Fitting for pivotally connecting aerodynamic control element to aircraft structure
View Patent ↗A method of installing an aerodynamic control element on an aircraft structure. The method comprising: attaching a fitting to the aircraft structure, the fitting comprising a pair of hinge ribs extending away from the aircraft structure and a spacer extending between the pair of hinge ribs; maintaining a desired distance between the pair of hinge ribs with the spacer as the fitting is attached; and pivotally mounting the aerodynamic control element to each hinge rib via a respective hinge.
1. A method of installing an aerodynamic control element on an aircraft structure, the method comprising:
attaching a fitting to the aircraft structure, the fitting comprising a pair of hinge ribs extending away from the aircraft structure and a web extending between the pair of hinge rib arms,
integrally forming said web as a single piece with the pair of hinge ribs;
maintaining a desired distance between the pair of hinge ribs with the web as the fitting is attached; and
pivotally mounting the aerodynamic control element to each hinge rib via a respective hinge.
2. The method of claim 1 wherein the fitting is attached to a trailing edge of the aircraft structure.
3. The method of claim 2 wherein the aircraft structure comprises a rear spar and a cover which is attached to the rear spar and overhangs to its rear, the method further comprising attaching each hinge rib to the cover.
4. The method of claim 3 wherein the aircraft structure further comprises a second cover which is attached to the rear spar and overhangs to its rear; the method further comprising attaching each hinge rib arm to the second cover.
5. The method of claim 4 wherein each hinge rib comprises a first hinge rib arm and a second hinge rib arm, the method further comprising: attaching the first hinge rib arm of each hinge rib to the first cover; and attaching the second hinge rib arm of each hinge rib to the second cover.
6. A fitting for pivotally connecting an aerodynamic control element to an aircraft structure, the fitting comprising a pair of hinge ribs each adapted to be pivotally connected to the control element; and a spacer extending between the pair of hinge ribs, wherein the spacer is integrally formed as a single piece with the pair of hinge ribs and wherein the spacer comprises a web extending between the pair of hinge ribs and two or more stiffening flanges extending from the web and extending between the pair of hinge ribs.
7. The fitting of claim 6 wherein each hinge rib comprises a pair of clevis arms, each clevis arm having a hole for receiving a hinge pin.
8. An aircraft assembly comprising:
an aircraft structure;
a fitting attached to the aircraft structure, the fitting comprising a pair of hinge ribs and a web spacer extending between the pair of hinge ribs, wherein the web spacer is integrally formed as a single piece with the pair of hinge ribs; and
an aerodynamic control element pivotally connected to each hinge rib by a respective hinge.
9. The assembly of claim 8 , wherein the aircraft structure comprises a rear spar, and a cover which is attached to the rear spar and overhangs to its rear; and
wherein each hinge rib engages the cover.
10. The assembly of claim 9 wherein the web engages the cover.
11. The assembly of claim 10 , wherein the aircraft structure further comprises a second cover which is attached to the rear spar and overhangs to its rear; and wherein each hinge rib engages the second cover.
12. The assembly of claim 11 wherein each hinge rib comprises a first hinge rib arm which is attached to the first cover; and a second hinge rib arm which is attached to the second cover.
13. The assembly of claim 12 wherein the first hinge rib arm extends longitudinally at an acute angle to the second hinge rib arm.
14. The assembly of claim 12 wherein the web extends between the first hinge rib arms of each hinge rib.
15. The assembly of claim 8 wherein the fitting is attached to a trailing edge of the aircraft structure.