Aircraft Fuselage Heating
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Abstract
A method of heating an aircraft fuselage comprises the step of supplying heat energy to air occupying an interior space enclosed by an aircraft fuselage shell structure so as to drive moisture from air in a region disposed immediately adjacent the structure to air in a region disposed from the structure within the enclosed space (20), thereby substantially preventing ice formation on the interior of the structure when the exterior of the structure is exposed to temperatures in the region of −35° C. to −85° C. The heat energy may be supplied by either a heater mat or a heat pipe assembly (16) in an aircraft fuselage.
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Citations
51 Claims
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1-34. -34. (canceled)
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35. An aircraft fuselage comprising:
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an aircraft fuselage shell structure enclosing an interior space; and a heater disposed in the enclosed space adjacent the aircraft fuselage shell structure for supplying heat energy to air occupying the enclosed space, wherein the heater is a heater mat comprising one or more heating elements supported by a support layer, the support layer being permeable to water vapour and impermeable to water droplets; and wherein the heater mat is adapted to drive moisture from air in a region disposed immediately adjacent the structure to air in a region disposed from the structure within the enclosed space, thereby substantially preventing ice formation on the interior of the structure when the exterior of the structure is exposed to temperatures in the region of −
35°
C. to −
85°
C. - View Dependent Claims (36, 37, 38, 39, 40, 41, 42, 43, 44, 45)
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46. A method of heating an aircraft fuselage, comprising the step of supplying heat energy to air occupying an interior space enclosed by an aircraft fuselage shell structure so as to drive moisture from air in a region disposed immediately adjacent the structure to air in a region disposed from the structure within the enclosed space, thereby substantially preventing ice formation on the interior of the structure when the exterior of the structure is exposed to temperatures in the region of −
- 35°
C. to −
85°
C., wherein the heat energy is supplied by energising a heater mat comprising one or more heating elements supported by a support layer disposed adjacent the aircraft fuselage shell structure, the support layer being permeable to water vapour and impermeable to water droplets. - View Dependent Claims (47, 48, 49, 50, 51)
- 35°
Specification