Abstract: An anti-ice system including means for removing water from a heated ice prone surface before the water reaches a surface downstream of the ice-prone surface. In one embodiment, the means comprises an eductor connected to the ice-prone surface. In another embodiment, the means comprises a mechanical pump connected to the ice-prone surface. Examples of the ice-prone surface include an engine inlet or an aero-surface on an aircraft.

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: A pressure control system may include a plurality of inflatable objects, each of the inflatable objects having a respective pressure sensor and a respective inflation valve, wherein each of the inflation valves has a behavior profile predictive of an amount of current used by the valve when operated. A valve controller of the system may have a pressure management circuit that receives information from the pressure sensors and is configured to automatically maintain a respective selected pressure in each of the inflatable objects by issuing commands to operate the inflation valves. An electrical current management circuit of the valve controller may be configured to predict, based on the valve behavior profiles, what effect the command would have on a total current usage, when executed, and automatically prevent any command that would cause the total current usage to exceed a maximum allowable current.

Abstract: A propulsion device for controlling the orbit of an earth-orbit satellite including a structure of which the orientation is maintained constant in relation to the Earth in an operational configuration of the satellite in the orbit; a center of mass of the satellite being contained in the structure of the satellite, includes two thrusters suitable for delivering a thrust according to one axis, and fixed to the structure of the satellite in the same half-space separated by the plane of the orbit. The thrusters are arranged on either side of a plane containing the center of mass and perpendicular to a Z-axis; the thrusters being configured in such a way that a force resulting from the thrusts of the two simultaneously activated thrusters represents a principal component according to a Y-axis of the satellite oriented perpendicular to the orbit.

Abstract: A system and method for reducing a psychoacoustic penalty of acoustic noise emitted by an aircraft, including a plurality of propulsion assemblies coupled to the aircraft, wherein each of the plurality of propulsion assemblies includes a motor, and a plurality of blades defined by a propeller, wherein the plurality of blades can define an asymmetric blade spacing; a control subsystem coupled to the aircraft and communicatively coupled to the motor of each of the plurality of propulsion assemblies, wherein the control subsystem is operable to rotate each of the plurality of propulsion assemblies at a different frequency to modulate the acoustic power distribution of the emitted acoustic signature.

Abstract: In one possible embodiment, a system capable of a self-propagating data link includes an unmanned vehicle having a data link transceiver and at least one deployable data link transceiver. The unmanned vehicle having a deployment means for deploying the at least one deployable data link transceiver.

Abstract: An aircraft nacelle air intake structure including an air intake lip with a U-shaped section to ensure air is shared between an inner face and an outer face. An acoustic panel is on the intake lip rear on the side of the inner face level with a first assembly point. An outer panel is on the intake lip rear on the side of the outer face level with a second assembly point. A front reinforcing frame on the intake lip inside is fixed to the air intake lip on the side of the inner face level with a first fixing point and on the side of the outer face level with a second fixing point. The length of the chord between the stop point and each fixing point is between ? and ? of the total chord between the stop point and the assembly point.

Abstract: Adjustment mechanisms, systems and methods allow for a moveable aerodynamic surface to be positionally adjusted relative to a stationary adjustment surface so as to ensure smooth aerodynamic transition between such surfaces. The adjustment mechanisms may include a base structure adapted for fixed connection to the moveable aerodynamic surface, a fixed-position receiver opposing the base structure and adapted for positionally fixed connection to the support structure of the moveable aerodynamic surface and an adjustment bolt having a head and a threaded shaft extending from the head through an elongate slot of the base structure, the slot defining an elongate axis which is aligned with an adjustment axis for the moveable aerodynamic surface, and being threadably coupled to the receiver to operably interconnect the base structure and the receiver.

Abstract: A carpet display system includes a plurality of carpet modules. Each of the plurality of carpet modules includes a translucent support panel, a carpet layer secured to the support panel, and a light-emitting element coupled to the support panel. The light-emitting element is configured to emit light through the support panel to provide lighting effects through the carpet layer.

Abstract: Systems and methods include providing an aircraft with a tail rotor system having a tail rotor housing that forms a cambered airfoil between an upper cambered surface and a lower cambered surface of the tail rotor housing. The cambered airfoil design of the tail rotor housing is capable of providing sufficient lifting force of an aircraft to offload the tail rotor during forward flight, thereby eliminating the need for a traditional vertical stabilizer or fin. The tail rotor blades of the tail rotor system are disposed within an aperture in the tail rotor housing, which minimizes or preferably eliminates exposure of the tail rotor blades to edgewise airflow typically encountered during forward flight, thereby allowing rigid rotor hubs, both in-plane and out-of-plane, to be used in the tail rotor system while also reducing noise output of the tail rotor system.

Abstract: Drainage devices intended to prevent the reentry of drained fluids, the devices including a base having a contact surface for mounting over a drainage opening in an aerodynamic surface, a mast portion connected to the base and extending away from the contact surface of the base, and a top portion connected to the end of the mast portion, the top portion having a periphery that is greater than the periphery of the mast portion and including an exit port. The top portion may include a cantilevered fence portion extending upstream relative to the aerodynamic surface, and the drainage devices may be part of a system including a first opening and a second opening in the aerodynamic surface, the second opening upstream from the first opening, where a drainage device is mounted over the first opening and the cantilevered fence portion of the drainage device extends upstream toward the second opening.

