Abstract: A method of fabricating a bonded cascade assembly of a thrust reverser for an aircraft nacelle. The method may include inserting individual turning vanes between spaced apart elongated stiffeners at an aft end thereof and sliding the turning vanes toward a front frame piece attached to or integrally formed with forward ends of the elongated stiffeners. The elongated stiffeners may have inner and outer flanges for trapping and limiting radial movement of the turning vanes. The method may further include bonding the turning vanes to the structural frame with a structural adhesive and attaching a closeout cap to the aft ends of each of the elongated stiffeners.

Abstract: A method of fabricating a bonded cascade assembly of a thrust reverser for an aircraft nacelle. The method may include inserting individual turning vanes between spaced apart elongated stiffeners at an aft end thereof and sliding the turning vanes toward a front frame piece attached to or integrally formed with forward ends of the elongated stiffeners. The elongated stiffeners may have inner and outer flanges for trapping and limiting radial movement of the turning vanes. The method may further include bonding the turning vanes to the structural frame with a structural adhesive and attaching a closeout cap to the aft ends of each of the elongated stiffeners.

Abstract: A method and aerodynamic device for modifying at least one vane of a cascade thrust reverser. One or more of the aerodynamic devices may be formed and attached to forward-facing surfaces of vanes of the thrust reverser. The aerodynamic device may include a first side shaped to rest flush against at least a portion of the forward-facing surface of the vane, a second side opposite of the first side, a ledge portion protruding from the first side and configured to rest flush against a blunt leading edge of the vane, a rounded first end portion extending from the ledge portion to the second side of the aerodynamic device, and a second end opposite of the first end portion at which the first side and the second side converge. The aerodynamic device changes the size and contour of airflow channels between the vanes, increase the efficiency of the thrust reverser.

Abstract: Latch beams and hinge beams of an aircraft thrust reverser and a method for manufacturing the beams. The latch and hinge beams may comprise a plurality of hollow composite tubes joined with a plurality of machined metal fittings in alternating succession. The metal fittings may comprise at least one of hinge fittings and latching fittings. The latch and hinge beams may further comprise slider tracks configured to slidably attach to a translating sleeve of the thrust reverser. The hinge beams may each be rotatably attached to an engine strut or pylon of the aircraft, and the latch beams may each be mechanically latched with each other. Each of the latch and hinge beams may also be fixedly attached to an inner engine cowling of the thrust reverser.

Abstract: A thrust reverser comprises a translating sleeve, a torque beam, a plurality of cascades, a plurality of blocker doors, and a plurality of actuators. The translating sleeve is positioned at the rear of an aircraft nacelle and is translated rearward during thrust reverser deployment. The torque beam is positioned within the nacelle and configured to prevent airflow into the nacelle during thrust reverser deployment. The plurality of cascades are positioned around the circumference of the torque beam during thrust reverser stowage and are translated rearward during thrust reverser deployment. The plurality of blocker doors are positioned in alignment with the plurality of cascades and direct airflow through the plurality of cascades during thrust reverser deployment. The plurality of actuators are coupled to the forward edge of the sleeve and configured to translate the sleeve rearward during thrust reverser deployment.

Abstract: A method and aerodynamic device for modifying at least one vane of a cascade thrust reverser. One or more of the aerodynamic devices may be formed and attached to forward-facing surfaces of vanes of the thrust reverser. The aerodynamic device may include a first side shaped to rest flush against at least a portion of the forward-facing surface of the vane, a second side opposite of the first side, a ledge portion protruding from the first side and configured to rest flush against a blunt leading edge of the vane, a rounded first end portion extending from the ledge portion to the second side of the aerodynamic device, and a second end opposite of the first end portion at which the first side and the second side converge. The aerodynamic device changes the size and contour of airflow channels between the vanes, increase the efficiency of the thrust reverser.

Abstract: Latch beams and hinge beams of an aircraft thrust reverser and a method for manufacturing the beams. The latch and hinge beams may comprise a plurality of hollow composite tubes joined with a plurality of machined metal fittings in alternating succession. The metal fittings may comprise at least one of hinge fittings and latching fittings. The latch and hinge beams may further comprise slider tracks configured to slidably attach to a translating sleeve of the thrust reverser. The hinge beams may each be rotatably attached to an engine strut or pylon of the aircraft, and the latch beams may each be mechanically latched with each other. Each of the latch and hinge beams may also be fixedly attached to an inner engine cowling of the thrust reverser.

Abstract: A thrust reverser comprises a translating sleeve, a torque beam, a plurality of cascades, a plurality of blocker doors, and a plurality of actuators. The translating sleeve is positioned at the rear of an aircraft nacelle and is translated rearward during thrust reverser deployment. The torque beam is positioned within the nacelle and configured to prevent airflow into the nacelle during thrust reverser deployment. The plurality of cascades are positioned around the circumference of the torque beam during thrust reverser stowage and are translated rearward during thrust reverser deployment. The plurality of blocker doors are positioned in alignment with the plurality of cascades and direct airflow through the plurality of cascades during thrust reverser deployment. The plurality of actuators are coupled to the forward edge of the sleeve and configured to translate the sleeve rearward during thrust reverser deployment.

Abstract: A connector for securing components is disclosed. A hooked portion extending axially from a first device engages a cavity portion within a second, receiving device. A fastener within the first device is secured to said hooked portion in a transverse direction, and through transverse tightening secures the first and second devices together.

Abstract: A protective cap for a rotatably-adjustable electrical component mounted to a PW board in an enclosed electronic control unit. The housing of the electronic control unit has a tuning access hole axially aligned with a tapered lead-in port in the center of the protective cap. An adjustment tool is inserted into the tuning access hole and guided into a tuning slot in the adjustable electrical component by the tapered lead-in port in the cap. The cap also protects the rotatable component from damage by a poorly-aimed adjustment tool. The several caps covering the rotatable components on a board as well as the access openings of the housing may be color-coded to assist in component identification.

Abstract: An improved portable two-way radio comprises a systems module and a removably connected, shielded RF module. Split universal device connector apparatus is provided having an RF connector portion associated entirely with the shielded RF module and a control connector portion associated entirely with the control module, the RF and control connector portions being located physically proximate to each other so that a single multi-pronged universal device connector can be electrically and mechanically connected to both the RF connector circuitry through the control systems module.

Abstract: An improved arrangement for powering a two-way portable radio or the like comprises rechargable battery cells and sets of power input and output contacts interconnected to each other and the battery cells in such a way that the output contacts may be electrically connected to the battery cells for powering the radio, or to the input contacts for receiving power directly from a battery charger for dead battery operation while simultaneously recharging the battery cells, all battery pack contacts being electrically isolated from the battery cells in the latter mode of operation.

Abstract: An externally connectable control unit for a portable radio includes an array of contacts matching a similar array of contacts on a portable radio. At lest one control switch is electrically connected with such connector contacts and disposed internally of a switch housing structure. The internal switch is located in association with a recess formed in the housing and a removable plug is friction-fitted within the recess so as to establish a first electrical condition of the control switch--but which is also capable of being manually pulled out of the recess to establish a second electrical condition of the control switch. The meaning to be associated with the switch is determined by a programming device in the control unit which interfaces with the portable radio circuits and is utilized to perform predetermined radio functions. One or more additional switches may also be located on the switch housing (e.g.