초록
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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),...
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.
대표
청구항
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1. 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 andstarting the releasing of the excitation energy when a control ...
1. 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 andstarting 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. 2. The method as claimed in claim 1, wherein the excitation energy is released at a door edge (10) along at least one lateral face (11, 12, 13) of the aircraft door (1, 1′), and/or along a lateral face (21, 22, 23, 25) of the fuselage (2, 2′) parallel with the door edge (10). 3. The method as claimed in claim 2, wherein the excitation energy is selected from the group consisting of a thermal energy, a vibration energy, an electro-expulsive energy, and a pneumatic energy. 4. The method as claimed in claim 3, wherein the thermal energy is implemented by an electric current. 5. The method as claimed in claim 3, wherein the pneumatic energy is implemented by a current of pressurized hot air. 6. The method as claimed in claim 1, wherein an anti-icing solution is vaporized along a door edge of the aircraft door. 7. 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, andexcitation 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. 8. The system as claimed in claim 7, wherein the aircraft door (1, 1′), excitation energy conductors extend parallel with at least one lateral face (11, 12, 13) of the aircraft door (1, 1′), along a support (5, 5′) of the sealing joint (4, 4′) which is fixedly joined to the door (1, 1′) facing a lateral face (21, 22, 23; 21′) of the fuselage (2, 2′) of a frame (20, 20′) of the door (1, 1′) and/or along a lateral face (21, 22, 23; 21′) of the fuselage (2, 2′), andthe sealing joint (4, 4′) of the door (1, 1′) becoming compressed against an abutment (6, 90) formed on a lateral face (25, 25′) of the fuselage (2, 2′). 9. The system as claimed in claim 7, wherein the excitation energy conductors are comprised of at least one insulated electrical conductor (81 to 83; 81′, 82′) which extends along a support (5, 5′) of the sealing joint (4, 4′), and/oralong a lateral fuselage face (21′), andthe source of excitation energy is a source of electric voltage which transmits a current having an intensity which is suitable for heating the excitation energy conductors to a temperature which does not exceed a predetermined upper value. 10. The system as claimed in claim 8, wherein the support (5, 5′) of the sealing joint (4, 4′) is produced from a material which is selected from a material having epoxy carbon fibers, composite fibers, and fibers based on silicone and elastomer materials, andthe excitation energy conductors are (81 to 83; 81′, 82′) formed by a filament (61 to 63) of metal alloy which is received within a sheath of electrically insulating material (71 to 73), the excitation energy conductors (81 to 83; 81′, 82′) being fixedly joined at least partially to or in the support (5, 5′). 11. The system as claimed in claim 7, wherein the excitation energy conductors are constituted by ultrasound transmitters and the energy source is an ultrasound source. 12. The system as claimed in claim 7, wherein the excitation energy conductors are constituted by dissipation loops of an electro-repulsive energy which is produced by a source of electrical pulses. 13. The system as claimed in claim 7, wherein the source of excitation energy is constituted by a jet of pressurized hot air which is supplied by a preheated air compressor as an energy source. 14. The system as claimed in claim 7, wherein anti-adhesive layers are deposited on a skin of the door (1e′) and a skin (2e′) of the fuselage in a region of the junction (J, J′) between the door (1, 1′) and the fuselage (2, 2′), wherein the anti-adhesive layers are nano-coatings (7a, 7b) which are chemically connected to the skins (1e′, 2e′) and/or a strip of electricity conducting paint which is connected to a voltage source (60). 15. The system as claimed in claim 9, wherein the at least one insulated electrical conductor extends in a protection rim of the support. 16. The system as claimed in claim 7, where the excitation energy conductors are further arranged in a region of at least one joint of a piece of equipment of the aircraft selected from passenger doors, outer door handles and vent panels.
