Abstract: An aircraft landing assist apparatus is designed to be retrofit to existing aircraft having internal constructions that have been modified to support the apparatus. The apparatus is designed so that on rough landings of the aircraft on a ship deck, the apparatus will collapse in a controlled manner to avoid any damage to ammunition and/or fuel storage areas of the aircraft.

Abstract: An aircraft landing assist apparatus is designed to be retrofit to existing aircraft having internal constructions that have been modified to support the apparatus. The apparatus is designed so that on rough landings of the aircraft on a ship deck, the apparatus will collapse in a controlled manner to avoid any damage to ammunition and/or fuel storage areas of the aircraft.

Abstract: A method for applying pressure to the area of a composite part masked by a secondary feature comprises the steps of positioning a pressure augmentation strip in contact with the masked area, securing a pressure transfer wedge on each of two sides of the secondary feature, such that pressure is transferred to the pressure augmentation strip during co-curing/co-bonding, and co-curing/co-bonding the composite part and the secondary feature. When the area between the composite part and the secondary feature is fairly large, the method can comprise the further steps of positioning a sine wave spring between the pressure augmentation strip and the secondary feature, injecting a structural paste adhesive into the voids around the sine wave spring, and curing the structural paste.

Abstract: The present invention presents a system for packaging fire suppressing material. An outer membrane is configured to support and release a fire suppression material when impacted by a ballistic or incendiary round. An inner membrane is configured to support and release the fire suppression material when impacted by a ballistic or incendiary round, and the inner membrane and the outer membrane is connected to form at least one cell holding the fire suppression material. In accordance with other aspects of the invention, the inner and outer membranes suitably form a bubble pack filled with a fire suppression powder. Further, the inner and outer membranes may be combined with a lightweight honeycomb panel to form a lightweight and simple system to support fuel tanks.

Abstract: A method for applying pressure to the area of a composite part masked by a secondary feature comprises the steps of positioning a pressure augmentation strip in contact with the masked area, securing a pressure transfer wedge on each of two sides of the secondary feature, such that pressure is transferred to the pressure augmentation strip during co-curing/co-bonding, and co-curing/co-bonding the composite part and the secondary feature. When the area between the composite part and the secondary feature is fairly large, the method can comprise the further steps of positioning a sine wave spring between the pressure augmentation strip and the secondary feature, injecting a structural paste adhesive into the voids around the sine wave spring, and curing the structural paste.

Abstract: The present invention presents a system for packaging fire suppressing material. An outer membrane is configured to support and release a fire suppression material when impacted by a ballistic or incendiary round. An inner membrane is configured to support and release the fire suppression material when impacted by a ballistic or incendiary round, and the inner membrane and the outer membrane is connected to form at least one cell holding the fire suppression material. In accordance with other aspects of the invention, the inner and outer membranes suitably form a bubble pack filled with a fire suppression powder. Further, the inner and outer membranes may be combined with a lightweight honeycomb panel to form a lightweight and simple system to support fuel tanks.

Abstract: A tool for fabricating fiber reinforced resin matrix composite structures having molded outside surfaces with intermittent molded inside surfaces e.g. aircraft skin with internal stiffeners. The tool employs a hybrid vacuum bag with soft portions in combination with rigid portions to produce the internal stiffeners. The stiffeners are supported and shaped during curing by pressurized elastomeric tubes, in lieu of mandrels, which can be easily removed when collapsed. The stiffeners and skin can be made from wet lay-ups or prepregs, formed in place or preformed, and in combinations where one part is precured or both parts are co-cured.

Abstract: A method for fabricating fiber reinforced resin matrix composite structures having molded outside surfaces with intermittent molded inside surfaces (e.g. an aircraft skin with internal stiffeners) is performed as follows: composite prepreg stiffener sections are preformed and laid up on the inside portion of the rigid portion of the vacuum bag and the lay-up debulked. Elastomeric tubes are then installed in rigid cavity portions of a hybrid vacuum bag and sealing wedges are forced into place to hold the elastomeric tubes and at the same time seal them to the rigid portion of the cavity. The elastomeric tubes extend through and protrude from the sealing wedges. Skin plies are then laid up on a primary mold and the hybrid bag installed on the mold. Index pins are provided to properly orient the hybrid bag to the primary mold or tool. A vacuum is then drawn on the bag, any vacuum leaks are remedied, and the part is ready for curing in either an oven or an autoclave.