Door frame component of cast titanium and structural fuselage part
View Patent ↗A door frame component of cast titanium for a door opening in an outer skin of an aircraft or space vehicle and a structural fuselage part that includes the door frame component. The component includes a contact surface for bearing against the outer skin formed to correspond to an inner contour of the outer skin, The structural part includes the door frame component and an outer skin of a carbon fiber reinforced plastic material.
1. A door frame system for a door opening in an outer skin of an aircraft or space vehicle, the door frame system comprising:
a door frame component comprising a contact surface for bearing against the outer skin of the aircraft or space vehicle,
wherein the door frame component is a single casting of a titanium alloy,
wherein the door frame component contact surface is formed to lay flush with an inside of the outer skin,
wherein the door frame component is mounted directly to the outer skin, and
wherein the outer skin comprises of a carbon fiber reinforced plastic composite.
2. The door frame system according to claim 1 , wherein the door frame component comprises at least one hinge portion for movable suspension of a door in the door opening.
3. The door frame system according to claim 1 , wherein the door frame component comprises at least one locking portion for locking a door in the door opening.
4. The door frame system according to claim 1 , wherein the door frame component comprises a door frame rib for arrangement on one side of the door opening, and the door frame rib is at least as long as the door opening is high.
5. The door frame system according to claim 4 , wherein the door frame rib has a C-shaped profile, the C-shaped profile comprised of two legs and a transverse wall connecting the two legs.
6. The door frame system according to claim 5 , wherein the contact surface is arranged on an outer side of one of the legs of the C-shaped profile.
7. The door frame system according to claim 6 , wherein the transverse wall of the C-shaped profile faces the door opening.
8. The door frame system according to claim 5 , further comprising at least one web connecting the two legs and the transverse wall together.
9. The door frame system according to claim 8 wherein the at least one web runs perpendicularly to the transverse wall, and the two legs.
10. The door frame system according to claim 4 , wherein the door frame component comprises at least one intercostal portion for support in an intercostal region of the outer skin located between the door frame component and an adjacent rib of the aircraft or space vehicle.
11. The door frame system according to claim 10 , wherein the intercostal portion extends perpendicularly to the transverse wall.
12. The door frame system according to claim 11 , wherein the intercostal portion has a fastening portion for fastening to an adjacent rib of the aircraft or space vehicle.
13. The door frame system according to claim 1 , wherein the door frame component is provided for arrangement on an upper edge of the door opening, wherein a length of the door frame component is equal to a height of the door opening.
14. The door frame system according to claim 1 , wherein the door frame component is provided for arrangement on a lower edge of the door opening, wherein the length of the door frame component is equal to a height of the door opening.
15. A fuselage structure part for an aircraft or space vehicle, the fuselage structure part comprising:
an outer skin, which comprises a carbon fiber reinforced plastic material; and
a door frame component for a door opening in the outer skin, wherein the door frame component comprises a contact surface for bearing against the outer skin, and wherein the contact surface is formed to lay flush with an inside of the outer skin,
wherein the door frame component comprises of a single casting of a titanium alloy,
wherein the door frame is mounted directly on the outer skin,
wherein the door frame component further comprises intercostal portions; and
wherein the intercostal portions have on their ends a fastening portion for fastening to a closest adjacent rib.
16. The fuselage structure part for an aircraft or space vehicle according to claim 15 , wherein the fuselage structure part further comprises:
ribs for stiffening the outer skin, and wherein the ribs comprise a carbon fiber reinforced plastic material; and
wherein the intercostal portions of the door frame component are fastened to the ribs by the fastening portions.