Abstract: An aircraft energy management system including a cabin air compressor adapted to be coupled to a source of fan discharge air at a first pressure during an inflight operating mode and adapted to be coupled to a ram intake air during a ground operating mode. The system further including an environmental control system mechanically coupled to a compressor exit of the cabin air compressor. The aircraft energy management system configured to provide a conditioned fluid flow to an aircraft cabin, cockpit or de-icing system.

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: There is disclosed a structural arrangement (10) for an access window (30) to a fuel tank (20) with composite coating (40), this structural arrangement (10) comprising an external lid (11) associated to the access window (30) by fastening means (12), the structural arrangement (10) for an access window (30) to a fuel tank (20) with composite coating (40) further comprising a continuous metal frame (31) disposed on an internal portion of the fuel tank (20), fastened to the composite coating (40) internally and perimetrally circumventing the access window (30), the continuous metal frame (31) being cooperative with the external lid (11) in the conduction of an electric current.

Abstract: Devices and methods are provided for testing weld strengths of a test coupon joint. A test coupon is positionally fixed to a base of the testing device. A punch assembly having a head portion is provided so as to exert an axial force against an upright part of the test coupon to thereby determine weld strength between the planar and upright parts of the test coupon (e.g., a maximum force at which weld failure occurs).

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: Devices and methods for stabilizing a structural component are provided. The devices may include a main body component, a pair of opposed stabilization feet engageable with opposed regions of the structural component, a pair of coaxially disposed and reciprocal rectilinearly movable support shafts coupling the stabilization feet to the main body component, and an actuator assembly for rectilinearly moving the support shafts opposite to one another which in turn moves the stabilization feet between retracted and extended positions relative to the main body component. In use, the device may be positioned between opposed flanges of a structural component so as to stabilize the component and facilitate automated assembly processes.

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: Maintenance interventions are planned using RUL (Remaining Useful Life) estimations obtained from a PHM (Prognostics and Health Monitoring) system as well as estimations of spare parts availability. PHM information is used to verify whether spare parts will be available when the next failures are expected to occur, and expected RUL of a component or system based on a set of measurements collected from the aircraft systems can be used to schedule repair times that do not conflict with other repairs to avoid wait time and maximize repair shop capacity utilization.

Abstract: In an improved inventory control policy and associated data processing system, effective inventory level is compared with a variable reorder point, R(t). When the effective stock is lower than the reorder point R, a new order of Q units is placed. Also, the lot size is optimized for each order. Parameters R and Q are continuously updated based on Remaining Useful Life (RUL) estimations obtained from a Prognostics and Health Monitoring (PHM) system.

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: A process for joining parts together is provided by positioning and temporarily clamping parts to be joined together. A number (n) of pilot holes may then be drilled through the temporarily clamped parts (e.g., by means of Cleco fasteners), wherein the number (n) of pilot holes is less than a total number (N) of holes required to be drilled to allow the parts to be joined together by permanent fasteners and to receive temporary fasteners therein. A remaining number (?) of holes to achieve the total number (N) of holes required for the parts to be joined together by permanent fasteners may thereafter be drilled so that permanent fasteners may be installed both, by automated system, in the number (n) of pilot holes and the remaining number (?) of holes that have been drilled to thereby permanently join the parts together.

Abstract: A system and method for analysis of steps of action of a person in activity in an environment with potential occlusion and without the need to use of invasive equipment. Non-limiting implementations use posture registration and postural analysis based on an observation protocol that allows reconstruction, in a digital human simulation environment, of the adopted postures observed in a real time situation or by video.

Abstract: Curing cauls formed of a one-piece three-dimensional resiliently shape-retentive fiber-reinforced body are provided, whereby the body includes a fibrous sheet coated with at least one layer of a cured elastomeric resin. The fibrous sheet may be embedded within the cured elastomeric resin, with the body having a stiffened perimetrical edge region and a stiffened ridge region vertically spaced from the edge region.

Abstract: A method to acquire the structural health state of an aircraft mechanical component performs measurements at each frequency point of interest by using a network of transducers and working each one simultaneously as actuator and sensor. Each transducer is individually excited by a sinusoidal, constant frequency and arbitrary amplitude, voltage waveform for each arbitrary frequency point used to interrogate the structure. A dedicated hardware executes an analogical (analog) quantization to measure electrical current and average electrical power consumed by each transducer. With these two variables, the electromechanical signature of the structure is obtained at different areas of the monitored structure.

Abstract: Diverter assemblies for aircraft air inlets include a diverter structure at least substantially surrounding the air inlet, and a fairing mounted to an upper edge of the diverter structure forwardly of the air inlet.