Abstract: A safe takeoff monitoring system checks the actual physical parameters of an airplane during takeoff, determines the actual takeoff weight, and warns the pilot to interrupt the takeoff if any dangerous situation is developing, before a high energy abort is necessary.

Abstract: It is described a movable pylon, associated with a lower portion of aircraft wing and with an aircraft engine to change the height of this engine between a flying position and a ground position, the movable pylon comprising: a main unique structure formed by a first movable structure pivoted to a second fixed structure, the first movable structure associated with the engine, the second fixed structure associated with the wing, and a pivot mechanism connecting the first movable structure to at least one point on the wing.

Abstract: An aircraft automatic control system protects structural parameters of an aircraft based on angle of attack protection by use of maximum allowed angle of attack values as a function of dynamic pressure or a combination of parameters that permit computation of dynamic pressure. Example techniques herein limit the wing lift coefficient as a function of dynamic pressure (or velocity) to create a limitation for the maximum lift produced by an aircraft wing.

Abstract: A flexible flight control system enables conversion from one architecture using one type of inceptor to another architecture using another type of inceptor, through the usage of modular software and hardware pieces with common interfaces among the different types of inceptors. Longitudinal and lateral directional control laws are adapted to be compatible with the specific aspects of the operation of each configuration/architecture, giving the option to the aircraft operator to choose any one of a number of inceptor architectures at time of manufacture.

Abstract: An aircraft compensates for asymmetry of engine failure by drawing part of the energy produced by the still-operating engine to generate thrust at the tip of the opposite wing. For example, the left engine drives its own thrust on the left wing, but a portion of the energy the left engine produces is delivered at a propeller at the tip of right wing. Similarly, the right engine drives its own thrust on the right wing, but a portion of the energy the right engine produces is delivered at a propeller at the tip of the left wing. In this way, every pair of engines and opposite tip thrust generators are intrinsically balanced. In the event of one engine failure, no yaw moment will be noticed.

Abstract: Reinforced wing spars for underwing mounted retractable landing gear assemblies include a unitary (one-piece) metal wing spar having a central web and an upper spar flange, a trunnion mounted in the web of the wing spar for pivotally receiving a transverse mounting tube of a retractable landing gear strut, and a reinforcement laminate adhered to and extending along the upper spar flange above the trunnion, wherein the reinforcement laminate is comprised of at least one fiber reinforced composite layer alternately interposed with at least one metal reinforcement layer.

Abstract: An inspection system for assessing and visualizing structural damage to a structural platform comprises sensors operatively coupled to the structural platform that assess structural damage to or failure of the structural platform. A structural health monitoring processor operatively coupled to the sensors determines structural damage in response to the sensors. At least one RF transponder and associated reader determines the position of the structural platform relative to a user augmented reality viewing device. The user augmented reality viewing device includes a camera that captures images of the structural platform. The user augmented reality viewing device displays real world images of the structural platform and virtual indications of determined structural damage that are dependent on the position and orientation of the user augmented reality viewing device relative to the structural platform.

Abstract: High precision radar to track aerial targets installed on the ground, in a container or in a vehicle, to determine the target parameters, such as azimuth angle (?a), elevation angle (?e), range, speed and flying direction and transmits them to a weapon system which comprises an array of two collinear antennas (19, 21) with narrow beam in elevation, installed on a platform (12) and rotating around a vertical axis at a rotational speed of, at least, 50 rpm, in which the direction of the said array varies between 0° and 90° by means of a positioning motor in elevation (18), and the precise target elevation angle (?e) is determined by interferometry. The precise target azimuth angle (9a) is determined through correlation between a signal detected by the said antennas (19, 21) with a +1/?1 step function, complemented by the search for the zero transition provided by the determination of the return pulse maximum.

Abstract: Devices and methods are provided whereby a preformed elastomeric tubular seal profile may be installed into a gap defined between an adjacent pair of structural panels. The device may include a frame and opposed first and second compression rollers attached to the frame for rotational movement about respective rotational axes. The opposed first and second compression rollers define a nip space therebetween for the introduction of a preformed elastomeric tubular seal profile, whereby moving the tubular seal profile through the nip space causes the tubular seal profile to compress and thereby form a downstream compressed profile portion and an upstream uncompressed profile portion. The compressed profile portion may thus be inserted into a gap between adjacent structural panels and thereafter allowed to expand (e.g., by removal of a plug element from a distal end thereof) to thereby seal the gap.

Abstract: Side-facing belted aircraft seats include a tactile signaling unit to induce movement of the seat occupant. For such purpose, the signaling unit may be provided with a signaling lid covering a female buckle of a lap belt restraint assembly. The signaling lid is moveable between a closed position wherein engagement of a male tab of the lap belt with the female buckle is precluded and an open position wherein engagement of the male tab with the female buckle is allowed. The signaling lid thereby provides tactile stimulation when in the open position thereof to induce the seated occupant to shift on the cushioned seat so that a midsaggital plane of the occupant is aligned with an offset plane of the seat that is offset by a predetermined distance toward one side of the seat relative to a midplane of the seat.

Abstract: A system and method for damage detection and for evaluating the real operation conditions for structural platforms using structural health monitoring is integrated to a system and method that permits for the platform to provide a flexible geometric control considering a self-adapting morphing which is capable of providing better operating structural platform performance.

