Hybrid electrical ice protection system and method including an energy saving mode
AssigneeHoneywell International Inc.
InventorsPhilip S. Chow, Jean-Luc Derouineau
Life of this patent
Estimating the term…
Abstract
A hybrid electrical ice protection system implements three ice protection methods in various combinations. The ice protection methods include the fully-evaporative anti-ice protection method, the wet running anti-ice protection method, and the de-ice method. The particular methods that are implemented vary, depending on the particular aircraft structure for which ice protection is being provided and on the power condition of the aircraft.
Claims30
An electrical ice protection system for an aircraft operable in at least a nominal power condition and an off-nominal power condition, and including a structure having at least an outer skin, the ice protection system comprising:
- a plurality of electrical heaters disposed at least proximate the aircraft structure outer skin and configured to heat at least a portion of the aircraft structure outer skin upon energization thereof, the plurality of electrical heaters including at least a first set of heaters and a second set of heaters;
- and
- a controller to determine whether the aircraft is in the nominal power condition or the off-nominal power condition, the controller coupled to each of the electrical heaters and in response to the determined power condition, to:
- selectively energize the first set of heaters in a manner that the first set of heaters are operated in a fully-evaporative anti-ice mode, and
- selectively energize the second set of heaters in a manner that the second set of heaters are operated in:
- (i) a wet running anti-ice mode, if the aircraft is in the nominal power condition, and
- (ii) a de-ice mode, if the aircraft is in the off-nominal power condition.
An electrical ice protection system for an aircraft operable in at least a nominal power condition and an off-nominal power condition, the aircraft including an engine nacelle having at least an inboard surface and an adjacent outboard surface, the inboard and outboard surfaces each including an outer skin, the ice protection system comprising:
- a first set of electrical heaters disposed proximate the engine nacelle inboard surface outer skin, the first set of heaters configured, upon energization thereof, to heat at least a portion of the engine nacelle inboard surface outer skin;
- a second set of electrical heaters disposed proximate the engine nacelle outboard surface outer skin, the second set of heaters configured, upon energization thereof, to heat at least a portion of the engine nacelle outboard surface outer skin;
- and
- a controller to determine whether the aircraft is in the nominal power condition or the off-nominal power condition, the controller coupled to the first and second set of electrical heaters and in response to the determined power condition, to:
- selectively energize the first set of electrical heaters in a manner that the first set of heaters are operated in a fully-evaporative anti-ice mode, and
- selectively energize the second set of electrical heaters in a manner that the second set of electrical heaters are operated in:
- (i) a wet running anti-ice mode, if the aircraft is in the nominal power condition, and
- (ii) a de-ice mode, if the aircraft is in the off-nominal power condition.
An electrical ice protection system for an aircraft operable in at least a nominal power condition and an off-nominal power condition, the aircraft including a wing having at least an upper surface and a lower surface, the upper and lower surfaces each including an outer skin, the ice protection system comprising:
- a first set of electrical heaters disposed proximate the wing upper surface outer skin, the first set of heaters configured, upon energization thereof, to heat at least a portion of the wing upper surface outer skin;
- a second set of electrical heaters disposed proximate the wing lower surface outer skin, the second set of heaters configured, upon energization thereof, to heat at least a portion of the wing lower surface outer skin;
- and
- a controller to determine whether the aircraft is in the nominal power condition or the off-nominal power condition, the controller coupled to the first and second set of electrical heaters and in response to the determined power condition, to:
- selectively energize the first set of electrical heaters in a manner that the first set of heaters are operated in a fully-evaporative anti-ice mode, and
- selectively energize the second set of electrical heaters in a manner that the second set of electrical heaters are operated in:
- (i) a wet running anti-ice mode, if the aircraft is in the nominal power condition, and
- (ii) a de-ice mode, if the aircraft is in the off-nominal power condition.
An electrical ice protection system for an aircraft operable in at least a nominal power condition and an off-nominal power condition, and including an engine nacelle and an aircraft wing, the engine nacelle having at least an inboard surface and an adjacent outboard surface, each with an outer skin, the aircraft wing including at least an upper surface and a lower surface, each with an outer skin, the ice protection system comprising:
- a first set of electrical heaters disposed proximate the engine nacelle inboard surface outer skin, the first set of heaters configured, upon energization thereof, to heat at least a portion of the engine nacelle inboard surface outer skin;
- a second set of electrical heaters disposed proximate the engine nacelle outboard surface outer skin, the second set of heaters configured, upon energization thereof, to heat at least a portion of the engine nacelle outboard surface outer skin;
- a third set of electrical heaters disposed proximate the aircraft wing upper surface outer skin, the third set of electrical heaters configured, upon energization thereof, to heat at least a portion of the wing upper surface outer skin;
- a fourth set of electrical heaters disposed proximate the aircraft wing lower surface outer skin, the fourth set of electrical heaters configured, upon energization thereof, to heat at least a portion of the wing lower surface outer skin;
- and
- a controller to determine whether the aircraft is in the nominal power condition or the off-nominal power condition, the controller coupled to the first, second, third, and fourth sets of electrical heaters and in response to the determined power condition, to:
- selectively energize the first and third sets of electrical heaters in a manner that the first and third sets of electrical heaters are operated in a fully-evaporative anti-ice mode, and
- selectively energize the second and fourth sets of electrical heaters in a manner that the second and fourth sets of electrical heaters are operated in:
- (i) a wet running anti-ice mode, if the aircraft is in the nominal power condition, and
- (ii) a de-ice mode, if the aircraft is in the off-nominal power condition.
Dependencies are inferred from the claim text.