An elastomeric transition for spanning a gap between first and second surfaces on an aircraft includes an elastomeric skin. A first skin edge is configured for attachment to the first surface and a second skin edge is configured for attachment to the second surface. The elastomeric skin has a longit
An elastomeric transition for spanning a gap between first and second surfaces on an aircraft includes an elastomeric skin. A first skin edge is configured for attachment to the first surface and a second skin edge is configured for attachment to the second surface. The elastomeric skin has a longitudinal dimension, coincident with the gap, which is significantly longer than a distance between laterally corresponding points on the first and second skin edges. At least one continuous rod is coupled at one end to a selected first point on the first surface and at another end to a selected second point, spaced apart from the first point, on the second surface. The at least one continuous rod is configured in the elastomeric transition to run along the gap such that the rod extends at an acute angle in relation to both the first and second skin edges.
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1. An elastomeric transition for spanning a gap between first and second surfaces on an aircraft, the elastomeric transition comprising: an elastomeric skin, a first edge of the skin attached to the first surface and a second edge of the skin attached to the second surface, the elastomeric skin havi
1. An elastomeric transition for spanning a gap between first and second surfaces on an aircraft, the elastomeric transition comprising: an elastomeric skin, a first edge of the skin attached to the first surface and a second edge of the skin attached to the second surface, the elastomeric skin having a longitudinal dimension, coincident with the gap, which is longer than a distance between laterally corresponding points on the first and second edges of the skin; andat least one continuous rod coupled at one end to a selected first point on the first surface and at another end to a selected second point on the second surface, the second point being spaced apart from the first point, the at least one continuous rod being configured in the elastomeric transition to run along the gap such that the rod extends at an acute angle in relation to both the first and second edges of the skin;wherein the gap includes at least one angular gap transition, the longitudinal dimension remaining coincident with the gap through the angular transition, and the continuous rod includes an angular rod transition at a location longitudinally spaced from both ends of the rod. 2. The elastomeric transition of claim 1, wherein the continuous rod extends laterally across the gap without contacting the first and second surfaces other than at the selected first and second points. 3. The elastomeric transition of claim 1, wherein the continuous rod connects the first surface to the second surface. 4. The elastomeric transition of claim 1, wherein the first surface is a perimeter control surface and the second surface is a fixed aircraft structure. 5. The elastomeric transition of claim 1, wherein the first and second surfaces are substantially rigid and the elastomeric skin is significantly more flexible, in the range of 2,000-30,000 times more flexible, than the first and second surfaces. 6. The elastomeric transition of claim 1, wherein the continuous rod is a single-piece, integrally formed, unitary rod. 7. The elastomeric transition of claim 1, wherein the continuous rod is encapsulated within the skin. 8. The elastomeric transition of claim 1, wherein the at least one continuous rod is a first continuous rod, and the elastomeric transition further includes a second continuous rod, the second continuous rod is coupled at one end to a selected third point, longitudinally spaced from the first point, on the first surface and at another end to a selected fourth point, longitudinally spaced from the second point, on the second surface, the third point being longitudinally spaced from the fourth point, the second continuous rod being configured in the elastomeric transition to run along the gap such that the second continuous rod extends at an acute angle in relation to both the first and second edges of the skin and does not contact the first continuous rod. 9. The elastomeric transition of claim 8, wherein the second continuous rod extends laterally across the gap without contacting the first and second surfaces other than at the selected third and fourth points, and without contacting the first control rod. 10. An aircraft, comprising: a substantially rigid fixed aircraft structure having an outer perimeter;a perimeter control surface laterally spaced from the outer perimeter of the aircraft structure to form a gap laterally therebetween;an elastomeric skin extending laterally between the perimeter control surface and the outer perimeter of the aircraft structure to bridge the gap; andat least one control rod having first and second control rod ends spaced apart by a control rod body, the control rod body including at least one angular rod transition coincident with a selected angular transition of the gap which is spaced from both the first and second rod end locations;the first control rod end being attached to the outer perimeter of the aircraft structure at a selected first rod end location, the control rod body extending from the first rod end location laterally away from the outer perimeter of the aircraft structure at an acute angle;the second control rod end being attached to the perimeter control surface at a selected second rod end location, the second rod end location being spaced along the gap from the first rod end location, the control rod body extending from the second rod end location laterally away from the perimeter control surface at an acute angle; andthe control rod body extending laterally across the gap. 11. The aircraft of claim 10, wherein the control rod body extends laterally across the gap without contacting the perimeter control surface and the outer perimeter of the aircraft structure other than at the first and second rod end locations. 