircraft pressure deck. One embodiment is a pressure deck of an aircraft. The pressure deck includes beams extending longitudinally along a fuselage of the aircraft, and a web attached to an underside of the beams, the web including arches between adjacent beams to allow the pressure deck to flex laterally. The pressure deck also includes a box structure between a middle pair of the beams and configured to transfer load forward to a rear spar of a wing of the aircraft and aft to an aft wheel well bulkhead of the aircraft. The pressure deck further includes a first intercostal outboard from the box structure and configured to stabilize a first outboard pair of the beams, and a second intercostal outboard from the first intercostal and coupled between a second outboard pair of the beams via a swing link to allow the second intercostal to flex laterally.

Abstract: A method according to certain embodiments generally involves operating a system including an unmanned aerial vehicle (UAV) and a base station. The base station includes a nest including an upper opening having an upper opening diameter and a lower opening having a lower opening diameter less than the upper opening diameter. The lower opening is accessible from within the base station. The method generally includes landing the UAV within the nest such that a portion of the UAV is accessible via the lower opening, releasably attaching a load to the UAV, and operating the UAV to deliver the load to a destination.

Abstract: Multiple telescopes of a telescope array are rigidly aligned at predetermined relative orientations to simultaneously image corresponding predesignated celestial objects. Detection of light from the celestial objects collected by the telescopes enables calculation or estimation of orientation of the telescope array with respect to the celestial sphere. That orientation, in combination with a planetary nadir direction, enables estimation or calculation of position of the telescope array relative to a planetary surface. The nadir can be measured by dropping a probe particle through an evacuated chamber onto or through a two-dimensional sensor.

Abstract: Described herein are methods and systems to dampen oscillations of a payload coupled to a tether of a winch system arranged on an unmanned aerial vehicle (UAV). For example, the UAV's control system may dampen the oscillations by causing the UAV to switch to a forward flight mode in which movement of the UAV results in drag on the payload, thereby damping the oscillations. In another example, the control system may cause the UAV to reduce an extent flight stabilization along at least one dimension, thereby resulting in damping of the detected oscillations due to energy dissipation during movement of the UAV along the dimension. In this way, the control system could select and carry out one or more such techniques, and could do so during retraction and/or deployment of the tether.

Abstract: A wall assembly for an interior of an aircraft includes a frame member secured within a cabin of the aircraft having a first side and a second opposing side. The assembly further includes a first decorative panel secured to the frame member on a first side of the frame and a second decorative panel secured to the frame member on a second side of the frame.

Abstract: An aircraft is disclosed having a structure at least part of which is capable of generating aerodynamic lift. A body having a mass is movably mounted to a portion of the structure by an active support. The active support includes an actuator to move the body relative to the portion of the structure, and a controller for controlling movement of the actuator in response to a dynamic input. The active support provides a range of movement for the body in at least one degree of freedom. The actuator moves the body across the entire range of movement in that one degree of freedom in a time period of less than 3 seconds. The actuator moves the body sufficiently rapidly to generate an inertial force that is equal to or greater than any aerodynamic force generated by the body during that movement of the body. The active support may be used to reduce loads on the aircraft structure.

Abstract: An overhead stowage compartment of a passenger aircraft includes a carrier and a pivoting part being pivotable about a pivot axis and rotatable in a pivoting range at least between an open position and a closing position. A resetting device brings about a closing force in the direction of the closing position at a gripping point of the pivoting part. The closing force is greater than and opposed to the gravitational force, which is effective at the gripping point, by using the unloaded pivoting part. The stowage compartment has a holding device through the use of which the pivoting part can be held at the open position.

Abstract: A system has a frame with first and second spaced apart edges, a first holder couplable to the fuselage structure and embodied for articulated connection to a first region of the frame that is close to the first edge, a second holder couplable to the fuselage structure, and a strut. A first end of the strut is connectable in an articulated manner to the second holder. A second end of the strut is connectable in an articulated manner to a second region of the frame near the second edge and remote from the first edge. The frame and the strut form a triangular structure with the first and second holders. The strut and the frame form two sides of the triangular structure. A length of the first and/or second side is variable to adjust the position of the frame.

