초록 ▼

An aircraft structure, for example a wing, includes a section of skin, for example a lower wing panel, the panel defining an external (lower) surface that in use is on the exterior of the aircraft and an internal (upper) surface opposite the external surface, and a duct comprising a section of duct

An aircraft structure, for example a wing, includes a section of skin, for example a lower wing panel, the panel defining an external (lower) surface that in use is on the exterior of the aircraft and an internal (upper) surface opposite the external surface, and a duct comprising a section of duct for transporting cooling fluid, for example air, between the internal and external surfaces of the panel from a first location in the panel to a second location that is spaced apart from the first location in a direction substantially parallel to the external surface of the panel. The cooling air cools an electronic hydrostatic actuator (EHA 4b) in the wing 2.

대표청구항 ▼

1. An aircraft structure including a lower skin and an upper skin, comprising: a section of lower skin, the lower skin defining an external surface that in use is on the exterior of the aircraft and an internal surface directly opposite the external surface, and wherein the section of lower skin is

1. An aircraft structure including a lower skin and an upper skin, comprising: a section of lower skin, the lower skin defining an external surface that in use is on the exterior of the aircraft and an internal surface directly opposite the external surface, and wherein the section of lower skin is defined by one or more panels,a duct comprising a section of duct defined by a region between the internal and the external surfaces of the lower skin, said section of duct transporting cooling fluid along said region from a first location in the lower skin to a second location that is spaced apart from the first location in a direction substantially parallel to the external surface of the lower skin,wherein the section of lower skin includes a cooling fluid inlet arranged on the external surface of the lower skin, the cooling fluid inlet being in fluid communication with the duct, wherein said section of lower skin includes a cooling fluid outlet arranged on the internal surface of the lower skin, the cooling fluid outlet being in fluid communication with an inlet of the section of duct, andan item of aircraft equipment that in use requires cooling being positioned and configured in fluid or thermal communication with an outlet of the section of duct. 2. An aircraft structure according to claim 1, wherein the cooling fluid inlet is configurable to (i) a closed position in which the inlet is closed, and (ii) an open position in which the inlet is open. 3. An aircraft structure according to claim 1, wherein the aircraft structure includes an air scoop configurable to a first position in which, during flight of the aircraft, the air scoop extends into airflow exterior of the aircraft structure so that air is admitted into the duct via the air scoop and a second position in which, during flight of the aircraft, the air scoop is substantially flush with the external surface of the skin and air is prevented from being admitted into the duct via the air scoop. 4. An aircraft structure according to claim 1, wherein the section of skin includes a cooling fluid outlet in fluid communication with the duct, the cooling fluid outlet being arranged on the internal surface of the skin. 5. An aircraft structure according to claim 1, wherein the section of duct is integrally formed with the section of lower skin. 6. An aircraft structure according to claim 1, wherein the section of duct includes a removably mounted wall that defines, at least in part, one of the internal surface and the external surface of the lower skin. 7. An aircraft structure according to claim 1, wherein the section of lower skin is defined by two or more panels and the duct is arranged to transport cooling fluid from one panel to another adjacent panel. 8. An aircraft structure according to claim 7, wherein the section of duct includes a joint in the region of the join between two adjacent panels. 9. An aircraft structure according to claim 1, wherein at least one wall of the duct has a cross-section which is substantially corrugated in shape. 10. An aircraft structure according to claim 1, wherein the structure defines at least part of a wing. 11. An aircraft including an aircraft structure according to claim 1. 12. A section of aircraft skin including a section of duct, the section of aircraft skin being configured so as to be suitable for use as the section of aircraft skin of the aircraft structure according to claim 1. 13. An aircraft structure including a lower skin and an upper skin, comprising a section of lower skin, the section of lower skin defining an external surface that in use is on the exterior of the aircraft and an internal surface opposite the external surface, and wherein the section of lower skin is defined by one or more panels, a duct comprising a section of duct for transporting cooling fluid between the internal and external surfaces of the section of lower skin from a first location in the wing skin to a second location that is spaced apart from the first location in a direction substantially parallel to the external surface of the section lower skin,wherein the aircraft structure includes an air scoop configurable to a first position in which, during flight of the aircraft, the air scoop extends into airflow exterior of the aircraft structure so that air is admitted into the duct via the air scoop and a second position in which, during flight of the aircraft, wherein a first portion of said air scoop is substantially flush with the external surface of the section of lower skin and a second portion of said air scoop is inwardly arcuate with the external surface of the section of lower skin and air is prevented from being admitted into the duct via the air scoop. 14. A method of cooling equipment inside an aircraft comprising an aircraft structure according to claim 1, the method including transporting cooling fluid to the equipment to be cooled, the cooling fluid being transported between the internal and external surfaces of the section of lower skin from a first location in the section of lower skin to a second location that is spaced apart from the first location in a direction substantially parallel to the external surface of the section of lower skin. 15. A method according to claim 14, wherein the method is performed during the use of back-up EHA equipment in a wing of an aircraft to cool such EHA equipment.