US 11,919,647 B2
Thermal control systems for aircraft landing gear wheel wells and related methods
Andrew David Clark, Mill Creek, WA (US); Thamir Rauf Al-Alusi, Hayward, CA (US); David William Kirkbride, Allyn, WA (US); Frederick T. Calkins, Renton, WA (US); and Bradley J. Mitchell, Snohomish, WA (US)
Assigned to The Boeing Company, Arlington, VA (US)
Filed by The Boeing Company, Chicago, IL (US)
Filed on May 15, 2020, as Appl. No. 16/875,704.
Prior Publication US 2021/0354831 A1, Nov. 18, 2021
Int. Cl. B64D 13/02 (2006.01); B60T 5/00 (2006.01); B64C 25/00 (2006.01); B64C 25/42 (2006.01); F16D 65/78 (2006.01)
CPC B64D 13/02 (2013.01) [B60T 5/00 (2013.01); B64C 25/001 (2013.01); B64C 25/42 (2013.01); F16D 65/78 (2013.01)] 23 Claims
OG exemplary drawing
 
1. A thermal control system for use with an aircraft, the thermal control system comprising:
a thermal protection plate to be positioned in a landing gear wheel well and above a landing gear of an aircraft;
a lip extending from the thermal protection plate, the lip surrounding a perimeter of the thermal protection plate to define a cavity to align with one or more wheels of the landing gear when the landing gear is in a retracted position, the cavity to receive heat from the one or more wheels of the landing gear when the landing gear is in the retracted position, the lip to restrict heat from spilling over the perimeter of the thermal protection plate and rising toward a structure of the aircraft; and
a pipe defining a fluid passageway between an inlet and an outlet, the inlet of the pipe positioned in fluid communication with the cavity, the outlet of the pipe positioned in fluid communication with the atmosphere, the pipe to generate a pressure differential through the fluid passageway between the inlet and the outlet to exhaust heat from the cavity to the atmosphere.