Abstract: Systems are disclosed to allow for the landing gear doors to be opened in the event of an emergency gravity free-fall landing gear deployment with little or no contact with the landing gear tires. The emergency gear extension systems according to the embodiments disclosed herein thus permit the free-fall movement of the landing gear to be synchronized with the opening of the associated gear doors. That is, according to the embodiments disclosed herein deployment of the landing gear assembly is time-delayed relative to the opening of the associated gear door(s). In such a manner, the landing gear assembly is synchronously released only after the associated gear door is in a safe position during its opening sequence thereby avoiding the risk that the gear door will jam the full extension of the landing gear during an emergency gear deployment due to contact between the landing gear tires and the gear door.

Abstract: Processes for fabricating a honeycomb core composite laminate structure are provided. The processes include subjecting a honeycomb core preform having a honeycomb core and a stabilizing layer of at least one ply of a resin-impregnated fiber reinforced matrix material (“prepreg material”) surrounding the honeycomb core to high temperature curing under an ambient atmospheric pressure condition. A final laminate layer formed of at least one ply of prepreg material may thereafter be laid up onto the stabilized preform to thereby provide a final product preform which is then subjected to high temperature and high pressure autoclave curing conditions sufficient to cure the final laminate layer and provide a final cured honeycomb core composite laminate structure.

Abstract: A counterbalance mechanism for counterbalancing weight of a bottom-hinged door (such as a clamshell-type airstair door of an aircraft) includes an operator handle, a hoist rod pivotally connected at one end to the operator handle and at an opposite end thereof to the door near a bottom region thereof. A force accumulator assembly is provided which includes a force biasing member which accumulates and dissipates a bias force when opening and closing the door, respectively, to provide mechanical counterbalance to the weight of the door. A bellcrank assembly operatively connects the operator handle to the force accumulator. In such a manner, weight counterbalancing of the door is achieved.

Abstract: The disclosed embodiments herein are generally directed toward force-balancing mechanisms for weighted members and/or loads. According to one embodiment, the force-balancing mechanism includes at least one gear rack, at least one spring assembly comprising a spring member operatively connected to the at least one gear rack, a pinion gear intermeshed with the at least one gear rack; and a variable radius cam. Rotation of the cam causes the pinion gear to rotate to thereby in turn linearly drive the at least one gear rack and accumulate spring force of the spring member. The spring member may be a compression or a tension spring. Preferably, the spring member is a compression spring.

Abstract: Enclosures for mass delivery of a living biological pest control agent according to the embodiments disclosed herein include a body section having a generally cylindrical wall with opposed ends defining an interior surface, parasitized eggs of a living biological pest control agent (e.g., an endoparasitic insect) adhered to the interior surface of the wall, and at least one egress opening to allow the pest control agent to exit the body section to an exterior environment.

Abstract: Finite element methods for compensating for springback in aircraft parts meet the visual appearance and aerodynamics of complex parts including those made of fabricated sheet metal. The methods can be used to make narrow parts (e.g., leading edge and slats) and double negative curvature parts, and do not need to leave marks on the surface of the sheet so that visual aspects are not adversely affected. The compensation technique, point to point uses approach equations with constant adjustable for curves. The constant(s) used depend on geometry and type of forming (e.g., stretch or hydraulic press). This example non-limiting process does not need to use mechanical properties of the material.

Abstract: Overhead bin assembly for transport vehicles (e.g., transport category aircraft) are provided with a generally U-shaped bin shell having a bottom wall, an outboard end wall and an upper wall defining an interior stowage space having an inboard opening opposite the end wall. A pair of separated transverse bin supports defining a bin space therebetween may be provided along with a bin door for closing the inboard opening. A cantilever hinge may be provided so as to connect the bin door to the transverse bin support in a cantilever manner to allow for pivotal movement of the bin door between closed and open positions relative to the inboard opening. An arcuate recessed wall may be positioned inboard relative to the upper wall of the bin shell (e.g., as a unitary (one-piece) extension thereof) such that the bin door is received within the recessed wall when in the open position thereof.

Abstract: A method estimates the health state of an aircraft pneumatic control valve through indirect measurements of available sensors. Measurements from identical valves operating under the same condition are compared. Residues are translated into estimates of individual valve degradation state. Historical degradation states can be used to predict expected time to failure.

