Abstract: Drilling jigs are provided which include a one-piece jig body (preferably additively manufactured from laser-sintered metallic (e.g., aluminum alloy) powders) having at least one set of cylindrical sockets that are spatially separated from one another, and a web member joining the at least one set of sockets. Cylindrical bushings may thus be positioned within each of the cylindrical sockets so as to define respective cylindrical guideways for a drill bit. According to certain embodiments, the web member may be planar and oriented parallel to a substantially longitudinal bisecting plane of the cylindrical sockets.

Abstract: Advancements in executive aircraft interior design explicitly address the limitations of traditional physical windows within aircraft cabins. The passenger experience is transformed by integrating advanced hybrid technology, replicating expansive exterior views, fostering a sense of connection to the surroundings, and an immersive travel experience through a mimetic virtual display.

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 light unit executes up to three different functions (cabin area illumination, individual/dedicated/decorative illumination and emergency illumination) and an emergency illuminated sign unit, each one with an internal controller and a rechargeable capacitor. An example non-limiting embodiment also provides a cabin light system and an emergency lighting system, where each illumination unit (light source or illuminated sign) is as described above.

Abstract: Processes for fabricating a partially stabilized honeycomb core is disclosed where a stabilizing layer of an adhesive film is aligned with and adhered to only one exterior surface of a honeycomb sheet. The opposed exterior surface thereby remains uncovered. A preform of the partially stabilized honeycomb core may be subjected to ambient atmospheric pressure cure conditions at an elevated temperature sufficient to adhere the stabilizing layer to the one exterior surface of the honeycomb sheet and thereby provide a partially stabilized honeycomb core that is partially stabilized against compressive forces exerted in widthwise and lengthwise directions thereof yet allows bending of the partially stabilized honeycomb core about axes in the widthwise and lengthwise directions.

Abstract: Hybrid tooling structures are provided which include an additively manufactured thermoplastic tooling unit defining a tooling surface for receiving and supporting a component part to be manufactured, and a rigid metal support member fixed to the tooling unit. The rigid metal support member may be internally provided as an integral part of the additively manufactured tooling unit (e.g., the integral support member serving as an endoskeletal support structure for the tooling unit) which is especially adapted for high temperature/pressure processing conditions or may be externally provided as a support frame to which the additively manufactured tooling unit is fixedly attached (e.g., the frame serving as an exoskeletal support structure for the tooling unit) which is especially adapted for ambient room temperature/pressure and loads during processing conditions.

Abstract: An aircraft fly-by-wire control system allows takeoffs with a single initial horizontal stabilizer or trim tab position while maintaining satisfactory rotation times, thus allowing simpler aircraft operation and avoiding the scenario in which the crew does not correctly trim the aircraft (mistrim takeoff scenario) which could reduce safety margins.

Abstract: Thermal barrier curtain systems include a thermal barrier curtain and port and starboard anchor/hoist strap assemblies. The thermal barrier curtain includes forward and aft flexible air-impervious panels which are sealed about peripheral edges thereof so as to define a central thermal barrier region and separator elements positioned between and attached to the forward and aft panels within the central thermal barrier region so as to define a dead air space therebetween. Each of the port and starboard anchor/hoist strap assemblies includes an elongate strap, upper and lower attachment members positioned at opposed upper and lower ends of the elongate strap, an upper attachment loop adapted to receive and be attached to a respective connection element of the thermal barrier curtain, and an intermediate retaining loop which is adapted to receive and be attached to the lower attachment member of the anchor/hoist assembly.

Abstract: Methods and systems for painting surfaces (especially vehicle surfaces such as exterior aircraft surfaces) are provided whereby an applied basecoat layer may be treated with plasma (e.g., a non-thermal atmospheric pressure plasma) or laser radiation so as to form a treated basecoat layer which exhibits a decreased contact angle and an increased wetting energy as compared to the contact angle and wetting energy of the basecoat layer which is untreated. At least one inkjet printed color layer may be applied onto the treated basecoat layer followed by the application of a clearcoat protective layer over the one or more inkjet printed color layers.

Abstract: Seat mounting assemblies and vehicle seat systems which include the same are provided whereby a pivot bracket is operatively connected to a mounting bracket for reciprocal vertical movements while a tubular support member is operatively be associated with the pivot bracket so as to be pivotally movable about a substantially vertical central axis of the pivot bracket. A cantilevered support base arm is fixed to and extends outwardly from the tubular support member. An arm member is telescopically connected to the cantilevered support base arm to allow reciprocal rectilinear movements relative to the support base arm along a substantially horizontal axis thereof between retracted and extended positions thereof and carries a swivel plate at a distal end thereof to thereby allow swivel movements of a vehicle seat about a substantially vertical seat axis parallel to the substantially vertical central axis of the pivot bracket.

Abstract: Processes for forming fiber reinforced composite aircraft components, i.e., aircraft components formed of a cured fiber-reinforced resin, are provided. According to specific embodiments, a finished surface of the composite aircraft component can be achieved by providing in-mold coating of the cured fiber-reinforced resin by a dried and cured film layer of a water-based primer paint material to thereby achieve a composite aircraft component having an exterior surface that does not necessarily require further finishing.

Abstract: Vehicle seat systems, especially seat systems for aircraft passengers are provided. In preferred forms, the aircraft seat systems according to the embodiments disclosed herein will include a seat base assembly, a seat tracking/swivel assembly fixed to the seat base assembly and a seat bucket fixed to the seat tracking/swivel assembly.

Abstract: Fuel cell and power train (FCPT) systems are provided and adapted to being operatively mounted at a tail section of an aircraft fuselage. The FCPT systems will include port and starboard subsystems each being comprised of a nacelle adapted to being laterally attached to a respective side of the tail section of the fuselage, an electric motor contained in the nacelle, a propeller assembly mounted to the nacelle and operatively connected to and adapted to be driven by the electric motor contained therein, and at least one fuel cell positioned in the tail section of the fuselage to supply electrical power to the electric motor contained in the nacelle. One or more hydrogen fuel tanks may be mounted within the tail section of the fuselage to provide a source of hydrogen gas (H2) as fuel to the fuel cells.

Abstract: Access cover panel assemblies are provided that are especially useful to cover access openings of aircraft wing fuel tanks and include an inner cover plate and an outer cover plate spaced from the inner cover plate which defines a circumferentially spaced-apart plurality of apertures. A circumferentially spaced-apart plurality of generally U-shaped floating nut plates dependently extend from the inner cover plate toward the outer cover plate with each nut plate being in alignment with a respective one of the apertures. A corresponding plurality of attachment bolts extend through each of the apertures of the outer cover plate and are threadably coupled to a respective one of the floating nut plates to thereby removably secure the inner and outer cover plates to one another and to the surrounding structure defining the access opening.

Abstract: In the event of a failed engine, an automatic takeoff thrust asymmetry compensation system (“ATACS”) for an aircraft improves capabilities to reduce VMCG and deal with the potential side-effects simultaneously. The system commands selected control surfaces (which can be e.g., rudder and/or ailerons and/or spoilers or any combinations thereof) for a short period of time, improving the capability to reduce the VMCG without increasing the penalty on system failures or poor handling qualities.