Abstract: A barrier for providing isolation between two internal volumes within an aircraft, comprises: a wall section adapted for location within an aircraft, the wall section having an aperture formed therein; mounting means located on the wall section proximate the aperture; and a substantially planar burst panel member having first and second opposingly-facing sides, the burst panel member adapted for location within the mounting means and dimensioned so as to overlie the aperture when received by the mounting means; the burst panel member comprising a line of weakness provided therein, adapted such that, in use, exposure of the burst panel member to an atmospheric pressure differential between air volumes respectively adjacent the first and second sides exceeding a predetermined value causes the burst panel member to rupture along said line of weakness.

Abstract: A balloon catheter includes a shaft, a balloon made of an expandable membrane, a flexible substrate, one or more electrodes, and one or more radiopaque flags. The shaft is configured for insertion into a heart of a patient. The balloon is fitted at a distal end of the shaft. The flexible substrate is disposed on the membrane. The one or more electrodes are disposed over the flexible substrate and have a fishbone configuration. The one or more radiopaque flags are coupled to the expandable membrane, wherein the one or more radiopaque flags include a serpentine pattern so that the radiopaque flags fold in conformance with flexible substrate as the expandable membrane is collapsed into a compressed or folded configuration.

Abstract: A passenger suite seating unit is disclosed. In embodiments, the passenger suite seating unit includes a first set of one or more passenger suites and a second set of one or more passenger suites. The passenger suite seating unit may further include a first privacy shell element defining at least a portion of a first side of the passenger suite seating unit, and a second privacy shell element defining at least a portion of a second side of the passenger suite seating unit. The passenger suite seating unit may further include a privacy bridge assembly including a bridge structure extending from the first privacy shell element to the second privacy shell element, and a partition wall coupled to the bridge structure, the partition wall configured to at least partially separate the first set of one or more passenger suites and the second set of one or more passenger seats.

Abstract: A locking pin assembly for a cargo loading system includes a shaft, a first retention pin, a second retention pin, and a synchronizer. The shaft defines a first shaft groove and a second shaft groove. The first retention pin and the second retention pin are disposed within the shaft. The synchronizer is disposed about the shaft and defines a first synchronizer groove that crosses over the first shaft groove and a second synchronizer groove that crosses over the second shaft groove.

Abstract: This application relates to a method for detecting chemical pollution cloud which is performed by an unmanned aerial vehicle comprising. In one aspect, the method includes receiving, from a control device for controlling the unmanned aerial vehicle, a control signal and generating a status signal indicating a state of the unmanned aerial vehicle. The method also includes determining an operation mode for detecting the chemical pollution cloud based on the control signal and the status signal. The method further includes detecting the chemical pollution cloud based on a pre-learned autonomous algorithm without the control of the control device when the determined operation mode is an automatic detection mode for detecting the chemical pollution cloud without control of the control device.

Abstract: Multiple telescopes of a telescope array are rigidly aligned at predetermined relative orientations to simultaneously image corresponding predesignated celestial objects. Detection of light from the celestial objects collected by the telescopes enables calculation or estimation of orientation of the telescope array with respect to the celestial sphere. That orientation, in combination with a planetary nadir direction, enables estimation or calculation of position of the telescope array relative to a planetary surface. The nadir can be measured by dropping a probe particle through an evacuated chamber onto or through a two-dimensional sensor.

Abstract: A morphing aerodynamic control surface geometry comprising a control surface having an articulated portion comprising a flexible skin coupled at an exterior of the articulated portion, the flexible skin comprising opposed interlocking elements sandwiched within a flexible polymer coupled to the interlocking elements; wherein the flexible skin is configured compliant responsive to an articulation of the articulated portion.

Abstract: Several embodiments of buffer zones are provided that are contemplated to be disposed with respect to two or more adjacent elements on an aircraft. The buffer zones adjust for dynamic spacing between the elements to help control different gapping requirements between the elements installed in the aircraft. Embodiments include an aircraft interior panel configuration, an aircraft interior wall panel configuration, an adjustable width aircraft bulkhead, and an aircraft personal service unit.

Abstract: An autonomous aircraft system an airframe configured with a ventrally located payload bay open to the empennage of said airframe and payload bay terminating with a forward bulkhead which is configured to receive a payload module. The payload bay and the payload module are configured with corresponding fittings for connecting the payload module to the aircraft control systems and for securing the payload module within the payload bay.

