Variable control aircraft control surface

• US 5,222,699 A
• Filed: 04/16/1990
• Issued: 06/29/1993
• Est. Priority Date: 04/16/1990
• Status: Expired due to Term

• Current Assignee: Vought Aircraft Company
• Original Assignee: LTV Aerospace and Defense Company
• Inventors: Fewel, Kenneth J., Albach, Walter C.
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US07/509,521
• Time in Patent Office: 1,170 Days
• Field of Search: 244/11, 244/22, 244/34 R, 244/35 R, 244/38, 244/198, 244/201, 244/213, 244/214, 244/215, 244/219, 244/45 R, 244/46, 244/90 R, 244/87, 244/89, 244/123, 244/124, 244/904
• US Class Current: 244/213
• CPC Class Codes: B64C 3/48 by relatively-movable parts of wing structures
• CPC Class Codes: B64C 3/52 Warping
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

A variable contour control surface (30a) and a transition section (30a) are designed to eliminate the discontinuities that exist between an aircraft wing control surface and the wing itself. The variable contour is provided by translating the top skin of the control surface relative to the top surface of the wing with the bottom surfaces of the wing and control surface being joined as a single surface. This movement results in a change in the camber of the control surface. The transition section (30a) is a flexible connection between the inboard and outboard ends of the control surface (30a) and the wing. The transition section (30a) is stiffened by rods (40, 41) which run both fore to aft and spanwise within an elastomeric material. The transition section (30b) may be used in conjunction with either a fixed contour control surface or a variable contour control surface.

Claims

1. An aircraft wing assembly comprising:

(a) a main wing portion having a top skin and a bottom skin;

(b) a variable contour control surface having a top skin and a bottom skin, either said top skin of said variable contour control surface or said bottom skin of said variable contour control surface being attached to the corresponding top or bottom skin of the main wing portion and the other skin of said variable contour control surface being translatable relative to the corresponding other skin of the main wing portion;

(c) means for translating said translatable skin relative to the main wing portion; and

(d) elastomeric spars attached between the top and bottom skins of the variable contour control surface, said spars being flexible in shear to permit the change of camber in said variable contour control surface as said translatalbe skin moves relative to the main wing portion.

2. The aircraft wing assembly according to claim 1 wherein said spars are positioned spanwise along said variable contour control surface.

3. The aircraft wing assembly according to claim 1 further comprising:

a transition section between at least one end of said variable contour control surface and the adjacent section of the main wing portion.

4. The aircraft wing assembly according to claim 3 wherein said transition section has upper and lower elastomeric layers joining the top and bottom skins, respectively, of said variable contour control surface to the corresponding top and bottom skins of the main wing portion.

5. The aircraft wing assembly according to claim 4 further comprising:

a plurality of rods positioned within said elastomeric layers to support loads on said transition section.

6. The aircraft wing assembly according to claim 5 wherein said rods are positioned spanwise within one or both of said elastomeric layers.

7. The aircraft wing assembly according to claim 6 further comprising rods positioned fore to aft in one or both of said elastomeric layers.

8. The aircraft wing assembly according to claim 6 wherein some of said rods are attached at one end to said main wing portion and others of said rods are attached at one end to said variable contour control surface.

9. The aircraft wing assembly according to claim 6 wherein some of said rods have one end thereof attached to said main wing portion with the other end thereof being a free end, and others of said rods have one end thereof attached to said variable contour control surface with the other end thereof being a free end, and wherein said rods are positioned in oversize holes in said transition section with the free ends of said some of said rods overlapping the free ends of said others of said rods.

10. An aircraft wing assembly comprising:

(a) a main wing portion having a top skin and a bottom skin;

(b) a variable contour control surface having a top skin and a bottom skin, said variable contour control surface having an inboard end, an outboard end, a forward edge and a trailing edge, said variable contour control surface being attached along its forward edge to the main wing portion so as to permit hinged movement between said variable contour control surface and said main wing portion;

(c) at least one elastomeric spar attached to the top and bottom skins of the variable contour control surface, said at least one elastomeric spar extending in a spanwise direction; and

(d) a transition section extending between and joining one of the inboard end and the outboard end of said variable contour control surface and the adjacent section of the main wing portion, said adjacent section of the main wing portion having a fixed contour, said transition section having upper and lower elastomeric layers joining the top and bottom skins, respectively, of the said variable contour control surface to the corresponding top and bottom skins of said adjacent section of the main wing portion.

