US 10,011,363 B2 · Anti-icing / de-icing system for aircraft door and aircraft door equipped with such a system

Abstract

The invention aims to make aircraft doors easier to open by preventing ice formation or, at the very least, favoring rapid breaking of the ice on the door edges connected to the skin of the fuselage. To that end, it is provided to supply energy along the door when specific conditions are met. According to one embodiment, an anti-icing/de-icing system for an aircraft door (1) according to the invention includes an excitation energy source and devices (81 to 83) for dissipating such energy extending parallel to a side surface (11) of the aircraft door (1), along a sealing gasket (4) support (5) secured to the door (1) across from a fuselage (2) side surface (21) framing (20) the door (1). The sealing gasket (4) of the door (1) is compressed against bearing (6) from a side surface (25) of the fuselage (2) when the door (1) is closed.

Claims16

Dependent claims

An anti-icing and/or de-icing method for an aircraft door (1, 1′), the aircraft door having a closed position wherein the aircraft door is surrounded by a fuselage (2, 2′) of an aircraft and, wherein a sealing joint (4, 4′) is located at a junction (J, J′) between the aircraft door and the fuselage, the method comprising the steps of:

releasing an excitation energy along at least one support (5, 21′) which at least partially follows and retains the sealing joint (4, 4′) in the junction and
starting the releasing of the excitation energy when a control processor receives information that engines of the aircraft are in operation and an external temperature is less than or substantially equal to a reference temperature.

An anti-icing and/or de-icing system for an aircraft door (1, 1′) of an aircraft, the aircraft provided with engines, a fuselage and a central control unit, the system comprising:

a control processor connected to the central control unit to receive pieces of information involving temperature and pieces of information involving the operation of the engines,
a sealing joint (4,4′) located at a junction (J, J′) between the aircraft door and the fuselage,
a source of excitation energy, and
excitation energy conductors (81 to 83;
81′, 82′) extending parallel with at least a portion of the sealing joint (4, 4′) to release excitation energy at the junction,
wherein the control processor controls the system to release excitation energy based on the pieces of information involving temperature and the pieces of information involving the operation of the engines.

3 more elements

Dependencies are inferred from the claim text.

Anti-icing / de-icing system for aircraft door and aircraft door equipped with such a system

Life of this patent

Anti-icing / de-icing system for aircraft door and aircraft door equipped with such a system

Life of this patent

Abstract

Claims16