Abstract: There is described a variable-width aerodynamic device (10) associable to aerodynamic high lift structures (30), the variable-width aerodynamic device (10) comprising: a main body (11) substantially flat and having constant thickness; a first longitudinal edge (12) associated to the aerodynamic high lift structure (30); and a second non-rectilinear longitudinal edge (13), forming, with the first longitudinal edge (12), a variable width (Lv) along its length.

Abstract: The Climb-Optimized Takeoff System is an aircraft functionality aimed at improving the takeoff performance. The improvement is obtained by allowing the airplane to rotate to an optimized pitch attitude at and after VR, while ensuring that the minimum required takeoff climb gradients and the geometric limitations of the airplane are being respected. The optimum takeoff performance is obtained by granting that the airplane pitch attitude, instead of being limited by a single takeoff constraint (such as a given pitch to avoid tail strike) is being tracked to its instantaneous, most constraining limit during the air transition phase (d2).

Abstract: Processes for fabricating an integrated fiber-reinforced cured resin-composite panel structure include forming a panel preform assembly by (i) positioning pre-cured fiber-reinforced resin-composite tubular stiffeners onto an uncured base skin, and (ii) applying uncured fiber-reinforced resin-composite overlapping layers onto the pre-cured stiffeners so that at least lateral edges of the overlapping layers are laminated to a corresponding region of the base sheet; and thereafter curing the fiber-reinforced resin-composite base skin and overlapping layers to thereby form an integrated composite panel structure.

Abstract: A process for fabricating an integrated panel structures and the structures thereby fabricated are provided with first and second stiffeners positioned on a base skin so that the stiffeners intersect at respective intersecting regions. First and second fiber-reinforced resin-composite overlapping layers are provided on the first and second stiffeners so that at least lateral regions thereof are laminated to a corresponding region of the base skin. The base skin and the overlapping layers may be assembled with the first and second stiffeners to form a panel preform which may then be subjected to curing conditions so as to co-cure all previously uncured components and thereby form an integrated composite panel structure with mutually intersecting first and second stiffeners.

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: 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: 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: 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: 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: A bleed leakage detection system includes an arrangement of thermostats that are capable of detecting the place where the bleed air leakage is occurring (e.g., the failed junction in bleed air duct work). The exemplary illustrative non-limiting implementation provides a bleed leakage detection system with continuous monitoring of thermostat sensor wiring during flight and thermostat self-test function (“Initiated Built In Test”—“IBIT”). The IBIT self-testing can be initiated before the aircraft takes off or optionally, during periodic self testing that may be run during predetermined periods such as overnight when the aircraft is not being flown. By the continuous monitoring the pilot is alerted when a bleed leakage has occurred or when the bleed leakage detection system has failed.

Abstract: Aircraft are provided with a perforated blade seal at the lower and/or upper side edges of a control surface contour, such as a flap, with the purpose of acting as a vortex generator, thereby making it difficult for the lower vortex system to move upwards and merge with the upper vortex system. The perforated blade seals are preferably arranged on the inboard and outboard edges of high lift flaps.

Abstract: Automated positioning and alignment methods and systems for aircraft structures use anthropomorphous robots with six degrees of freedom to carry the aero structure parts during the positioning and alignment. The parts and structures (if any) supporting the parts are treated as robot tools.

Abstract: Aircraft are provided with a pair of auxiliary power units (APUs) adjacently mounted in parallel relative to one another within the tail cone section of the aircraft's fuselage. In some embodiments, the APUs are mounted generally vertically adjacent to one another. Alternatively, the APUs may be mounted generally horizontally adjacent to one another. The aircraft fuselage may include a pair of downwardly and outwardly oriented strakes adjacent the tail cone having lower edges which establish a maximum take-off pitch angle of the fuselage and define a spatial zone therebetween. The APUs are positioned within such a spatial zone defined between the strakes so that the maximum take-off pitch angle is not required to be changed when modifying an existing single APU aircraft with dual APUs.

Abstract: A longitudinal control law is designed to optimize the flying qualities when aircraft is set to approach configuration, i.e. when the flap lever is set to the landing position and landing gears are locked down. Under such circumstances, the effort of trimming the aircraft speed can be extremely reduced by the usage of a momentary on-off switch or other control in the sidestick, instead of or in addition to a conventional trim up-down switch, making easier the task of airspeed selection by the pilot. This control law provides excellent handling qualities during approach and landing, with the benefit of not needing or using radio altimeter information in safety-critical applications.

Abstract: A VG (vortex generator) placed on a body surface (aircraft or similar), upstream of a flush air inlet, in order to generate vortexes that will sweep away the boundary layer in front of the inlet, inducing a downwash effect in the freestream airflow, such VG consisting of a wing (1) parallel to the surface of the aircraft or similar, said wing supported by a support (2) or a pair of supports (2) such as fins disposed in a divergent angle; the VG considerably improves the inlet ram recovery ratio and the mass flow ratio of the air inlet and it has an effect of reduction of the VG boundary layer thickness, thus reducing the distortion level of the flow entering the inlet as the inlet ingests more freestream air and the vortexes are not ingested by the inlet.

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: 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: A method for joining components through mechanical adhesion comprising the following stages is disclosed: a) curing a resin laminate (1) on a surface (10) of a first component (11) imprinting a texture portion (30) upon the resin laminate (1); b) positioning an adhesive material laminate (2) on the texture portion (30); c) positioning a second component (12) on the adhesive material laminate (2); and d) curing the adhesive material laminate (2) and penetration of the adhesive material laminate (2) into the texture portion (30). Also described is a mechanical adhesion joint (20) for joining components, comprising an anchorage (40) formed by a texture portion (30) disposed on a first component (11) and permeated by an adhesive material laminate (2) contained in a second component (12), the texture portion (30) comprising a locking profile (31).