Abstract: An apparatus for aircraft anti-icing includes a nozzle body, at least one nozzle extending from the nozzle body, and at least one vane disposed in at least one of the nozzle(s), the at least one vane configured to impart rotational movement of a hot gas moving through the nozzle(s).

Abstract: Modular armor for a hard upper torso (HUT) of an atmospheric suit that maintains a specific atmosphere within the suit includes a first outer layer including a first surface and a second surface opposite the first surface and a second outer layer including a first surface and a second surface opposite the first surface. A core is sandwiched between the first surface of the first outer layer and the first surface of the second outer layer. The armor is fabricated such that the second surface of the first outer layer is conformally affixed to the HUT.

Abstract: An apparatus for aircraft anti-icing includes a nozzle body, a nozzle extending from the nozzle body, an eductor shroud at least partially surrounding the nozzle, the eductor shroud configured to focus a first flow of ambient air towards a first flow of hot gas exiting the first nozzle.

Abstract: An apparatus for aircraft anti-icing includes a nozzle head including an inner wall and an outer wall, the inner wall defining a through-hole extending through the nozzle, the outer wall circumscribing the inner wall, wherein a plenum is disposed between the inner wall and the outer wall, and a neck extending from the outer wall of the nozzle head, the neck configured to supply a flow of hot gas to the plenum, wherein a maximum width of the inner surface of the neck is less than a maximum width of the through-hole.

Abstract: An apparatus for aircraft anti-icing includes a nozzle body, a nozzle extending from the nozzle body, an eductor shroud at least partially surrounding the nozzle, the eductor shroud configured to focus a first flow of ambient air towards a first flow of hot gas exiting the first nozzle.

Abstract: An apparatus for aircraft anti-icing includes a nozzle body, at least one nozzle extending from the nozzle body, and at least one vane disposed in at least one of the nozzle(s), the at least one vane configured to impart rotational movement of a hot gas moving through the nozzle(s).

Abstract: An apparatus for aircraft anti-icing includes a nozzle head including an inner wall and an outer wall, the inner wall defining a through-hole extending through the nozzle, the outer wall circumscribing the inner wall, wherein a plenum is disposed between the inner wall and the outer wall, and a neck extending from the outer wall of the nozzle head, the neck configured to supply a flow of hot gas to the plenum, wherein a maximum width of the inner surface of the neck is less than a maximum width of the through-hole.

Abstract: A thrust reverser actuator gimbal assembly for mounting a thrust reverser actuator to fixed structure of the thrust reverser is disclosed. The thrust reverser actuator gimbal assembly may comprise a gimbal, first and second gimbal pins mounted to the gimbal and defining a first pivot axis, the first and second gimbal pins adapted to form a pivotal joint with the fixed structure of the thrust reverser, third and fourth gimbal pins mounted to the gimbal and defining a second pivot axis normal to the first pivot axis, the third and fourth gimbal pins adapted to form a pivotal joint with the thrust reverser actuator, wherein the first and second gimbal pins each include a shaft and a flange integrally formed together, the flange including a pair of bores for receiving a fastener to fasten the respective gimbal pin to the thrust reverser fixed structure.

Abstract: A thrust reverser actuator gimbal assembly for mounting a thrust reverser actuator to fixed structure of the thrust reverser is disclosed. The thrust reverser actuator gimbal assembly may comprise a gimbal, first and second gimbal pins mounted to the gimbal and defining a first pivot axis, the first and second gimbal pins adapted to form a pivotal joint with the fixed structure of the thrust reverser, third and fourth gimbal pins mounted to the gimbal and defining a second pivot axis normal to the first pivot axis, the third and fourth gimbal pins adapted to farm a pivotal joint with the thrust reverser actuator, wherein the first and second gimbal pins each include a shaft and a flange integrally formed together, the flange including a pair of bores for receiving a fastener to fasten the respective gimbal pin to the thrust reverser fixed structure.

Abstract: A fuel control system uses a fuel pump powered by a variable speed pump motor controlled by a closed loop electronic feedback system that tracks motor speed and corrects fuel pump motor speed so that the fuel pump delivers flow according to a desired flow schedule based on the pressure feedback from the manifold.

Abstract: An ignitor for setting off an incendiary device. The ignitor includes a container into one end of which is placed a charge of thermite. A shock tube is inserted into the other end of the container and when initiated, sends a shock wave into the container to cause ignition of the thermite. In order to prevent accidental ignition from an electrical charge, in a preferred embodiment an electrically conducting filler material surrounds the shock tube within the container, which preferably is crimped around the filler material.