System for reducing thermal stresses in a leading edge of a high speed vehicle
A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. The leading edge assembly includes a plurality of structural layers and a plurality compliant layers alternately stacked with each other to facilitate thermal expansion and movement between the plurality of structural layers, while also providing a thermal break between the plurality of structural layers.
1. A leading edge assembly for a hypersonic vehicle, the leading edge assembly comprising:
an outer wall that is tapered at a forward end thereof; and
a tip portion joined to the forward end of the outer wall and extending forward toward a leading edge, the tip portion comprising:
a forward end that is curved,
an aft end that is curved,
an inner layer positioned at the aft end of the tip portion and conforming to the aft end of the tip portion,
an outer layer defining the leading edge at a forward end of the tip portion and conforming to the forward end of the tip portion, and
one or more compliant layers that is curved and positioned between the inner layer and the outer layer for facilitating movement between the inner layer and the outer layer, and
wherein the inner layer and the outer layer have a first coefficient of thermal expansion and the one or more of compliant layers have a second coefficient of thermal expansion, the second coefficient of thermal expansion being greater than the first coefficient of thermal expansion.
2. The leading edge assembly of claim 1 , wherein the tip portion further comprises:
an intermediate layer positioned between the inner layer and the outer layer, and
wherein the one or more compliant layers comprises a first compliant layer positioned between the inner layer and the intermediate layer and a second compliant layer positioned between the intermediate layer and the outer layer.
3. The leading edge assembly of claim 2 ,
wherein the outer wall includes a first wall section and a second wall section separated by a chamber, and
wherein the inner layer, the intermediate layer, and the outer layer are each curved and extend between the first wall section and the second wall section.
4. The leading edge assembly of claim 1 , wherein the inner layer and the outer layer are made from different materials.
5. The leading edge assembly of claim 1 , wherein the outer layer and the inner layer are made from a metal, a ceramic material, or a ceramic matrix composite material.
6. The leading edge assembly of claim 1 , wherein the outer layer and the inner layer have different densities.
7. The leading edge assembly of claim 1 , wherein at least two of the one or more compliant layers are made from different materials.
8. The leading edge assembly of claim 1 , wherein at least one cooling passageway is defined through the inner layer, the outer layer, and the one or more compliant layers.
9. The leading edge assembly of claim 8 , further comprising:
a coolant supply in fluid communication with the at least one cooling passageway for selectively providing a flow of coolant through the at least one cooling passageway.
10. The leading edge assembly of claim 1 , wherein the leading edge assembly is positioned on a wing, a nosecone, an engine cowl, an engine inlet, a fuselage, or a stabilizer of the hypersonic vehicle.
11. A leading edge assembly for a hypersonic vehicle, the leading edge assembly comprising:
an outer wall that is tapered at a forward end thereof; and
a tip portion joined to the forward end of the outer wall,
the tip portion comprising:
a forward end that is curved,
an aft end that is curved, and
a plurality of structural layers and a plurality compliant layers alternately stacked with each other,
wherein one of the plurality of structural layers is positioned at the aft end of the tip portion and conforms to the aft end of the tip portion,
wherein one of the plurality of structural layers is positioned at the forward end of the tip portion and conforms to the forward end of the tip portion,
wherein the plurality of compliant layers are curved and facilitate movement between the plurality of structural layers, and
wherein the plurality of structural layers each have a first coefficient of thermal expansion and the plurality of compliant layers each have a second coefficient of thermal expansion, the second coefficient of thermal expansion being greater than the first coefficient of thermal expansion.
12. The leading edge assembly of claim 11 ,
wherein the outer wall includes a first wall section and a second wall section separated by a chamber, and
wherein the plurality of structural layers are curved and extend between the first wall section and the second wall section.
13. The leading edge assembly of claim 11 , wherein the plurality of structural layers are made from different materials.
14. The leading edge assembly of claim 11 , wherein the plurality of structural layers are made from a metal, a ceramic material, or a ceramic matrix composite material.
15. The leading edge assembly of claim 11 , wherein at least two of the plurality of structural layers have different densities.
16. The leading edge assembly of claim 11 , wherein at least two of the plurality of compliant layers are made from different materials.
17. The leading edge assembly of claim 11 , wherein at least one cooling passageway is defined through the plurality of structural layers and the plurality of compliant layers.
18. The leading edge assembly of claim 17 , further comprising:
a coolant supply in fluid communication with the at least one cooling passageway for selectively providing a flow of coolant through the at least one cooling passageway.
19. The leading edge assembly of claim 1 , wherein the outer wall and the tip portion have a uniform thickness.
20. The leading edge assembly of claim 1 , wherein both forward and aft ends of each of the one or more compliant layers are curved.
21. The leading edge assembly of claim 11 , wherein the outer wall and the tip portion have a uniform thickness.
22. The leading edge assembly of claim 11 , wherein both forward and aft ends of each of the plurality compliant layers are curved.