System and method for improving fuel storage within a wing of an aircraft
A system and method for improving fuel storage within the wing of an aircraft. In one exemplary embodiment, the system and method eliminate the traditional spars and ribs, and any spanwise and cordwise connecting vertical webs, within a wing. Instead, the system comprises a plurality of modified flared spars, each having a length defined by an angled hat section, to form a wing structure. The modified flared spars may also comprise one or more lengths defined by a specialized section configured to accommodate a portion of a box section, or any other internal component of the wing. The system and method may also involve a contiguous fuel bladder of any size/type. The fuel bladder for the wing may comprise a fabric coated or impregnated with an elastomeric material that may include a polyurethane dispersion layer combined with a sealant.
1. A wing structure comprising:
a root wall opposite to a wing tip wall;
a plurality of spars extending longitudinally from the root wall to wing tip wall and coupled to the root wall and the wing tip wall;
a wing skin extending from the root wall to the wing tip wall and coupled to each spar and to the root wall and wing tip wall, each spar comprising a multisided cross-sectional shape that forms a closed channel between an internal region of the multi-sided cross-sectional shape and a side of the wing skin, whereby the spars, root wall, wing tip wall, and wing skin define a volume maximized for internal storage while maintaining strength of the wing structure; and
at least one utility housing formed within the volume and coupled to at least one or more spars;
wherein the multi-sided cross-sectional shape that forms a closed channel for each spar further comprises:
a coupling section that is fastened to a wall of a utility housing; and
an engagement flange section that is coupled to the wing skin.
2. The wing structure of claim 1 , wherein the wing skin comprises a plurality of sections that are coupled to the spars, root wall, and wing tip wall.
3. The wing structure of claim 2 , wherein one of the wing sections comprises a half-elliptical cross-sectional shape configured to be removable relative to the other wing sections and provides an opening to the volume defined by the spars, root wall, and wing tip wall.
4. The wing structure of claim 3 , wherein the multi-sided cross-sectional shape that forms a closed channel for each spar further comprises:
a hat section; and
two engagement flange sections that are coupled to the wing skin.
5. The wing system of claim 3 , wherein the multi-sided cross-sectional shape that forms a closed channel for each spar further comprises: a hat section; and two engagement flange sections that are coupled to the wing skin.
6. The wing structure of claim 2 , wherein the multi-sided cross-sectional shape that forms a closed channel for each spar further comprises:
a hat section; and
two engagement flange sections that are coupled to the wing skin.
7. The wing system of claim 2 , wherein the multi-sided cross-sectional shape that forms a closed channel for each spar further comprises: a hat section; and two engagement flange sections that are coupled to the wing skin.
8. The wing structure of claim 1 , wherein the multi-sided cross-sectional shape that forms a closed channel for each spar further comprises:
a hat section; and
two engagement flange sections that are coupled to the wing skin.
9. A wing system comprising:
a root wall opposite to a wing tip wall;
a plurality of spars extending longitudinally from the root wall to wing tip wall and coupled to the root wall and the wing tip wall; and a wing skin extending from the root wall to the wing tip wall and coupled to each spar and to the root wall and wing tip wall, each spar comprising a multisided cross-sectional shape that forms a closed channel between an internal region of the multi-sided cross-sectional shape and a side of the wing skin, whereby the spars, root wall, wing tip wall, and wing skin define a volume maximized for internal storage while maintaining strength of the wing structure;
a flexible fuel bladder positioned within the volume; and
at least one utility housing formed within the volume and coupled to at least one or more spars;
wherein the multi-sided cross-sectional shape that forms a closed channel for each spar further comprises:
a coupling section that is fastened to a wall of a utility housing; and
an engagement flange section that is coupled to the wing skin.
10. The wing system of claim 9 , wherein the wing skin comprises a plurality of sections that are coupled to the spars, root wall, and wing tip wall.
11. The wing system of claim 10 , wherein one of the wing sections comprises a half-elliptical cross-sectional shape configured to be removable relative to the other wing sections and provides an opening to the volume defined by the spars, root wall, and wing tip wall.
12. The wing system of claim 10 , wherein the multi-sided cross-sectional shape that forms a closed channel for each spar further comprises: a hat section; and two engagement flange sections that are coupled to the wing skin.
13. The wing system of claim 10 , wherein the flexible fuel bladder has a geometry which substantially mirrors the volume defined by the spars, root wall, wing tip wall, and wing skin.
14. The wing system of claim 10 , wherein the flexible fuel bladder comprises a groove ( 280 ) for receiving an outer geometry of at least one spar.
15. The wing system of claim 10 , wherein flexible fuel bladder comprises a U-shaped opening for receiving a utility housing.
16. The wing system of claim 9 , wherein the multi-sided cross-sectional shape that forms a closed channel for each spar further comprises: a hat section; and two engagement flange sections that are coupled to the wing skin.
17. The wing system of claim 9 , wherein the flexible fuel bladder has a geometry which substantially mirrors the volume defined by the spars, root wall, wing tip wall, and wing skin.
18. The wing system of claim 9 , wherein the flexible fuel bladder comprises a groove ( 280 ) for receiving an outer geometry of at least one spar.
19. The wing system of claim 9 , wherein flexible fuel bladder comprises a U-shaped opening for receiving a utility housing.
20. The wing system of claim 9 , wherein the flexible fuel bladder is a type which is at least one of: (a) crashworthy and self-sealing; (b) crashworthy and non-self-sealing; (c) crash resistant and self-sealing; and (d) crash resistant and non-self-sealing.