11. The aircraft wing assembly according to claim 10 further comprising:

a plurality of rods positioned within said elastomeric layers to support loads on said transition section.

12. An aircraft wing assembly comprising:

(a) a main wing portion having a top skin and a bottom skin;

(b) a variable contour control surface having a top skin and a bottom skin, said variable contour control surface being attached along its forward edge to the main wing portion so as to permit hinged movement between said variable contour control surface and said main wing portion;

(c) at least one elastomeric spar attached between the top and bottom skins of the variable contour control surface; and

(d) a transition section extending between at least one end of said variable contour control surface and the adjacent section of the main wing portion, said transition section having upper and lower elastomeric layers joining the top and bottom skins, respectively, of the said variable contour control surface to the corresponding top and bottom skins of the main wing portion;

wherein a plurality of rods are positioned within said elastomeric layers to support loads on said transition section; and

wherein said rods are positioned spanwise within one or both of said elastomeric layers.

13. The aircraft wing assembly according to claim 12 wherein some of said rods are attached at one end to said main wing portion and others of said rods are attached at one end to said variable contour control surface.

14. The aircraft wing assembly according to claim 12 wherein some of said rods have one end thereof attached to said main wing portion with the other end thereof being a free end, and others of said rods have one end thereof attached to said variable contour control surface with the other end thereof being a free end, and wherein said rods are positioned in oversize holes in said transition section with the free ends of said some of said rods overlapping the free ends of said others of said rods.

15. The aircraft wing assembly according to claim 13 further comprising rods positioned fore to aft in one or both of said elastomeric layers.

16. In an aircraft wing assembly having a main wing portion with a top skin and a bottom skin and a control surface having a corresponding top skin and a bottom skin, said control surface having an inboard end, an outboard end, a forward edge and a trailing edge, said control surface being hinged at its forward edge to the main wing portion, a transition section extending between and joining one of the inboard end of said control surface and the outboard end of said control surface and the adjacent section of the main wing portion, said adjacent section of the main wing portion having a fixed contour and a trailing edge, said transition section comprising:

upper and lower elastomeric layers joining the top and bottom skins, respectively, of the control surface to the corresponding top and bottom skins of the main wing portion, said transition section being installed in compression between said control surface and the adjacent section of the main wing portion to allow said elastomeric layers to elongate.

17. The aircraft wing assembly according to claim 16 further comprising:

a plurality of rods positioned within said elastomeric layers to support loads on said transition section.

18. In an aircraft wing assembly having a main wing portion with a top skin and a bottom skin and a control surface having a corresponding top skin and a bottom skin, said control surface being hinged at its forward edge to the main wing portion, a transition section between at least one end of said control surface and the adjacent section of the main wing portion, said transition section comprising:

upper and lower elastomeric layers joining the top and bottom skins, respectively, of the control surface to the corresponding top and bottom skins of the main wing portion; and

a plurality of rods positioned within said elastomeric layers to support loads on said transition section;

wherein said rods are positioned spanwise within one or both of said elastomeric layers.

19. The aircraft wing assembly according to claim 18 further comprising rods positioned fore to aft in one or both of said elastomeric layers.

20. The aircraft wing assembly according to claim 18 wherein some of said rods are attached at one end to said main wing portion and others of said rods are attached at one end to said control surface.

21. The aircraft wing assembly according to claim 18 wherein some of said rods have one end thereof attached to said main wing portion with the other end thereof being a free end, and others of said rods have one end thereof attached to said control surface with the other end thereof being a free end, and wherein said rods are positioned in oversize holes in said transition section with the free ends of said some of said rods overlapping the free ends of said others of said rods.

22. An aircraft wing assembly comprising:

(a) a main wing portion having a fixed contour trailing edge;

(b) a variable contour control surface, said variable contour control surface having an inboard end, an outboard end, a leading edge and a trailing edge;

said leading edge of said variable contour control surface being attached to the fixed contour trailing edge of the main wing portion, wherein said variable contour control surface comprises a top skin and a bottom skin defining an airfoil shape, said top skin and said bottom skin being separated from each other by at least one spanwise elastomeric spar;

(c) means to adjust the camber of said variable contour control surface; and

(d) a transition section extending between and joining one of the inboard end and the outboard end of said variable contour control surface and the adjacent portion of the fixed contour trailing edge of the main wing portion.