Abstract: Disclosed are structures and features of a space frame aircraft. In particular, this disclosure relates to a space frame aircraft with a pressure membrane.

Abstract: There is provided a sidewall closeout area assembly for an aircraft. The assembly includes a raceway with a first end to attach to a sidewall assembly, a second end to attach to aircraft floor structure(s), and a raceway body with first access opening(s) providing access to one or more of, a crown area and an underfloor area, for conductive elements routed along the raceway. The assembly further includes a raceway cover removably coupled to the raceway and having second access opening(s) providing access to the cabin and to an overfloor area in the cabin for the conductive elements. The assembly further includes a closeout area formed between the raceway body and the raceway cover, to house and protect the conductive elements. The assembly facilitates accessibility to the conductive elements, and provides a routing path for the conductive elements that does not need to be reconfigured for different aircraft cabin layouts.

Abstract: A radome assembly of an aircraft includes a shell having an elongated shape wherein the shell defines a first opening having a diameter of a first dimension and is positioned within a first end portion of the shell. The shell defines a second opening having an elongated shape which extends along a length of the shell and has a second dimension which is greater than the first dimension. First fastener extends through the first opening and is engaged with a first surface associated with a first structural element and resists movement of the shell and the first structural element relative to one another. Second fastener extends through the second opening and is engaged with a second surface associated with the first structural element such that the shell is moveable along the length of the shell relative to the first structural element.

Abstract: A container extraction assembly that includes an extractor assembly and a retainer assembly. The extractor assembly includes a pull member and an extractor member. The extractor member is movable between a distal position and a proximal position and the pull member is movable between first, second third positions. Moving the pull member from the first position to the third position moves the extractor member from the distal to the proximal position. The retainer assembly includes a proximal leg member and a distal leg member that are hingedly connected to one another. The retainer assembly is movable between a deployed position, a folded position and a finish position. Moving the pull member from the first position to the second position moves the retainer assembly from the deployed to the folded position, and moving the pull member from the second position to the third position moves the retainer assembly from the folded to the finish position.

Abstract: In various embodiments, the present disclosure provides an energy attenuating mounting foot comprising a load beam having a longitudinal axis, a top surface, a bottom surface, an inner track interface lobe, and an outer track interface lobe, the inner track interface lobe and the outer track interface lobe extending laterally from the load beam, and a channel along the longitudinal axis having a depth extending from the load beam bottom surface toward the top surface. In various embodiments, the inner track interface lobe has a first length extending in a direction from the bottom surface towards the top surface and the outer track interface lobe has a second length extending in a direction from the bottom surface towards the top surface, the first length being less than the second length.

Abstract: A modular panel system for attachment to an overhead stowage bin including an elongate bracket, a plurality of spacers, and at least one panel removably attached to the plurality of spacers without requiring tools to facilitate panel interchangeability independent of stowage bin structure. The at least one panel can be marked with, for example, branding, cabin class designation, advertising or wayfinding.

Abstract: A stowage bin assembly is configured to be positioned above at least a portion of one or more seats within a vehicle. The stowage bin assembly may include a pivot bin including a forward end panel, an aft end panel that is opposed to the forward end panel, a front panel extending between the forward and aft end panels, and a closeout bracket secured to the forward end panel, the aft end panel, and the front panel. A baggage retaining chamber is defined between the forward end panel, the aft end panel, and the front panel. The closeout bracket spans between the forward end panel and the aft end panel.

Abstract: In an example, an overhead payload module is described. The overhead payload module comprises a ceiling assembly, an aisle floor assembly, a first payload assembly attached to the ceiling assembly and the aisle floor assembly to form a first side of the overhead payload module, and a second payload assembly attached to the ceiling assembly and the aisle floor assembly to form a second side of the overhead payload module. The first payload assembly comprises a first payload module and a first overhead stowbin module structurally integrated with the first payload module and having a first stowage area configured to receive stowbins. The second payload assembly is positioned opposite the first payload assembly to form an aisle therebetween and comprises a second payload module and a second overhead stowbin module structurally integrated with the second payload module and having a second stowage area configured to receive stowbins.