12. The aircraft of claim 10, wherein the control rod connects the perimeter control surface to the outer perimeter of the aircraft. 13. The aircraft of claim 10, wherein the control rod is a single-piece, integrally formed, unitary rod. 14. The aircraft of claim 10, wherein the control rod changes length during in-flight expansion of the elastomeric skin. 15. The aircraft of claim 10, wherein the control rod extends around at least one angular gap transition at an angular rod transition having a rod corner angle, and the rod corner angle changes during in-flight movement of the perimeter control surface relative to the outer perimeter of the aircraft. 16. The aircraft of claim 10, wherein the control rod is encapsulated within the skin. 17. The aircraft of claim 10, wherein the at least one control rod is a first control rod, and the aircraft further includes a second control rod having third and fourth control rod ends spaced apart by a second control rod body, the third control rod end being attached to the outer perimeter of the aircraft structure at a selected third rod end location spaced along the gap from the first and second rod end locations, the second control rod body extending from the third rod end location laterally away from the outer perimeter of the aircraft structure at an acute angle,the fourth control rod end being attached to the perimeter control surface at a selected fourth rod end location spaced along the gap from the first, second, and third rod end locations, the second control rod body extending from the fourth rod end location laterally away from the perimeter control surface at an acute angle, andthe second control rod body extending laterally across the gap. 18. The aircraft of claim 17, wherein the second control rod body extends laterally across the gap without contacting the perimeter control surface and the outer perimeter of the aircraft structure other than at the third and fourth rod end locations, and without contacting the first control rod. 19. An elastomeric transition spanning a gap between first and second surfaces on an aircraft, the gap defining a gap circumference substantially surrounding the first surface, the elastomeric transition comprising: an elastomeric skin extending laterally between the first and second surfaces to bridge the gap; andat least one control rod having first and second control rod ends spaced apart by a control rod body,the first control rod end being attached to the first surface at a selected first rod end location, the second control rod end being attached to the second surface at a selected second rod end location, andthe control rod body extending laterally across the gap and circumferentially about a supermajority of the gap circumference. 20. The elastomeric transition of claim 19, wherein the second rod end location is spaced along the gap circumference from the first rod end location. 21. The elastomeric transition of claim 19, wherein the first and second rod end locations are substantially laterally aligned along the gap circumference. 22. The elastomeric transition of claim 19, wherein the control rod body extends laterally across the gap without contacting the first and second surfaces other than at the first and second rod end locations. 23. The elastomeric transition of claim 19, wherein the control rod body includes at least one angular rod transition coincident with a selected angular transition of the gap which is spaced from both the first and second rod end locations. 24. The elastomeric transition of claim 19, wherein the control rod is a single-piece, integrally formed, unitary rod. 25. The elastomeric transition of claim 19, wherein the control rod is encapsulated within the skin. 26. The elastomeric transition of claim 19, the at least one control rod is a first control rod, and the elastomeric transition further includes a second control rod having third and fourth control rod ends spaced apart by a second control rod body, the third control rod end being attached to the first surface at a selected third rod end location spaced along the gap from the first and second rod end locations, the fourth control rod end being attached to the second surface at a selected fourth rod end location spaced along the gap from the first and second rod end locations, andthe second control rod body extending laterally across the gap and circumferentially about a supermajority of the gap circumference. 27. The elastomeric transition of claim 26, wherein the second control rod body extends laterally across the gap without contacting the first and second surfaces other than at the third and fourth rod end locations, and without contacting the first control rod.
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