US 11,939,076 B2
Avionic exhaust air for cooling engine bay
Giuseppe S. Alberti, Shelton, CT (US); Adriano Cirioli, North Haven, CT (US); Sean Thomas Barrows, Stratford, CT (US); Nolan John Birtwell, Southbury, CT (US); Michael Alexander, Bridgeport, CT (US); and Nicholas Scott Coury, Shelton, CT (US)
Assigned to LOCKHEED MARTIN CORPORATION, Bethesda, MD (US)
Filed by Lockheed Martin Corporation, Bethesda, MD (US)
Filed on Sep. 1, 2021, as Appl. No. 17/464,532.
Prior Publication US 2023/0060791 A1, Mar. 2, 2023
Int. Cl. B64D 33/08 (2006.01); A62C 3/08 (2006.01); F01P 7/02 (2006.01)
CPC B64D 33/08 (2013.01) [A62C 3/08 (2013.01); F01P 7/026 (2013.01); F01P 2050/20 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An aircraft, comprising:
an airframe defining a first enclosed space;
an engine bay disposed within the first enclosed space, the engine bay comprising:
a firebox defining a second enclosed space; and
an engine disposed at least partially within the second enclosed space; and
a cooling system configured to selectively fluidly couple the first enclosed space with the second enclosed space, wherein the cooling system comprises:
a valve repositionable between an open position and a closed position;
a valve actuator coupled to the valve;
a user interface; and
a fire suppression controller communicably coupled to the valve actuator and the user interface, the fire suppression controller configured to:
receive an arm command from the user interface;
transmit a control signal to the valve actuator to move the valve from the open position to the closed position in response to receiving the arm command; and
transmit a notification to the user interface that indicates a position of the valve.