Abstract: A Mobile Aircraft Secondary Barrier Cart which includes a main housing, with at least two retractable and expandable rigid barriers or a soft non-porous curtain that rise up from the main housing and encompass the entire forward galley/main cabin entrance and locks into place. The rigid barriers, when present, generally wedge into a female channel surrounding forward galley/main cabin entrance to hold the rigid barriers in placed. The purpose of the Mobile Aircraft Secondary Barrier Cart and the included curtain is to prevent unauthorized individuals from entering the Flightdeck when it is unlocked during flight.

Abstract: An obstacle avoidance system for an aircraft includes distance sensors mounted to the aircraft. The distance sensors each have one or more lasers for illuminating nearby obstacles and a detector for receiving laser light reflected off the nearby obstacles. A controller is configured for controlling the distance sensors and for determining distances between the distance sensor and the nearby obstacles based on data received from the detector. At least one camera may be externally mounted to the aircraft to provide images of the nearby obstacles. A user interface displays the images and the distances of the nearby obstacles.

Abstract: A monument has a connection device, a fluid source and a compartment for the installation of a modular unit. The connection device is intended for connecting the fluid source to a modular unit installed in the compartment. The connection device includes two line sections. It is connected to the fluid source via one line section and can be connected to a modular unit via the other line section. The connection device is arranged so as to be displaced in the compartment on a predefined track between a connection position and an operating position. In the connection position the connection device is further from the rear end of the compartment than in the operating position. The connection device can be connected, in the connection position, via the second line section to a modular unit arranged outside the compartment. Also described is a system including a monument and a modular unit.

Abstract: An observation system for an aircraft, related aircraft and method are provided. The observation system includes an observation assembly deployable between a retracted inner position and a deployed outer position outside a passage opening and a deployment mechanism of the observation assembly. The system includes a hatch, mounted moving between a position closing off the passage opening and a position clearing the passage opening, and a mechanism for maneuvering the hatch between the closing off position and the clearing position. The system also includes a conjugating assembly between the mechanism for deploying the observation assembly and the mechanism for maneuvering the hatch, active over at least part of the movement of the observation assembly between the retracted position and the deployed position, to move the hatch from the closing off position to the clearing position during the movement.

Abstract: An article of manufacture may include a tangible, non-transitory computer-readable storage medium having instructions stored thereon for orienting a display of a portable electronic device configured to control a cargo handling system. The instructions, in response to execution by a processor, cause the processor to perform operations which may comprise identifying an optical label scanned by a camera of the portable electronic device, determining a viewing angle of the camera relative to the optical label, and determining an orientation of the display of the portable electronic device based on the viewing angle of the camera relative to the optical label.

Abstract: Payload engagement systems, vehicles including the same, and related methods. A payload engagement system includes a vehicle supported portion and a payload mounted portion, one of which includes an insert component, and the other of which includes a receptor component. The payload engagement system is configured to transition between a disengaged configuration and an engaged configuration via rotation of the insert component with respect to the receptor component. In the engaged configuration, the receptor component receives the insert component such that the insert component is rotationally constrained within the receptor component. A method of transporting a payload with a vehicle includes engaging the payload with a payload engagement system that includes a vehicle supported portion and a payload mounted portion, transporting the payload with the vehicle, and disengaging the payload.

Abstract: In an example, an overhead payload module is described. The overhead payload module comprises a ceiling assembly, an aisle floor assembly, a first payload assembly attached to the ceiling assembly and the aisle floor assembly to form a first side of the overhead payload module, and a second payload assembly attached to the ceiling assembly and the aisle floor assembly to form a second side of the overhead payload module. The first payload assembly comprises a first payload module and a first overhead stowbin module structurally integrated with the first payload module and having a first stowage area configured to receive stowbins. The second payload assembly is positioned opposite the first payload assembly to form an aisle therebetween and comprises a second payload module and a second overhead stowbin module structurally integrated with the second payload module and having a second stowage area configured to receive stowbins.

Abstract: In one possible embodiment, a UAV payload module retraction mechanism is provided including a payload pivotally attached to a housing. A biasing member is mounted to bias the payload out of the housing and a winch is attached to the payload. An elongated flexible drawing member is coupled between the housing and the winch, the elongated drawing flexible member being capable of being drawn by the winch to retract the payload within the housing.

