Aircraft tail assembly
View Patent ↗An aircraft tail assembly planform comprising curvilinear leading edges ( 21 ) and trailing edges ( 22 ), with an aircraft tail assembly configuration in which the hinge line ( 13 ) is rectilinear and has a non-constant percentage with respect to the chord ( 50 ) in each section ( 51 ), being the front ( 11 ) and rear ( 12 ) spars rectilinear with a non-constant percentage with respect to the chord ( 50 ) in each section ( 51 ), or being these spars ( 11, 12 ) curvilinear with a constant or non-constant percentage with respect to the chord ( 50 ) in each section ( 51 ). Moreover, the invention describes an aircraft tail assembly planform comprising rectilinear leading edges ( 21 ) and trailing edges ( 22 ), in which the hinge line ( 13 ) has a non-constant percentage with respect to the chord ( 50 ) in each section ( 51 ), being the front ( 11 ) and rear ( 12 ) spars rectilinear, with a constant or non-constant percentage with respect to the chord ( 50 ) in each section ( 51 ), or being these spars ( 11, 12 ) curvilinear, with a constant or non-constant percentage.
1. An aircraft tail assembly having a chord and a span which assembly comprises a curvilinear leading edge and a curvilinear trailing edge, with an aircraft tail assembly configuration and having a hinge line for a rudder or elevator and wherein the distance between the leading edge and the hinge line is not a constant percentage of the chord at each location along the span and wherein the assembly comprises curvilinear front and rear spars having a constant percentage of the chord at each location along the span.
2. An aircraft tail assembly according to claim 1 , wherein the leading edge trailing edge are convex curvilinear.
3. An aircraft tail assembly according to claim 1 , wherein the leading edge and trailing edge are concave curvilinear.
4. An aircraft tail assembly according to claim 1 wherein the leading edge is convex curvilinear and the trailing edge is concave curvilinear.
5. An aircraft tail assembly according to claim 1 wherein the leading edge is concave curvilinear and the trailing edge is convex curvilinear.
6. An aircraft tail assembly according to claim 1 , wherein the distance between the leading edge and the hinge line has been optimized by computer fluid dynamics.
7. An aircraft tail assembly, having a chord and a span, which assembly comprises a curvilinear leading edge and a curvilinear trailing edge, with an aircraft tail assembly configuration and having a hinge line for a rudder or elevator wherein the distance between the leading edge and the hinge line is not a constant percentage of the chord at each location along the span and which comprises curvilinear front and rear spars tracing a non-constant percentage curve which has been optimized by computer computation and wherein the leading edge, the trailing edge and the hinge line position are also optimised by computer computation.
8. An aircraft tail assembly according to claim 7 , wherein the curvilinear front and rear spars trace a non-constant percentage curve which has been optimized by computer fluid dynamics computation or computer structural analysis computation or a combination thereof.
9. An aircraft tail assembly according to claim 7 , wherein the leading edge, the trailing edge and the hinge line position have been optimized by computer fluid dynamics computation or computer structural analysis computation or a combination thereof.
10. An aircraft tail assembly according to claim 7 , wherein the distance between the leading edge and the hinge line has been optimized by computer fluid dynamics.
11. An aircraft tail assembly having a chord and a span, said assembly comprising a leading edge ( 21 ) and a trailing edge ( 22 , and having a hinge line for a rudder or elevator wherein the distance between the leading edge and the hinge line is not a constant percentage of the chord at each location along the span and wherein the assembly comprises curvilinear front and rear spars having a constant percentage of the chord at each location along the span.
12. An aircraft tail assembly according to claim 11 , wherein said leading edges and trailing edges are rectilinear.
13. An aircraft tail assembly according to claim 11 , wherein the distance between the front and rear spars is a constant percentage of the chord at each location along the span wherein the location of said spars along the span has been optimized by computer computation and wherein the leading edge, the trailing edge and the hinge line position are also optimised by computer computation.
14. An aircraft tail assembly, having a chord and a span, said assembly comprising rectilinear leading edges and trailing edges, and having a hinge line for a rudder or elevator wherein in the aircraft tail assembly configuration and wherein the distance between the leading edge and the hinge line is not a constant percentage of the chord at each location along the span and wherein the assembly comprises curvilinear front and rear spars and wherein the distance between the spars is not a constant percentage of the chord at each location along the span.
15. An aircraft tail assembly according to claim 14 , wherein the distance between the leading edge and the hinge line has been optimized by computer fluid dynamics.
16. An aircraft tail assembly having a chord and a span, which assembly comprises a curvilinear leading edge and a curvilinear trailing edge, with an aircraft tail assembly configuration and having a hinge line for a rudder or elevator and wherein the distance between the leading edge and the hinge line is not a constant percentage of the chord at each location along the span and wherein the assembly comprises curvilinear front and rear spars having a constant percentage of the chord at each location along the span wherein the location of said curvilinear front and rear spars has been optimized by computer computation and wherein the leading edge, the trailing edge and the hinge line position are also optimised by computer computation.
17. An aircraft tail assembly having a hinge line for a rudder or elevator wherein in the aircraft tail assembly configuration, and wherein the distance between the leading edge and the hinge line is not a constant percentage of the chord at each location along the span and wherein the assembly comprises curvilinear front and rear spars having a constant percentage of the chord at each location along the span has been optimized by computer computation and wherein the leading edge, the trailing edge and the hinge line position are also optimised by computer computation.
18. An aircraft tail assembly comprising a rectilinear leading edge and a rectilinear trailing edge and having a hinge line for a rudder or elevator wherein the distance between the leading edge and the hinge line is not a constant percentage of the chord at each location along the span and wherein the assembly comprises curvilinear front and rear spars having a constant percentage of the chord at each location along the span wherein the location of said spars along the span has been optimized by computer computation and wherein the leading edge, the trailing edge and the hinge line position are also optimised by computer computation.