A thermal management system for managing the temperature of an aircraft wing comprises a gas flow path comprising a first flow path portion 224a and a second flow path portion 224b, the first flow path portion directs a flow of gas at least proximal to an aircraft component 22 for managing the component temperature, the second flow path portion receives the flow of gas from the first flow path portion and directs the flow of gas to the wing for managing the temperature of the wing for ice protection. Also provided is a method. The second flow path may extend through the leading edge of the wing. The system may comprise a temperature sensor 242 for sensing the temperature of the wing, a flow control system selectively controlling the mass flow along the second flow path portion as a function of the sensed temperature. The component may be an electric motor, a generator, power electronics.
ELECTRIC AIRCRAFT PROPULSION SYSTEM
ANTRIEBSSYSTEM FÜR EIN ELEKTRISCHES FLUGZEUG
SYSTÈMES, AGENCEMENTS, STRUCTURES ET PROCÉDÉS ASSOCIÉS À UN AÉRONEF
2022-09-28
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |