Abstract: A system and method for a number of backup systems in an aircraft. The apparatus comprises a movement system; a latch system; a lock system; and at least one of a backup valve, a backup actuator, or a backup power source connected to at least one of the movement system, the latch system, or the lock system. The movement system has a first number of actuators and is connected to a hydraulic power source. The latch system has a second number of actuators and is connected to the hydraulic power source. The lock system has a third number of actuators and is connected to the hydraulic power source.

Abstract: A wing fold system of a wing of an aircraft. The system may include a first lock of a latch to prevent movement of a latch pin of the latch to prevent movement of an unfixed portion of the wing with respect to a fixed portion of the wing, the first lock may include a first cam configured to prevent the second lock from transitioning to a second engaged position until the first lock may be in a first engaged position via contact with a second cam of the second lock. A second lock of the latch, the second lock may include the second cam configured to prevent the first lock from transitioning away from the first engaged position until the second lock transitions away from the second engaged position.

Abstract: Illustrative embodiments may provide for an apparatus and method of controlling the folding of a wing. The apparatus may include a sensor, an actuator, and a wing fold controller. The method may include receiving a status of at least one of an aircraft and a wing fold system of the aircraft by the wing fold controller of the wing fold system. The method may also include receiving an automated command by the wing fold controller in response to receiving the status. The method may also include operating the wing fold system by the wing fold controller based on the automated command and the status. The method may also include transitioning a wingtip of a wing of the aircraft to one of a flight position and an on-ground position by an actuator of the wing fold system in response to commands from the wing fold controller.

Abstract: A wing fold system of a wing of an aircraft. The system may include a first lock of a latch to prevent movement of a latch pin of the latch to prevent movement of an unfixed portion of the wing with respect to a fixed portion of the wing, the first lock may include a first cam configured to prevent the second lock from transitioning to a second engaged position until the first lock may be in a first engaged position via contact with a second cam of the second lock. A second lock of the latch, the second lock may include the second cam configured to prevent the first lock from transitioning away from the first engaged position until the second lock transitions away from the second engaged position.

Abstract: A method and apparatus for controlling a movement of a control surface comprises a first linkage system, a second linkage system, and an actuator system. The first linkage system is connected to a first location of a control surface. The second linkage system is connected to a second location of the control surface. The first location is closer to a leading edge of the control surface than the second location. The actuator system is configured to move the first linkage system and the second linkage system.

Abstract: Disclosed is a closed-cell polyisocyanurate foam composition capable of high compressive strength at temperatures up to 200° C. The new composition further exhibits no loss or degradation in conventional mechanical properties—less than that which impacts the intended use. The formulation of the present invention is based on the reaction product of a isocyanate and an epoxide resin catalyzed by a mixture of a tertiary amine and a cyclic amine. Compressive strength is augmented by incorporating a large fraction of a non-reactive bulk filler into the precursor polymer gel.

Abstract: Disclosed is a closed-cell polyisocyanurate foam composition capable of high compressive strength at temperatures up to 200° C. The new composition further exhibits no loss or degradation in conventional mechanical properties—less than that which impacts the intended use. The formulation of the present invention is based on the reaction product of a isocyanate and an epoxide resin catalyzed by a mixture of a tertiary amine and a cyclic amine. Compressive strength is augmented by incorporating a large fraction of a non-reactive bulk filler into the precursor polymer gel.

Abstract: A method of brazing together a lightweight metallic aerostructure sandwich panel having at least two spaced face sheets and an intermediate honeycomb core layer comprises: providing a tooling base having a determinable upper surface; assembling spaced upper and lower metal face sheets and an intermediate metal honeycomb core layer together with at least one layer of braze material upon the upper surface of the tooling base to provide an unbrazed aerostructure panel; positioning a layer of conformable working honeycomb core upon the upper face sheet; positioning apressure means upon the layer of conformable working honeycomb core to provide downward pressure upon the layer of conformable working honeycomb core and causing the conformable working honeycomb core to provide a uniform downward pressure over the upper face sheet of the unbrazed aerostructure panel; and subjecting the unbrazed aerostructure panel to a predetermined cycle of elevated temperature and time to permit the layer of braze material to