초록 ▼

Embodiments of the present invention relate a wing arrangement for an aerial vehicle configured to adjust the vehicles aspect ratio in response to flight mission parameters. The wing arrangement may include a pair of wing assemblies capable of deploying to a first winged position defining a first as

Embodiments of the present invention relate a wing arrangement for an aerial vehicle configured to adjust the vehicles aspect ratio in response to flight mission parameters. The wing arrangement may include a pair of wing assemblies capable of deploying to a first winged position defining a first aspect ratio. Each wing assembly may have a forward inboard wing pivotally connected to the fuselage and an aft inboard wing pivotally connected to the carriage. The forward inboard wing and aft inboard wing of each assembly may be connected, forming a bi-plane configuration. Additionally, the each assembly may include a set of outboard wings configured to telescope from the inboard wings to an extended winged position defining a second aspect ratio greater than the first aspect ratio.

대표청구항 ▼

What is claimed is: 1. A wing arrangement for an aerial vehicle, comprising: a deployment mechanism configured to attach to a first side of a fuselage and configured to move from a first position to a second position; a first wing configured to be rotationally coupled to a second side of the fusela

What is claimed is: 1. A wing arrangement for an aerial vehicle, comprising: a deployment mechanism configured to attach to a first side of a fuselage and configured to move from a first position to a second position; a first wing configured to be rotationally coupled to a second side of the fuselage; a second wing configured to be rotationally coupled to the deployment mechanism and rotationally coupled to the first wing; a third wing configured to be rotationally coupled to the second side of the fuselage; and a fourth wing configured to be rotationally coupled to the deployment mechanism and rotationally coupled to the third wing; wherein: the wing arrangement has a stowed position, in which: the deployment mechanism is in the first position; the first and third wings are stacked on the second side of the fuselage; and the second and fourth wings are stacked on the first side of the fuselage; and movement of the deployment mechanism from the first position to the second position causes the first and second coupled wings and the third and fourth coupled wings to deploy to a first winged position. 2. The wing arrangement of claim 1, further comprising: a fifth wing configured to be telescopingly stowed substantially inside the first wing; a sixth wing configured to be telescopingly stowed substantially inside the second wing; a seventh wing configured to be telescopingly stowed substantially inside the third wing; and an eighth wing configured to be telescopingly stowed substantially inside the fourth wing; wherein the first and fifth wings are rotationally coupled to the second and sixth wings and the third and seventh wings are rotationally coupled to the fourth and eighth wings. 3. The wing arrangement of claim 2, wherein: in the first winged position, the fifth, sixth, seventh, and eighth wings are substantially stowed within the first, second, third, and fourth wings respectively and the first winged position defines a first aspect ratio; and the fifth, sixth, seventh, and eighth wings are configured to telescope out of the first, second, third, and fourth respectively to a second winged position defining a second aspect ratio. 4. The wing arrangement of claim 3, wherein the second aspect ratio that is greater than the first aspect ratio. 5. The wing arrangement of claim 4, wherein the fifth, sixth, seventh, and eighth wings are configured to deploy to an intermediate position defining a third aspect ratio between the first aspect ratio and the second aspect ratio. 6. A wing arrangement for an aerial vehicle, comprising: a carriage configured to be attached to a fuselage and move from a first position to a second position; a pair of wing assemblies having a stowed position and deployed position, each wing assembly in the deployed position comprising: a forward wing configured to be pivotally coupled to the fuselage and arranged on a first side of the fuselage; an aft wing configured to be pivotally coupled to the carriage and arranged on a second side of the fuselage substantially opposite the first side; and a connector pivotally connecting an outboard end of the forward wing and an outboard end of the aft wing; and an actuator coupled to the fuselage and configured to move the carriage from the first position to the second position whereby movement of the carriage to the second position causes the forward wing and the aft wing of each pair of wing assemblies to deploy from the stowed position to the deployed position. 