23. The aircraft wing assembly according to claim 22 wherein at least one spanwise spar is rigidly fixed to the inner surfaces of both the top skin and the bottom skin and is capable of elastic deformation.

24. The aircraft wing assembly according to claim 22 wherein said transition section comprises:

a flexible connection extending between and joining one of the inboard end and the outboard end of said variable contour control surface and the adjacent portion of the fixed contour trailing edge of said main wing portion.

25. The aircraft wing assembly according to claim 22 wherien said transition section further comprises a plurality of rods embedded within an elastomeric material.

26. An aircraft wing assembly comprising:

(a) a main wing portion having a trailing edge;

(b) a variable contour control surface attached to the trailing edge of the main wing portion, wherein said variable contour control surface comprises a top skin and a bottom skin defining an airfoil shape, said top skin and said bottom skin being separated from each other by at least one spanwise elastomeric spar;

(c) means to adjust the camber of said variable contour control surface; and

(d) a transition section between at least one end of said variable contour control surface and the adjacent portion of the trailing edge of the main wing portion;

wherein said top skin is slidable both fore and aft and said bottom skin is fixed to the main wing portion.

27. An aircraft wing assembly comprising:

(a) a main wing portion having a trailing edge;

(b) a variable contour control surface attached to the trailing edge of the main wing portion, wherein said variable contour control surface comprises a top skin and a bottom skin defining an airfoil shape, said top skin and said bottom skin being separated from each other by at least one spanwise elastomeric spar;

(c) means to adjust the camber of said variable contour control surface; and

(d) a transition section between at least one of said variable contour control surface and the adjacent portion of the trailin edge of the main wing portion;

wherein said transition section further comprises a first plurality of rods running fore and aft and a second plurality of rods running spanwise.

28. The aircraft wing assembly according to claim 27 wherein said second plurality of rods running spanwise are attached at one end to either the variable contour control surface or to the trailing edge of said main wing portion.

29. The aircraft wing assembly comprising:

(a) a main wing portion having a trailing edge of fixed contour;

(b) a variable contour control surface having a flexible top surface translatable relative to the top surface of the trailing edge of the main wing portion and a flexible bottom surface attached to the trailing edge of the main wing portion, said flexible top surface by at least one elastomeric spar running through the variable contour control surface;

(c) means for adjusting the camber of said variable contour control surface;

(d) means for sealing the space between the flexible top surface of the variable contour control surface and the top surface of the trailing edge of the main wing portion; and

(e) a flexible transition section between at least one end of said variable contour control section and the trailing edge of the main wing portion.

30. The aircraft wing assembly of claim 29 wherein said flexible top surface of said variable contour control surface is slidable both fore and aft under the trailing edge of said main wing portion.

31. The aircraft wing assembly of claim 29 wherein said transition section comprises:

an elastomeric sheet with oversized tunnels running spanwise and structural rods located in said tunnels.

32. The aircraft wing assembly of claim 31 wherien a rib closeout structure is positioned between the transition section and the adjacent section of the main wing portion, and wherein said structural rods are rotatably attached to either the variable contour control surface or the rib closeout structure.

33. An aircraft control surface assembly comprising:

(a) a main fuselage portion;

(b) a movable control surface attached to said main fuselage portion and having an outboard end and an inboard end; and

(c) a transition section positioned between the inboard end of the movable control surface and the adjacent section of the main fuselage portion and providing a continuous surface from said adjacent section of the main fuselage portion to the moveable control surface, wherein said transition section has upper and lower elastomeric layers and a first plurality of rods positioned within said elastomeric layers to support loads on said transition section, said first plurality of rods extending between the moveable control surface and said adjacent section of the main fuselage portion, and a second plurality of rods positioned within said elastomeric layers and extending at least generally perpendicularly to said first plurality of rods to distribute loads into said first plurality of rods.