Abstract: Passenger interface units include individual passenger modules having co-located controls for passenger comfort and entertainment systems. The modules will include a glass panel having front and rear surfaces, a structural support panel bonded to the rear surface of the glass panel and a light-emitting unit supported by the support panel behind the rear surface of the glass panel. The rear surface of the glass panel may include an opaque printed coating layer having at least one unpainted region that is transparent to visible light emitted by the light-emitting unit thereby allowing the visible light to be transmitted through the glass panel and visible at the front surface thereof.

Abstract: Adaptive, self-adjusting decorative trim assemblies are especially adapted for use in aircraft cabin interiors where the fuselage undergoes deformation and/or distortion due to pressurization during flight. The self-adjusting features of the decorative trim assemblies according to the embodiments described herein thus allow for relative movement between mutually intersecting interior cabin panels without jeopardizing the cabin interior aesthetics (e.g., since the relative positioning of the panels is not disrupted by virtue of such fuselage deformations).

Abstract: Assemblies and methods for the handling, transporting and/or positioning component parts include a jig assembly for supporting a component part is provided with an elongate spar assembly, a plurality of rib assemblies attached to the spar, and a plurality of tensionable strap assemblies operatively associated with the rib assemblies for capturing and holding the component part against the rib assemblies. The strap assemblies may include a strap ratchet mechanism and a strap, so that operation of the strap ratchet mechanism allows strap slack to be removed thereby tensioning the strap. The jig assembly may be positioned and oriented by suspension cables and a hoist mechanism to allow it to be removably connected to a moveable transport dolly.

Abstract: Methods and systems are provided to comply with structural load requirements applicable to aircraft additional fuel tank systems. A plurality of aircraft fuel tanks may be positioned adjacent to one another, preferably within the fuselage (e.g., a cargo compartment) of the aircraft so as to be disposed generally along a longitudinal axis of the aircraft. The tank body defining an interior space for holding aircraft fuel, an intercommunication conduit assembly between the fuel tank modules configured to refuel and transfer fuel from the tank modules by a cascade mode and an intentional air-filled ullage space are operatively associated with the tank body to prevent an overpressure condition within the interior space of the fuel tank body. The intentional air-filled ullage is obtained through the predetermined positioning of the terminal open end of the intercommunication tube inside the respective fuel tank module.

Abstract: Sensor pod attachment assemblies are provided for attaching a sensor pod containing airborne sensor equipment to an aircraft fuselage. The sensor pod assemblies may include fore and aft pairs of attachment pylon assemblies each having a lower end attached to the aircraft fuselage and an upper end attached to the sensor pod. The fore pair of attachment pylon assemblies can include port and starboard pylon structures, and a cross-support base connected to upper ends of the port and starboard pylon structures. The aft pair of attachment pylon assemblies may include a lengthwise adjustable spar assembly.

Abstract: Aircraft fuselage structures have reinforcement members in the vicinity of the stringer openings formed in frame members and are rigidly lap joined to a surface region of the frame members by a friction stir weld region. Such aircraft fuselage structural components may thus be provided with plural longitudinally spaced-apart frame members defining a transversal cross-section of an aircraft fuselage section, the frame members having a plurality of stringer holes therethrough, and plural longitudinally oriented stringers each being positioned within a respective one of the stringer holes of the frame member. The reinforcement members are lap joined to corresponding surfaces of frame members in the vicinity of the stringer holes such that the reinforcement members are joined rigidly to the corresponding surfaces of the frame members by a friction stir weld region.

Abstract: Switches for Ethernet-based aircraft data buses in avionics systems provide manual means (through human interaction) to route the information transmitted on avionics system high speed data buses. For instance, the information path can be selected according to crew or maintenance people intentions. Considering a point-to-point databus connection between two pieces of equipment, adding an appropriate switch in the connection between those two pieces of equipment can allow one or more pieces of equipment to be connected to the other terminals of the switch. Therefore, depending on switch position, it is possible to establish a connection between those two or more selected pieces of equipment, where other equipment connected to open terminals may remain without access to the data bus.

Abstract: A flight control system can achieve a relatively steep descent (using drag devices such as flight spoilers) at relatively low speeds while retaining good airplane handling qualities from the pilot's point of view. The system and method optimize the drag device's positioning used to perform steep approach to improve performance.

Abstract: Landing gear mechanism for aircraft are provided which include first and second connecting arms and front and rear wheels operatively associated with the first and second connecting arms, respectively. A balance beam element is indirectly linked to the front and rear wheels through each one of the connecting arms and shock absorber elements, respectively, so that the front portion of the balance beam element is associated with the first portion of the first shock absorber element. A positioning damper element is hingedly connected to the aircraft structure and also connected, directly or indirectly, to a portion of the body of the balance beam element.