US 11,702,213 B2
Aircraft engine nacelle provided with an icing protection system and associated protection method
Alain Porte, Colomiers (FR); François Pons, Daux (FR); and Jonathan Carcone, Toulouse (FR)
Assigned to AIRBUS OPERATIONS SAS, Toulouse (FR)
Filed by Airbus Operations SAS, Toulouse (FR)
Filed on Apr. 8, 2019, as Appl. No. 16/377,813.
Claims priority of application No. 1853110 (FR), filed on Apr. 10, 2018.
Prior Publication US 2019/0308737 A1, Oct. 10, 2019
Int. Cl. B64D 15/22 (2006.01); B64D 15/12 (2006.01); B64D 29/00 (2006.01); H05B 1/02 (2006.01); H05B 3/00 (2006.01); B64D 15/20 (2006.01); F02C 7/047 (2006.01); B64D 33/02 (2006.01)
CPC B64D 15/22 (2013.01) [B64D 15/12 (2013.01); B64D 15/20 (2013.01); B64D 29/00 (2013.01); B64D 33/02 (2013.01); F02C 7/047 (2013.01); H05B 1/0236 (2013.01); H05B 3/0019 (2013.01); B64D 2033/0233 (2013.01)] 12 Claims
OG exemplary drawing
 
1. An aircraft engine nacelle comprising:
an air inlet comprising:
a lip,
a tubular air inlet piece, and
an icing protection system, said icing protection system comprising:
an icing prevention means powered continuously by a first electrical energy source and wholly or partly covering the lip and a de-icing means comprising an array of resistive heating elements, the array of resistive heating elements powered by a second electrical energy source, the de-icing means covering the tubular air inlet piece,
wherein the de-icing means further comprises a controller:
wherein the controller acquires a current total air temperature value, and
the controller controls the second electrical energy source as a function of the current total air temperature value.
 
12. An aircraft engine nacelle comprising:
an air inlet comprising:
a lip,
a tubular air inlet piece, and
an icing protection system, said icing protection system comprising:
an icing prevention means powered continuously by a first electrical energy source and wholly or partly covering the lip and a de-icing means, powered by a second electrical energy source, covering the tubular air inlet piece,
wherein the de-icing means further comprises a controller configured to:
acquire a current total air temperature value, and
control the second electrical energy source as a function of the current total air temperature value, and
wherein the de-icing means further comprises a thermal jacket comprising:
a core comprising resistive heating elements powered by the second electrical energy source;
a first layer of glass fiber on one side of the core,
a second layer of glass fiber on a second side of the core, and
a thermal insulation secured to the second layer of glass fiber by a first adhesive,
wherein the thermal jacket is secured to the part to the tubular air inlet piece by a second adhesive.