Abstract: Pylon mounting assemblies are provided for mounting an engine (e.g., a turbojet engine) to a wing of an aircraft. The pylon mounting assemblies include an upper pylon connection member, and a lower pylon connection box, wherein the upper pylon connection member and the lower pylon connection box respectively include multiple opposed pairs of connection lobes. At least one pair of the connection lobes includes a pin connection to restrict degrees of freedom thereat along an x-axis and a mutually perpendicular z-axis, while at least one other pair of connection lobes includes a connection rod to restrict degrees of freedom thereat along the z-axis.

Abstract: Landing gear doors may be opened in an emergency event, e.g., a failure of the normal landing gear actuation system that requires a gravity free-fall deployment. The retractable aircraft landing gear door actuation mechanism will include a landing gear door and a door support bracket attached to the landing gear door. The support bracket is attached to aircraft structure for pivotal movement about a pivot axis between a closed condition whereby the landing gear door covers an aircraft landing gear when retracted relative to the aircraft structure, and an opened condition whereby the landing gear door is moved laterally and upwardly relative to the aircraft landing gear when extended relative to the aircraft structure. A gear door actuation assembly is operatively connected to the door support bracket for moving the door support bracket and the gear door supported thereby between the closed and opened conditions thereof.

Abstract: An integrated system for assessing the condition and management of a structural platform or a plurality of platforms includes a Structural Health Monitoring System (SHM), an Operational loads Monitoring System (OLM), a static, fatigue and damage tolerance analysis (FDTA) subsystem, a databank storing a maintenance plan, and a subsystem configured for damage and repair management (iSRM). The SHM may include a plurality of transducers, including a plurality of pairs of actuators and sensors; a generator device configured to excite at least one of said sensors to produce ultrasonic guided waves; and a signal processor device configured to receive the signals reflected from damage identification. The Operational loads Monitoring System (OLM) may comprise parametric models using flight parameter data. The static, fatigue and damage tolerance analysis (FDTA) subsystem may be configured to use parametric models using Finite element Models results and abacus.

Abstract: A flight control law enhances braking efficiency through the operation of aircraft elevators (or another pitch control system) using measured longitudinal acceleration and/or pedal position as references to the control law. Through this solution, it is possible to increase the vertical load in the main landing gear and consequently enhance braking efficiency.

Abstract: The present patent of invention describes a recycling process to recover fibrous reinforcing material of composite materials, particularly carbon fiber, primary reactor compound (101), for the controlled pyrolysis and oxidation of the composite material matrix (resin) at low temperature (400° C. to 500° C.) and a system for treating waste gases produced by thermal decomposition of composite material matrixes which employs a secondary reactor (201), containing within the same a thermal plasma arc (211). The main characteristic of the process, within the scope of the carbon fiber recycling, is the possibility of maintaining the fabric web, obtaining fabrics made of pure carbon fiber, without a significant amount of residues and preserving their structural characteristics. The thermal plasma allows managing high temperatures (2,000° C. to 15,000° C.

Abstract: Lightning protected vent lines associated operatively with aircraft fuselage fuel tanks (i.e., on-board fuel tanks that are not physically located in an aircraft's wing but instead are physically located within the aircraft's fuselage structure) are provided which include a vent conduit, a coupling at a proximal end of the vent conduit for fluid connecting the vent conduit to the fuel tank, a vent opening positioned at a distal end of the vent conduit and at an external location of the fuselage and a flame arrestor positioned in the conduit between the coupling and the vent opening. The vent conduit will have an effective axial dimension (L) between the coupling and the vent opening and the flame arrestor will be positioned in the conduit at an effective separation distance (D) between an inlet of the flame arrestor and the vent opening such that L/D is greater than 5.

Abstract: Aircraft antenna fairing assemblies include a fairing shell and connection components for positionally fixing the fairing shell to airframe structure of an aircraft. The connection components may comprise a guide assembly having a guide head and a receiver defining a guide channel for receiving the guide head therewithin, and a latch assembly for latching the fairing shell to the airframe structure of the aircraft. The receiver of the guide assembly may define a generally C-shaped or generally U-shaped channel for receiving the guide head therewithin.

Abstract: An online real-time method of measuring the thickness of a moving belt uses infrared thermography technology to continuously and noninvasively measure the thickness of rubber cover regions and detect damage. This technique solves technical problems and realizes potential gains such as increased efficiency in planning maintenance/replacements of conveyor belts; provides rationalizations and advanced planning for stocking spare conveyor belts; provides a lookahead of acute wear at points to avoid premature wear or belt loss; generates a history of generating wear after each belt replacement with life projections and early planning acquisitions and operational stoppages for exchange; and provides early warning system integration.

Abstract: Composite acoustic panels are provided which may usefully be employed for aircraft interior panel assemblies. The composite acoustic panels may include a core member defining opposed surfaces, and a pair of exterior face sheets each attached to a respective one of the opposed surfaces of the core member. At least one of the face sheets may be microperforated. The core member comprises an adjacent plurality of tubular channels extending through a thickness dimension of the core member between the opposed surfaces thereof, while predetermined adjacent ones of the tubular channels are filled with a material to define a series of filled tubular channels which are adjacent to a region of open tubular channels. Certain ones of the open tubular channels may be partially filled with an acoustic dampening material. Discontinuous viscoelastic layers may be positioned so as to overlay central regions of the adjacent plurality of the open tubular channels which are bounded by an array of the filled tubular channels.