Abstract: A method for testing a cooling system for use in a gas turbine engine control system is provided. The method includes connecting an inlet of the cooling system to a differential pressure sensor, connecting an outlet of the cooling system to the differential pressure sensor, and determining whether or not a difference in pressure exists between the inlet and outlet, wherein such a pressure difference is indicative of whether cooling fluid is flowing through the cooling system.
Abstract: A geometric morphing wing 12 is provided, including a rigid internal core 20 surrounded by an expandable spar 22 and covered by a wing surface overlay 24. The expandable spar 22 includes an elastomeric bladder 30 movable between a non-inflated state 26 and an inflated state 28 such that the airfoil shape 29 of the geometric morphing wing 12 is adjusted.