Abstract: A stowage bin assembly includes a bin bucket assembly having a bin bucket which includes at least one sidewall, the at least one sidewall including a notch and the at least one sidewall having an interior surface. The stowage bin assembly also includes at least one hinge assembly. The at least one hinge assembly includes a housing which is received in the notch, the housing having an interior surface, wherein the interior surface of the housing is substantially flush with the interior surface of the at least one sidewall when the housing of the at least one hinge assembly is received in the notch. The stowage bin assembly also includes a stowage bin door pivotably coupled to the bin bucket assembly via the at least one hinge assembly, the stowage bin door moveable between an open position and a closed position. Related components, assemblies, and devices are also provided.

Abstract: An aircraft assembly with first and second seat rails for interlocking with an aircraft seat, and a systems component mounting member interlocked with those seat rails. The mounting member has a first anchor member interlocked with the first seat rail and a second anchor member interlocked with the second seat rail. The assembly includes an aircraft systems component mounted on the mounting member. Existing seat rails or tracks of the aircraft can be used for attachment of support brackets for aircraft systems components. A novel way of using existing seat rails to provide anchorage points for systems brackets for systems components is disclosed.

Abstract: An interior component carrier system comprises a first and second installation rail. Each rail includes at least one connecting portion connectable to an associated primary structure component to fasten the rail to the component, and a carrier portion extending from the connecting portion in a direction along a longitudinal axis of the system. The system further comprises a first carrier element having a first end connected to a first carrier rod extending in a direction along the longitudinal axis and a second end connectable to a first interior component, wherein the first carrier rod is fastened to the carrier portion of the first rail, and a second carrier element having a first end connected to a second carrier rod extending in the longitudinal axis direction and a second end connected to the first carrier element, wherein the second carrier rod is fastened to the second rail carrier portion.

Abstract: This invention relates to a drone based predictive system for detecting and analyzing web and drone based data in order to mitigate potential losses and enhance risk mitigation activities in commercial insurance such as for business owners policies and workers compensation. The drone is able to capture from a plurality of angles and perspective to provide data to effect a variety of insurance based actions.

Abstract: In an illustrative embodiment, an upper monument attachment system is provided for retaining aircraft monuments, the system including a first support, a second support, and a joiner connecting a first end of the first support and a first end of the second support, a stay having a first end pivotably connected to the joiner, a tie rod configured to connect the joiner to an attachment point of the aircraft, a first rail having a first base configured to connect to an upper surface of the monument and a first facing configured to connect to the first support and the second support, and a second rail having a second base configured to connect to the upper surface of the monument and a second facing configured to connect to a second end of the stay.

Abstract: A system including a base provided with the means in the form of clamping and locking jaws for clamping and locking of the system into position in the rail, the means in the form of clamping jaws being movable between a first position and a second position by making use of maneuvering means that are operable by an operator between an unlocking position and a locking position, wherein the maneuvering means includes a clamping screw engaged in a hole and adapted so as to cooperate with a threaded hole and in that it has a smooth section in order to allow the screwing thereof into the threaded hole only when the base and the means in the form of clamping jaws are in the correct position of fastening in the rail.

Abstract: Provided are techniques for monitoring a moving vessel using a detachable drone coupled to the moving vessel. An event is identified that triggers detachment of the detachable drone from the moving vessel. The detachable drone is detached from the moving vessel. The detachable drone is moved to a predetermined location. A beacon based on beacon data is transmitted from the detachable drone. In response to the detachable drone receiving a request for the data, data collected from monitoring the moving vessel is delivered.

Abstract: Disclosed here is a cargo drive unit for a cargo hold of an aircraft. The cargo drive unit includes at least one driven power transmission element, which is configured to transmit drive forces to a load arranged in the cargo hold, in order to move the load inside the cargo hold. The cargo drive unit also includes a sensor unit configured to acquire at least one movement parameter of the load. The cargo drive unit also includes a control unit configured to control the power transmission element according to the acquired movement parameter. Also disclosed here is a cargo hold that includes such a cargo drive unit, and a related method for operating such a cargo hold.

Abstract: An overhead bin for an aircraft comprises a base unit that is designed to fasten the overhead bin to a retaining structure of the aircraft, and a mounting unit that is connected to the base unit. By way of the mounting unit, a stowage space of the overhead bin can be accessed. The base unit provides a first stowage space region, and the mounting unit provides a second stowage space region that together with the first stowage space region forms the stowage space of the overhead bin.