Abstract: Cargo aircraft having a cargo ramp and cargo door oppositely hinged relative to one another to allow access to the aircraft's cargo space may be provided with a flying boom mast that is physically mounted at the aft portion of the fuselage so as to configure such cargo aircraft for aerial refueling operations. The flying boom mast may therefore be operably associated with the aft portion of the fuselage and moveable between a stowed and deployed conditions relative to the aft portion of the fuselage, while a fuel supply line fluid-interconnects the flying boom mast with an on-board fuel supply of the aircraft so as to allow aerial refueling of a receiver aircraft when the flying boom mast is in the deployed condition thereof.

Abstract: A flexible distributed multi-system architecture for aircraft control integrates electronic computers comprising plural types of high integrity, dissimilar, generic and reconfigurable controllers (GECs) that can assume different purposes. GECs are configured as actuator controllers (able to control up to three channels including hydraulic or electro-mechanical actuators) or as Control Law Computers (able to calculate more sophisticated and processor demanding control laws). The multi-system architecture is built around a backbone of high performance, high integrity digital protocols and three hubs with dual connection to two different GECs.

Abstract: A no/low visibility automatic takeoff system for an aircraft obtains a runway reference centerline and aircraft pointing direction (via the aircraft's sensors) and automatically controls the aircraft pointing direction to track the runway reference centerline. An initial vector is obtained based on the initial position of the aircraft the first piloted initiation of the takeoff roll. After the system obtains a centerline, it automatically tracks the centerline and corrects aircraft trajectory so the aircraft heading closely matches the runway centerline as the aircraft proceeds down the runway.

Abstract: Aircraft cargo lock assemblies are capable of positionally restraining movement of a cargo load pallet in both vertical and horizontal planes relative to the cargo deck of the aircraft. According to certain embodiments, the lock assemblies will include an actuator case and a restraint element which comprises at least one restraint plate and restraint detent, the restraint element being connected to the actuator case for pivotal movements between locked and released conditions relative to an edge of a cargo load pallet positioned on a cargo deck of an aircraft so as to positionally restrain the cargo load pallet against movement in both vertical and horizontal planes relative to the cargo deck. An actuator assembly is operably connected to the restraint element for moving the restraint element between the locked and released conditions thereof.

Abstract: Separable partition assemblies provide privacy between adjoining aircraft cabin sections, e.g., between a main passenger cabin section and a section having an emergency exit and a belted toilet seat such as may be provided in executive aircraft. The separable partition assembly includes a bulkhead structure defining a bulkhead passageway opening to allow passenger egress from one vehicle cabin section to an adjoining vehicle cabin section that is provided with at least one panel sized and configured to close the bulkhead passageway. A nonpermanent mounting system mounts the panel to an inboard edge of the bulkhead structure to allow the at least one panel to be separably uncoupled from the bulkhead structure in response to exertion of a force of predetermined magnitude thereagainst to thereby allow unimpeded passenger egress between the adjoining vehicle cabin sections.

Abstract: Describes a deflection mechanism of the flap panels of an aircraft, the aforesaid deflection mechanism being connected to a wing of an aircraft by means of a first fixed structure and to the flap panels by linkage points, in order to support and deflect the flap panels in desired positions, the deflection mechanism of the flap panels of an aircraft comprises of a set of moving hinged links pivotally connected with each other and linked to a first fixed structure, and a hinged drive link connected to the flap panel and to a second fixed structure, the set of moving hinged links being linked to the flap panel by at least one linkage point in order to pivot jointly the moving hinged links deploying the flap panels in an initially predominantly rectilinear and subsequently deflected trajectory and at the same time aligned with a longitudinal direction of the aircraft, without the use of tracks and rollers, the hinged drive link being pivoted from the movement of the flap panels by the set of moving hinged links.

Abstract: To improve high gain tracking characteristics of an aircraft during inflight probe and drogue refueling and other tasks requiring rapid trim capturing, an attitude hold button on the inceptor controls capture of current aircraft attitude and uses this attitude to update reference attitude datum. The pilot has the option of adjusting the attitude reference using an additional control such as a standard trim hat button.

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: The disclosed non-limiting embodiment provides important improvements in aircraft performance in short rejected takeoff systems by automatically detecting whether the speed of the aircraft does not exceed Vshort, where Vshort>V1; automatically detecting whether one of said plural engines has failed during takeoff while the aircraft is still in contact with the ground; and if the aircraft speed does not exceed vshort and an engine has failed, automatically performing an autonomous abort takeoff sequence to allow an improved takeoff weight in case of a single engine failure autonomously rejected takeoff. The aircraft's take off weight increase leads to increased payload or fuel quantity. The Payload increase allows for increased passenger and/or cargo capability. The fuel quantity increased allows the aircraft to achieve greater ranges. An aircraft provided with the proposed system, which reduces accelerate-stop distance, may then operate in shorter runways as compared to the prior art.

Abstract: Environmental control systems and methods to control environmental temperature of an enclosed space by integrating a passive heat exchange subsystem (e.g., a loop heat pipe (LHP) heat exchange subsystem) having a closed loop heat exchange fluid circuit in heat-exchange relationship with the enclosed space for providing environmental temperature control therewithin, a RAM-air subsystem having a RAM-air circuit for circulating RAM cooling air, and a vapor compression cycle machine (VCM) subsystem having a VCM fluid circuit having a compressor, an evaporator, a condenser and an expansion valve.

Abstract: Counterbalance assemblies include a torsion bar spring for counter-balancing the weight of upwardly opening aircraft doors for ease of opening and closing. The torsion bar spring may be linked to the aircraft door through an integrated gear reduction system comprised of two pairs of spur gears and respective shafts as well as a linkage assembly. A cable reel is connected to the output shaft and the input shaft is connected to a four bar linkage system attached to the end of the torsion bar. The cable reel stores the lift cable and provides the output torque to lift the aircraft door. When the aircraft door opens or closes, the center of mass loses or gains height respectively, causing a variation of gravitational potential energy. In such a manner, the gravitational potential energy is exchanged with strain elastic energy from the counter-balance spring therefore reducing the required external source of energy whether it is from a power assisted means or manual operation.

Abstract: A method converts an aircraft takeoff trim setting that would be a function of several parameters to a value that is a function of CG position only. In this way, it is possible to create a direct simple equivalence between Stabilizer angle and CG. The equivalent CG can be presented in real time to the pilot.

Abstract: Devices are provided to measure the mass inertia of moving surfaces (e.g., aircraft components). In certain embodiments, the devices will include a support frame formed by first and second structural frame members which form a space for positioning of a moving surface to be measured for mass inertia. A pivot joint assembly is supported by an upper portion of the first structural frame member while a distance alignment device is arranged at a lower portion of the support frame. The second structural frame member including an extension and a dynamometer supported operatively by the extension. The first structural frame member includes a comparator clock at a lower portion thereof.

Abstract: Exemplary embodiments are directed to thermally driven actuator systems including a thermally driven element and one or more heating elements coupled to and in thermal contact with the thermally driven element. The thermally driven element can be capable of being selectively reconfigured in shape based on a thermal strain or temperature driven phase change. The one or more heating elements can be configured to selectively and independently apply heat to one or more of a plurality of different regions of the thermally driven element to selectively raise a temperature or temperatures of the selected region or regions of the thermally driven element to selectively reconfigure the shape of the thermally driven element.

Abstract: Aircraft and associated methods, apparatus, system and storage devices for automatically positioning of lift control devices such as high lift devices including slats and flaps so an aircraft equipped with this technology will not need to count on the crew to command the lift control devices.