Abstract: An unmanned aircraft system (UAS) configured for both vertical take-off and landing (VTOL) and fixed-wing flight operations includes forward and aft wing assemblies mounted to the fuselage, each wing assembly including port and starboard nacelles terminating in motor-driven rotors powered by an onboard control system capable of adjusting rotor speeds. The UAS may transition between a powered-lift VTOL configuration to a winged-flight configuration by shifting its center of gravity forward, pivoting the wing assemblies from a powered-lift position perpendicular to the fuselage to a winged-flight position parallel to the fuselage. The forward rotor blades may be folded back so that the aft rotors may provide primary thrust for winged flight operations. Onboard attitude sensors may detect rotor or control failures, to which the control system responds by triggering a conversion to the winged-flight configuration for recovery operations.

Abstract: A solar powered aircraft including a modular main wing and a pair of relatively large modular winglets attached to the transverse end portions of the main wing. To collect solar radiation, including relatively low-angle radiation, solar panels are mounted to both the main wing and the winglets. In some embodiments, the aspect ratio of the main wing is relatively low, such as between 9 and 15, i.e., the main wing is relatively deep compared to its wing span. In some embodiments, the winglets are relatively long, such as in the range of 0.2 to 0.7 times the length of the main wing semi-span. In some embodiments, a truss-like spar passes through and helps support the wing and the winglets.

Abstract: A modular electrical signal supply assembly includes a floor panel and at least one power/data strip (PDS) panel insert configured to provide an electrical signal to an electrical device. A vehicle includes an interior cabin with an electrical signal distribution system that includes a plurality of modular electrical signal supply assemblies and a plurality of electrical devices. Each modular electrical signal supply assembly includes a floor panel and at least one PDS panel insert. Each PDS panel insert is configured to provide an electrical signal to an electrical device and is electrically coupled to at least one other PDS panel insert. A method of assembling an interior cabin includes providing at least two modular electrical signal supply assemblies, each of which includes a floor panel and a PDS panel insert, positioning the floor panels in the interior cabin, and electrically coupling each PDS panel insert to at least one other PDS panel insert.

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 tip on the housing beneath the slot, and wherein the slot is adapted to receive a handle of a payload. A method of delivering a payload using the payload coupling apparatus is also provided.

Abstract: An actuator system for controlling a flight surface of an aircraft includes a first actuator having a first actuator input and a first linear translation element that moves based on rotational motion received at the first actuator input and a first sensor coupled to the first linear translation element that generates a first output based on a displacement of the first linear translation element. The system also includes a second actuator having a second actuator input and a second linear translation element that moves based on rotational motion received at the second actuator input and a second sensor coupled to the second linear translation element that generates a second output based on a displacement of the second linear translation element. The system also includes a control unit that receives the first and second outputs and determines if an error condition exists for the system based on first and second output.

Abstract: An electronic baggage stowage system for an aircraft comprising a first detector to detect free space in a cabin stowage space, wherein the first detector is configured to output cabin stowage space data based on the detection, a processing unit communicating with the first detector, wherein the processing unit is configured to process the cabin stowage space data, receive and process baggage size data indicating the size of one or more baggage items, and output baggage stowage mapping data in response to the processing of the cabin stowage space data and the baggage size data. The baggage stowage mapping data indicates one or more target positions in the cabin stowage space at which the baggage items are to be placed. An indicator communicates with the processing unit to provide the indication of the one or more target positions to a flight attendant or passenger of the aircraft.

Abstract: An automated aerial vehicle (AAV) and system for automatically detecting a contact or an imminent contact between a propeller of the AAV and an object (e.g., human, pet, or other animal) are described. A safety profile for the AAV may be selected based on various factors including a position or configuration of the AAV. When a contact or an imminent contact is detected, the selected safety profile may be executed to reduce or avoid any potential harm to the object and/or the AAV. For example, if a contact with a propeller of the AAV by an object is detected, the rotation of the propeller may be stopped to avoid harming the object. Likewise, an object detection component may be used to detect an object that is nearing a propeller, stop the rotation of the propeller, and/or navigate the AAV away from the detected object.

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: A wing or stabilizer of an aircraft. The wing or stabilizer comprises a box portion, comprising at least one spar and an outer skin coupled to the at least one spar. The wing or stabilizer also comprises at least one panel, comprising an outer face-sheet and an inner face-sheet. In a fore-aft direction the outer face-sheet terminates at an outer free edge. In the fore-aft direction the inner face-sheet terminates at an inner free edge. The at least one panel also includes a core sandwiched between the outer face-sheet and the inner face-sheet. The inner face-sheet comprises a cantilevered portion. The cantilevered portion defines the inner free edge. The cantilevered portion is fastened to the outer skin of the box portion.