Aircraft door and a method for the manufacture of an aircraft door of this type
An aircraft door includes an outer skin configured as a panel structure; and a rear body structure configured as an integral cast structure and operatively connected to the panel structure so as to provide rigidity.
1. An aircraft door, comprising:
an outer skin configured as a panel structure; and
a rear body structure configured as an integral cast structure and operatively connected to the panel structure so as to provide rigidity, the rear body structure including at least two central frames extending over an entire length of the aircraft door, the at least two central frames being curved in an arched shape relative to a longitudinal axis of the aircraft door from a perspective orthogonal to the outer skin so as to extend around a window opening in the aircraft door.
2. The aircraft door as recited in claim 1 , wherein the rear body structure includes at least one beam portion extending across a width of the aircraft door.
3. The aircraft door as recited in claim 1 , wherein the rear body structure comprises an outer side attached to the outer skin and an inner side opposite the outer skin, and wherein each of the central frames includes:
a web extending transverse to the outer skin from the outer side to the inner side, and
at least one flange disposed transverse to the web on the inner side of the rear body structure.
4. The aircraft door as recited in claim 1 , wherein each of the central frames includes a side facing away from the outer skin that includes at least one section curved in an arc shape.
5. The aircraft door as recited in claim 4 , wherein the at least one section is curved relative to a longitudinal axis of the aircraft door so as to vary a structural height of the central frames along the longitudinal axis of the door.
6. The aircraft door as recited in claim 2 , wherein the at least one beam portion includes a plurality of beams, a structural height of the plurality of beams decreasing from a center of the door to edge regions of the door.
7. The aircraft door as recited in claim 2 , wherein a side of the at least one beam portion facing away from the outer skin includes at least one section curved in a convex arc shape.
8. The aircraft door as recited in claim 7 , wherein the side of the at least one beam portion is curved in a manner configured to withstand a structural loading.
9. The aircraft door as recited in claim 1 , wherein the rear body structure includes an integral framework structure including a plurality of stiffening webs.
10. The aircraft door as recited in claim 1 , wherein the rear body structure includes an integral framework structure including a plurality of cutouts.
11. A method for manufacturing an aircraft door, comprising:
forming a rear body structure using a casting technique;
the rear body structure including at least two central frames which extend over an entire length of the aircraft door, the at least two central frames being curved in an arched shape relative to a longitudinal axis of the aircraft door from a perspective orthogonal to the outer skin so as to extend around a window opening in the aircraft door; and
connecting an outer skin configured as a panel structure to the rear body structure.
12. The method as recited in claim 10 , wherein the connecting includes connecting the outer skin to the rear body structure using riveting, an adhesive technique, or riveting and an adhesive technique.