Thermal control systems for aircraft landing gear wheel wells and related methods

• Main Authors: Clark, Andrew David, Calkins, Frederick T, Mitchell, Bradley J, Al-Alusi, Thamir Rauf, Kirkbride, David William
• Format: Patent
• Language: English
• Published: 05.03.2024
• Subjects: AEROPLANES; AIRCRAFT; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT; AVIATION; BLASTING; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; BRAKES; CLUTCHES; COSMONAUTICS; COUPLINGS FOR TRANSMITTING ROTATION; ENGINEERING ELEMENTS AND UNITS; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS; HEATING; HELICOPTERS; LIGHTING; MECHANICAL ENGINEERING; PARACHUTES; PERFORMING OPERATIONS; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OFVEHICLES; THERMAL INSULATION IN GENERAL; TRANSPORTING; VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES; VEHICLES IN GENERAL; WEAPONS

Thermal control system for aircraft main landing gear wheel wells and related methods are disclosed. An example thermal control system includes a conduit defining a fluid passageway between an inlet and an outlet. The inlet of the conduit positioned in fluid communication with a landing gear wheel well and the outlet of the conduit positioned in fluid communication with the atmosphere. The conduit generates a pressure differential through the fluid passageway between the inlet and the outlet to exhaust heat from the landing gear wheel well to the atmosphere.