Abstract: A load limiting break away arrangement for a subsea umbilical includes telescoping inner and outer bodies. The inner body includes multiple cross-bored holes; the outer body has slotted openings on its top and bottom sides. A shearing blade is positioned at one end of a top slot of the outer body. Individual umbilical tubes pass through a bottom slot of the outer body, through individual holes in the inner body and out a top slot of the outer body for attachment to multiple quick connect couplers on an umbilical termination head of an Umbilical Termination Assembly (UTA) and of an Electro-Hydraulic Distribution Module (EHDM). Tension resistant actuation members run between the UTA and EHDM so that when a snag of an umbilical occurs, the inner and outer bodies are pulled apart and the tubes are severed one by one by the blade of the outer body.

Abstract: A flow diverting mechanism for the twin duct offtakes or coannular offtake for a turbo fan engine powering aircraft with either thrust reversing or short takeoff and vertical landing or both capabilities includes a rotary drum mounted between the turbine and afterburner sections and includes ports complementing the inlets in the offtakes to divert the core stream through the offtakes and passages to proportion the fan discharge air utilized for cooling purposes in the engine to cool the liner and walls of the offtakes and the engine components located downstream of the rotary drum while assuring separation of the core stream flow and fan air flow.

Abstract: A flow diverting mechanism for the twin duct offtakes or coannular offtake for a turbo fan engine powering aircraft with either thrust reversing or short takeoff and vertical landing or both capabilities includes a rotary drum mounted between the turbine and afterburner sections and includes ports complementing the inlets in the offtakes to divert the core stream through the offtakes and passages to proportion the fan discharge air utilized for cooling purposes in the engine to cool the liner and walls of the offtakes and the engine components located downstream of the rotary drum while assuring separation of the core stream flow and fan air flow.

Abstract: Exit area control panels 18 are supported for movement at an angle with respect to the nozzle axis 12. A varying exit area is formed as actuator 26 axially positions the panels 18. In each exit area control panel 18, there is slidably supported a throat area control panel 28, driven by actuator 32. A sliding throat is achieved as the two panels 18,28 are moved in each quadrant. Yaw and pitch vectoring is accomplished with selective positioning of the two panels.