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US 10,696,412 B2Granted
Combined fluid ice protection and electronic cooling system
AssigneeThe Boeing Company
InventorSteve G Mackin
Life of this patent
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Abstract
A method and apparatus combining an aircraft wing and engine ice protection system with an aircraft electronic cooling system.
Claims20
An ice protection system for an aerodynamic surface of an aircraft, the ice protection system comprising:
- a reservoir;
- an electronics cooling system connected to the reservoir and comprising a first conduit, wherein:
- the electronics cooling system distributes coolant from the reservoir through the first conduit in thermal contact with electronics, whereby
- heat is transferred from the electronics to the coolant;
- a pump operatively coupled to the reservoir;
- and
- a second conduit in communication with the pump and including an outlet disposed at the aerodynamic surface located on an outside of the aircraft, wherein the pump pumps the coolant onto the aerodynamic surface and the coolant reduces or prevents ice formation on the aerodynamic surface.
4 more elements
A method of manufacturing, refitting, or servicing an aircraft, comprising:
- mounting an electronics cooling apparatus distributing coolant for cooling electronics comprising an air conditioning unit on an aircraft;
- and
- mounting an ice protection apparatus on the aircraft and connecting the ice protection apparatus to the electronics cooling apparatus, wherein the ice protection apparatus receives the coolant from the electronics cooling apparatus and distributes the coolant onto the aerodynamic surface outside of the aircraft, the coolant reducing and removing ice formation on the aerodynamic surface of the aircraft, wherein the coolant distributed to the aerodynamic surface comprises at least a portion of heat transferred from the air conditioning unit.
A method of operating an aircraft, comprising:
- providing an aircraft comprising an ice protection system, the ice protection system comprising
- a reservoir;
- an electronics cooling system connected to the reservoir and comprising a first conduit, wherein:
- the electronics cooling system distributes coolant from the reservoir through the first conduit in thermal contact with electronics, whereby
- heat is transferred from the electronics to the coolant;
- a pump operatively coupled to the reservoir;
- and
- a second conduit in communication with the pump and including an outlet disposed at an aerodynamic surface located on an outside of the aircraft, wherein the pump pumps the coolant onto the aerodynamic surface and the coolant reduces or prevents ice formation on the aerodynamic surface;
- providing instructions allowing higher thrust for the aircraft in icing conditions, as compared to the aircraft without the ice protection system;
- and
- providing instructions allowing an operation of the ice protection system while the aircraft is parked.
8 more elements
Dependencies are inferred from the claim text.