34. An aircraft control surface assembly comprising:

(a) a main fuselage portion;

(b) a movable control surface attached to said main fuselage portion; and

(c) a transition section positioned between the movable control surface and the adjacent section of the main fuselage portion, wherein said transition section has upper and lower elastomeric layers and a plurality of rods positioned within said elastomeric layers to support loads on said transition section;

wherein said rods are positioned in oversize holes in said elastomeric layers.

35. An aircraft control surface assembly comprising:

(a) a main fuselage portion;

(b) a movable control surface attached to said main fuselage portion; and

(c) a transition section positioned between the movable control surface and the adjacent section of the main fuselage portion, wherein said transition section has upper and lower elastomeric layers and a first plurality of rods positioned within said elastomeric layers to support loads on said transition section,

wherein some of said rods have one end thereof attached to said movable control surface with the other end thereof being a free end, and others of said rods have one end thereof attached to said main fuselage portion with the other end thereof being a free end, such that the free ends of said some of said rods are overlapping the free ends of said others of said rods.

36. An aircraft wing assembly comprising:

(a) a main wing portion having a top skin and a bottom skin;

(b) a variable contour control surface having a top skin and a bottom skin, either said top skin of said variable contour control surface or said bottom skin of said variable contour control surface being attached to the corresponding top or bottom skin of the main wing portion and the other skin of said variable contour control surface being translatable relative to the corresponding other skin of the main wing portion;

(c) means for translating said translatable skin relative to the main wing portion;

(d) elastomeric spars attached between the top and bottom skins of the variable contour control surface, said spars being flexible in shear to permit the change of camber in said variable contour control surface as said translatable skin moves relative to the main wing portion;

(e) a transition section between at least one end of said variable contour control surface and the adjacent section of the main wing portion, said transition section having upper and lower elastomeric layers joining the top and bottom skins, respectively, of said variable contour control surface to the corresponding top and bottom skins of the main wing portion; and

(f) a plurality of rods positioned within said elastomeric layers to support loads on said transition section, said rods being positioned spanwise within one or both of said elastomeric layers.

37. The aircraft wing assembly according to claim 36 further comprising rods positioned fore to aft in one or both of said elastomeric layers.

38. The aircraft wing assembly according to claim 36 wherein some of said rods are attached at one end to said main wing portion and others of said rods are attached at one end to said variable contour control surface.

39. The aircraft wing assembly according to claim 36 wherein some of said rods have one end thereof attached to said main wing portion with the other end thereof being a free end, and others of said rods have one end thereof attached to said variable contour control surface with the other end thereof being a free end, and wherein said rods are positioned in oversize holes in said transition section with the free ends of said some of said rods overlapping the free ends of said others of said rods.

40. An aircraft wing assembly comprising:

(a) a main wing portion having a top skin and a bottom skin;

(b) a variable contour control surface having a top skin and a bottom skin, said variable contour control surface having an inboard end, an outboard end, a forward edge and a trailing edge, said variable contour control surface being attached along its forward edge to the main wing portion so as to permit hinged movement between said variable contour control surface and said main wing portion;

(c) a transition section extending between and joining one of the inboard end of said variable contour control surface and the outboard end of said variable contour control surface and the adjacent section of the main wing portion, said adjacent section of the main wing portion having a fixed contour, wherein said transition section has upper and lower elastomeric layers joining the top and bottom skins, respectively, of the said variable contour control surface to the corresponding top and bottom skins of said adjacent section of the main wing portion; and

(d) a plurality of rods positioned within one or both of said elastomeric layers to support loads on said transition section.

41. An aircraft wing assembly comprising:

(a) a main wing portion having a top skin and a bottom skin;

(b) a variable contour control surface having a top skin and a bottom skin, said variable contour control surface being attached along its forward edge to the main wing portion so as to permit hinged movement between said variable contour control surface and said main wing portion;

(c) a transition section between at least one end of said variable contour control surface and the adjacent section of the main wing portion wherein said transition section has upper and lower elastomeric layers joining the variable top and bottom skins, respectively, of the said variable contour control surface to the corresponding top and bottom skins of the main wing portion; and

(d) a plurality of rods positioned within one or both of said elastomeric layers to support loads on said transition section;

wherein said rods are positioned spanwise within one or both of said elastomeric layers.

