초록 ▼

The ice prevention system of the present invention utilizes, in combination, a de-ice subsystem and anti-ice subsystem in a new configuration on an aircraft with engines located behind its wings. Depending on the vertical location of the engines with respect to the wings, the anti-ice subsystem is c

The ice prevention system of the present invention utilizes, in combination, a de-ice subsystem and anti-ice subsystem in a new configuration on an aircraft with engines located behind its wings. Depending on the vertical location of the engines with respect to the wings, the anti-ice subsystem is configured on an upper or lower portion of a leading edge of the wings. If the engine is located above the wing, the anti-ice system is configured only on a section of the wing aligned with the engine and only on the upper portion of the leading edge. If the engine is located below the wing, the placement of anti-ice system is reversed. The de-ice subsystem is configured on the opposite portion of the leading edge adjacent to the anti-ice subsystem and on the remainder of the leading edge of the wing.

대표청구항 ▼

1. An aircraft, comprising: a fuselage defining a longitudinal center axis of the aircraft;first and second wings extending from opposite sides of the fuselage, each wing defining a leading edge, said each wing further defining first and second sections along a length thereof;a first engine offset f

1. An aircraft, comprising: a fuselage defining a longitudinal center axis of the aircraft;first and second wings extending from opposite sides of the fuselage, each wing defining a leading edge, said each wing further defining first and second sections along a length thereof;a first engine offset from the center axis on a first side of the fuselage and generally rearward of the first wing leading edge, said first engine being disposed on a first vertical side of the first wing;a second engine offset from the center axis on a second, opposite side of the fuselage and generally rearward of the second wing leading edge, said second engine being disposed on the first vertical side of the second wing;an anti-ice subsystem configured solely along a first portion of the leading edge of the first section of each wing, wherein the first sections are aligned with the first and second engines on the first and second wings, and wherein the first portion is only on the first vertical side of the first and second wings; anda subsystem, capable of performing a de-icing function only, configured on the first section of each wing solely along a second portion, opposite the anti-ice subsystem, said second portion being on a second vertical side of the first and second wings;wherein the anti-ice subsystem prevents ice from forming on, and subsequently detaching from, the wing at a location where said detached ice can contact the first and second engines and the de-ice subsystem allows ice to form on, and be subsequently detached from the wing at a location where detaching ice passes around the first and second engines. 2. The aircraft of claim 1, wherein the de-ice subsystem is disposed along the second vertical side of the leading edge of the entire first section of each wing. 3. The aircraft of claim 1, wherein the second section is located farther from the fuselage than the first section and wherein only a de-ice subsystem is additionally configured along the leading edge of the second section of each wing. 4. The aircraft of claim 3, wherein the leading edge of the first section is configured at a first angle with respect to the center axis of the fuselage and the second section is configured at a second, different angle with respect to the center axis of the fuselage. 5. The aircraft of claim 1, wherein the first section of each wing is directly adjacent to the aircraft fuselage. 6. The aircraft of claim 5, wherein the second section extends from a distal end of the first section to an end of the wing. 7. The aircraft of claim 1, wherein the first and second engines are secured to the fuselage. 8. The aircraft of claim 1, wherein the first engine is secured to the first wing and the second engine is secured to the second wing. 9. The aircraft of claim 1, wherein the anti-ice subsystem is an electric heater type. 10. The aircraft of claim 1, wherein the anti-ice subsystem is a hot bleed type. 11. The aircraft of claim 1, wherein the de-ice subsystem is an inflatable bladder type. 12. An aircraft, comprising: a fuselage defining a longitudinal center axis of the aircraft;first and second wings extending from opposite sides of the fuselage, each wing defining a leading edge, said each wing further defining first and second sections along a length thereof;a first engine offset from the center axis on a first side of the fuselage and generally rearward of the first wing leading edge, said first engine being disposed on a first vertical side of the first wing;a second engine offset from the center axis on a second, opposite side of the fuselage and generally rearward of the second wing leading edge, said second engine being disposed on the first vertical side of the second wing;an anti-ice subsystem configured solely along a first portion of the leading edge of the first section of each wing, wherein the first sections are aligned with the first and second engines on the first and second wings, and wherein the first portion is only on the first vertical side of the first and second wings; anda subsystem, capable of performing a de-icing function only, configured along a second portion, opposite the anti-ice subsystem, of the leading edge of the first section of each wing, said second portion being on a second vertical side of the first and second wings;wherein a second section is located farther along the length of the wing from the fuselage than the first section and wherein only a de-ice subsystem is additionally configured along the leading edge of the second section of each wing; andwherein the anti-ice subsystem prevents ice from forming on the portion of the leading edge of each aircraft wing that is on a side of the wing that is adjacent to the position of an aircraft engine. 13. The ice protection system of claim 12, wherein the one vertical side of the leading edge of the aircraft wing is an upper side. 14. The aircraft of claim 12, wherein the first section of each wing is directly adjacent to the aircraft fuselage. 15. The aircraft of claim 12, wherein the second section extends from a distal end of the first section to an end of the wing. 16. The aircraft of claim 12, wherein the leading edge of the first section is configured at a first angle with respect to the center axis of the fuselage and the second section is configured at a second, different angle with respect to the center axis of the fuselage. 17. The aircraft of claim 12, wherein the anti-ice subsystem is an electric heater type.