Abstract: A thrust reverser system and method for controlling actuation thereof. The thrust reverser system may have a control system, two thrust reverser doors actuatable between an open position and a closed position, hydraulic actuators attached to and used to actuate each of the thrust reverser doors, servo valves each communicatively coupled with one of the hydraulic actuators to control hydraulic flow to and from the hydraulic actuators, and position sensors mounted on each of the thrust reverser doors to provide signals associated with a position thereof to the control system. The control system may send command signals to the servo valves to independently adjust at least one of hydraulic flow rate, hydraulic pressure, direction, and position of the hydraulic actuators depending on an amount of offset between the signals received from the position sensors.

Abstract: A bladder monitoring apparatus and method for monitoring an inflatable bladder during curing of composite material in an autoclave. The bladder may be wrapped with composite material and have an impermeable membrane sealed around the composite material. The method may include the steps of fluidly coupling a vacuum port of the impermeable membrane with a vacuum source and fluidly coupling a vent of the bladder with a first port of a flow meter located outward of the autoclave. A second port of the flow meter may also be fluidly coupled with atmosphere within the autoclave. The method may then include evacuating air from within the impermeable membrane. If a flow above a threshold flow is detected by the flow meter, the leak in the bladder may be located and repaired or a valve of the flow meter between the first and second ports may be closed.

Abstract: An aircraft engine pylon comprises a top wall, a bottom wall, a left side wall, and a right side wall. The left side wall includes a left truss structure along with a left upper ledge and a left lower ledge. The right side wall includes a right truss structure along with a right upper ledge and a right lower ledge. The top wall is joined with the left upper ledge and the right upper ledge and an upper truss structure is formed in the left upper ledge, the right upper ledge, and the top wall. The bottom wall is joined with the left lower ledge and the right lower ledge and a lower truss structure is formed in the left lower ledge, the right lower ledge, and the bottom wall.

Abstract: An inlet for an aircraft engine nacelle having an acoustic barrel panel, a septum buried or sandwiched within the acoustic barrel panel, and a perforated face sheet. The inlet may be located forward of an engine and/or an engine fan housed within the aircraft engine nacelle. Both the septum and the perforated face sheet may have perforations or holes therein of varying sizes and varying distances apart from each other. The smaller the area of the perforations or holes and the further apart they are from each other, the higher the impedance of a given area of the septum or the perforated face sheet. The impedance of the septum and/or the perforated face sheet may progressively increase in a direction away from the engine fan.

Abstract: A manufacturing method is adapted for materials that are susceptible to deformation during the manufacturing process, such as composite parts that change shape during curing. The method includes modifying a part design to compensate for changes in the shape of the part that occur during a curing phase of the manufacturing process. A manufacturing mold is created according to the modified part design, then a part is formed in the mold and cured in the mold. While the part is still in the mold after the curing phase, the part is finished according to the modified part design wherein excess material is removed and apertures are created. While the part is still in the mold after the finishing phase, the finished part is inspected using automated inspection equipment to confirm that the finished part conforms to the modified part design.