42. The aircraft wing assembly according to claim 41 further comprising rods positioned fore to aft within one or both of said elastomeric layers.

43. An aircraft wing assembly comprising:

(a) a main wing portion having a top skin and a bottom skin;

(b) a variable contour control surface having a top skin and a bottom skin, said variable contour control surface being attached along its forward edge to the main wing portion so as to permit hinged movement between said variable contour control surface and said main wing portion;

(c) a transition section between at least one end of said variable contour control surface and the adjacent section of the main wing portion wherein said transition section has upper and lower elastomeric layers joining the top and bottom skins, respectively, of the said variable contour control surface to the corresponding top and bottom skins of the main wing portion; and

(d) a plurality of rods positioned within one or both of said elastomeric layers to support loads on said transition section;

wherein some of said rods are attached at one end to said main wing portion and others of said rods are attached at one end to said variable contour control surface.

44. An aircraft wing assembly comprising:

(a) a main wing portion having a top skin and a bottom skin;

(b) a variable contour control surface having a top skin and a bottom skin, said variable contour control surface being attached along its forward edge to the main wing portion so as to permit hinged movement between said variable contour control surface and said main wing portion;

(c) a transition section between at least one end of said variable contour control surface and the adjacent section of the main wing portion wherein said transition section has upper and lower elastomeric layers joining the top and bottom skins, respectively, of the said variable contour control surface to the corresponding top and bottom skins of the main wing portion; and

(d) a plurality of rods positioned within one or both of said elastomeric layers to support loads on said transition section;

wherein some of said rods have one end thereof attached to said main wing portion with the other end thereof being a free end, and others of said rods have one end thereof attached to said variable contour control surface with the other end thereof being a free end, and

wherein said rods are positioned in oversize holes in said transition section with the free ends of said some of said rods overlapping the free ends of said others of said rods.

45. In an aircraft wing assembly having a main wing portion with a top skin and a bottom skin and a control surface having a corresponding top skin and a corresponding bottom skin, said control surface being hinged at its forward edge to the main wing portion, a transition section between at least one end of said control surface and the adjacent section of the main wing portion, said transition section comprising:

(a) upper and lower elastomeric layers joining the top and bottom skins, respectively, of the control surface to the corresponding top and bottom skins of the main wing portion; and

(b) a plurality of rods positioned within one or both of said elastomeric layers to support loads on said transition section, said rods being positioned spanwise.

46. The aircraft wing assembly according to claim 45 further comprising rods positioned fore to aft in at least one of said elastomeric layers.

47. The aircraft wing assembly according to claim 45 wherein some of said rods are attached at one end to said main wing portion and others of said rods are attached at one end to said control surface.

48. The aircraft wing assembly according to claim 45 wherein some of said rods have one end thereof attached to said main wing portion with the other end thereof being a free end, and others of said rods have one end thereof attached to said control surface with the other end thereof being a free end, and wherein said rods are positioned in oversize holes in said transition section with the free ends of said some of said rods overlapping the free ends of said others of said rods.

49. An aircraft wing assembly comprising:

(a) a main wing portion having a trailing edge of fixed contour, said trailing edge having a top surface and a bottom surface;

(b) a variable contour control surface having a flexible top surface translatable relative to the top surface of the trailing edge of the main wing portion and a flexible bottom surface attached to the trailing edge of the main wing portion, said flexible top surface of said variable contour control surface being separated from said flexible bottom surface of said variable contour control surface by at least one elastomeric spar running spanwise through the variable contour control surface;

(c) means for adjusting the camber of said variable contour control surface;

(d) means for sealing the space between the flexible top surface of the variable contour control surface and the top surface of the trailing edge of the main wing portion; and

(e) a flexible transition section positioned between at least one end of said variable contour control surface and the adjacent section of the trailing edge of the main wing portion, said transition section comprising an elastomeric sheet with oversized tunnels running spanwise and structural rods slidably located in said tunnels.

50. The aircraft wing assembly of claim 49 wherien a rib closeout structure is positioned between the transition section and the adjacent section of the trailing edge of the main wing portion, and wherein said structural rods are rotatably attached to either the variable contour control surface or to the rib closeout structure.