7. The wing arrangement of claim 6, wherein: the forward wing comprises a forward inboard wing panel in telescoping relation with a forward outboard wing panel; the aft wing comprises a aft inboard wing panel in telescoping relation with an aft outboard wing panel; and the connector pivotally connects the forward outboard wing panel to the aft outboard wing panel. 8. The wing arrangement of claim 7, wherein, in the deployed position, the forward outboard wing panel is stowed substantially within the forward inboard wing panel and the aft outboard wing panel is stowed substantially within the aft inboard wing panel and the deployed position defines a first aspect ratio. 9. The wing arrangement of claim 8, wherein the forward outboard wing panel and the aft outboard wing panel are configured to telescope to an extended position defining a second aspect ratio. 10. The wing arrangement of claim 9, wherein the second aspect ratio is greater than the first aspect ratio. 11. An aerial vehicle having a folding wing arrangement, comprising: a fuselage defining a first side and a second side substantially opposite each other; a carriage connected to the fuselage on the first side and configured to move from a first position to a second position; a pair of wing assemblies having a stowed position and a deployed position, each wing assembly in the deployed position comprising: a first wing pivotally connected to the fuselage on the second side; and a second wing pivotally connected to the carriage and pivotally connected to the first wing; and an actuator connected to the fuselage and configured to translate the carriage from the first position to the second position whereby movement of the carriage to the second position causes the first wing and the second wing of each pair of wing assemblies to deploy from the stowed position to the deployed position. 12. The aerial vehicle of claim 11, wherein: the first wing comprises a first inboard wing panel in telescoping relation with a first outboard wing panel; and the second wing comprises a second inboard wing panel in telescoping relation with a second outboard wing panel, the second outboard wing panel being pivotally connected to the forward outboard wing panel. 13. The aerial vehicle of claim 12, wherein, in the deployed position, the first outboard wing panel is stowed substantially within the first inboard wing panel and the second outboard wing panel is stowed substantially within the second inboard wing panel and the deployed position defines a first aspect ratio. 14. The aerial vehicle of claim 13, wherein the first outboard wing panel and the second outboard wing panel are configured to telescope to an extended winged position defining a second aspect ratio. 15. The aerial vehicle of claim 14, wherein the second aspect ratio is greater than the first aspect ratio. 16. The aerial vehicle of claim 11, wherein the aerial vehicle is at least one of a missile, a munition, a bomb, or an aircraft. 17. A wing arrangement for an aerial vehicle, comprising: a deployment mechanism configured to attach to a first side of a fuselage and configured to move from a first position to a second position; a first wing configured to be rotationally coupled to a second side of the fuselage; a second wing configured to be rotationally coupled to the deployment mechanism and rotationally coupled to the first wing; a third wing configured to be rotationally coupled to the second side of the fuselage; and a fourth wing configured to be rotationally coupled to the deployment mechanism and rotationally coupled to the third wing; a fifth wing configured to be telescopingly stowed substantially inside the first wing; a sixth wing configured to be telescopingly stowed substantially inside the second wing; a seventh wing configured to be telescopingly stowed substantially inside the third wing; and an eighth wing configured to be telescopingly stowed substantially inside the fourth wing; wherein: the first and fifth wings are rotationally coupled to the second and sixth wings and the third and seventh wings are rotationally coupled to the fourth and eighth wings; movement of the deployment mechanism from the first position to the second position causes the first and second coupled wings and the third and fourth coupled wings to deploy to a first winged position. 18. The wing arrangement of claim 17, wherein: in the first winged position, the fifth, sixth, seventh, and eighth wings are substantially stowed within the first, second, third, and fourth wings respectively and the first winged position defines a first aspect ratio; and the fifth, sixth, seventh, and eighth wings are configured to telescope out of the first, second, third, and fourth respectively to a second winged position defining a second aspect ratio. 19. The wing arrangement of claim 18, wherein the second aspect ratio that is greater than the first aspect ratio. 20. The wing arrangement of claim 19, wherein the fifth, sixth, seventh, and eighth wings are configured to deploy to an intermediate position defining a third aspect ratio between the first aspect ratio and the second aspect ratio.