Systems and methods for assembling stiffened composite structures
US-9221235-B1 · Dec 29, 2015 · US
US8991759B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-8991759-B2 |
| Application number | US-201113242003-A |
| Country | US |
| Kind code | B2 |
| Filing date | Sep 23, 2011 |
| Priority date | Sep 24, 2010 |
| Publication date | Mar 31, 2015 |
| Grant date | Mar 31, 2015 |
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Rear fuselage of an aircraft comprising a tail cone end and a rest of the real fuselage whereby the tail cone end is attached to the rest of the rear fuselage by means of an attachment system comprising two upper lugs, two lower lugs and a detachable balancer fitting. The balancer fitting is an adjustable fitting, being locked in a Z and Y directions of a Cartesian axis and being movable along an X direction of the Cartesian axis providing guidance for the tail cone end and the rest of the rear fuselage.
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The invention claimed is: 1. A rear fuselage of an aircraft comprising a tail cone end having a cone axis extending generally along an X direction of a Cartesian system, and a remainder of the rear fuselage, where the tail cone end is attached to the remainder of the rear fuselage by an attachment system comprising two upper lugs, two lower lugs and a detachable balancer fitting at an interface point of said tail cone end and said remainder of the rear fuselage, said balancer fitti…
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