Fuel storage means

• US 4,776,537 A
• Filed: 08/08/1986
• Issued: 10/11/1988
• Est. Priority Date: 08/08/1985
• Status: Expired due to Fees

• Current Assignee: British Aerospace, Inc.
• Original Assignee: British Aerospace, Inc.
• Inventors: Rhodes, Arthur N., Garside, Christopher M.
• Primary Examiner(s): Barefoot, Galen
• Application Number:
  US06/894,913
• Time in Patent Office: 795 Days
• Field of Search: 244/135 R, 244/135 B, 244/105, 244/107, 244/219, 244/130, 220/85 B, 220/1 B, 220/18, 114/331
• US Class Current: 244/135.00R
• CPC Class Codes: B64D 37/04 Arrangement thereof in or on aircraft

Abstract

This invention relates to a collapsible fuel storage tank for storing fuel on an aircraft. According to this invention, there is provided an aircraft including a fuselage portion, a wing portion connected thereto and an expandable fuel storage tank disposed adjacent the intersection of the wing portion and the fuselage portion. The fuel storage tank has an external surface which includes spanwise spaced inner and outer edge regions extending in a generally chordwise direction. The inner edge region of the tank extending alongside the fuselage portion and the outer edge region being attached to the wing portion to allow movement of the external surface between an empty position in which it lies generally flush with the surrounding surface of the wing portion and a fuel storing position in which it lies at an acute angle to said surrounding surface forming a fillet region between the wing portion and the fuselage portion. By this arrangement when the external surface is in a fuel storing position the wetted area of the aircraft is decreased, rather than increased. In addition, the external surface moves to its fuel storing position without creating large gaps or slots.

Claims

1. An aircraft including a fuselage portion, a wing portion connected thereto and expandable fuel storage means entirely disposed at a wing root location adjacent the intersection of said wing portion and said fuselage portion, said fuel storage means having external surface-defining means which includes spanwise spaced inner and outer edge regions extending in a generally clockwise direction, said inner edge region extending alongside and moveably mounted to pass over said fuselage portion and said outer edge region being hingedly attached to said wing portion to allow movement of the surface-defining means between an empty position in which the surface-defining means forms a contiguous and coplanar surface with the surrounding surface of the wing portion and a fuel storing position in which it lies at an acute angle to said surrounding surface and forms a fillet region between the wing portion and the fuselage portion and such that the wetted area of said aircraft is greater with the surface-defining means in said empty position than with the surface-defining means in said fuel storing position.

2. An aircraft as claimed in claim 1 and wherein the external surface-defining means is of trapezoidal planform having an inner edge region lying generally alongside the body portion, an outer edge region extending generally chordwise, a forward edge region extending along a leading edge region of the wing portion and a rearward edge region extending along a trailing edge region of the wing portion.

3. An aircraft as claimed in claim 1 and wherein said fuselage portion over which the inner edge region of the external surface-defining means passes when moving between the empty and the fuel storing position is of concave form.

4. An aircraft as claimed in claim 1 and wherein the fuel storage means includes retraction means operable to draw the external surface-defining means from the fuel storing position towards the empty position.

5. An aircraft as claimed in claim 4 and wherein the retraction means comprises a plurality of tie members attached to the external surface-defining means at spaced locations along its inner edge region.

6. An aircraft as claimed in claim 5 and wherein each of said tie members is caused to retract at a predetermined rate relative to the remainder of said tie members thereby to ensure that said inner edge region adopts a predetermined profile when moving between the fuel storage position and the empty position.

7. An aircraft as claimed in claim 6 and further including a windlass device comprising winding portions for each tie member of predetermined diameter selected having regard to the desired relative rate of retraction.

8. An aircraft as claimed in claim 7 and wherein the windlass is driven by means of a flexible drive element wrapped around a driving portion of the windlass and having a free end attached to a hydraulic ram for effecting longitudinal movement.

9. An aircraft including a fuselage portion, a wing portion connected thereto and expandable fuel storage means disposed adjacent the intersection of said wing portion and said fuselage portion, said fuel storage means having external surface-defining means of trapezoidal planform having an inner region lying generally alongside the fuselage portion, and outer edge region extending generally chordwise, a forward edge region extending along a leading edge region of the wing portion and a rearward edge region extending along a trailing edge region of the wing portion, the trapezoidal surface-defining means comprising a forward resiliently deformable panel element of generally triangular planform and a rearward resiliently deformable panel element of generally rectangular planform, the forward panel element having an inner edge region attached to said leading edge region for hinging movement, and a rearward edge region slidably coupled to a forward edge region of the rearward panel element, said outer edge region being attached to said wing portion to allow movement of the surface-defining means between an empty position in which it lies generally flush with the surrounding surface of the wing portion and a fuel storing position in which it lies at an acute angle to said surrounding surface, forming a fillet region between the wing portion and the fuselage portion.

10. An aircraft as claimed in claim 9 and wherein there is further provided a resiliently flexible beam element of variable effective length attached to and extending along the inner edge regions of said forward and rearward panel elements and being anchored to the wing portion at forward and rearward anchorage points.