Aerospace vehicle flow body systems and associated methods
First Claim
1. An aerospace vehicle system, comprising:
- a first flow body coupleable to an aerospace vehicle;
a second flow body having a first portion rigidly connected to a second portion, the second portion of the second flow body being laterally disposed from the first portion of the second flow body, the first portion having a first chord line and being rotatably coupled to the first flow body at a first hinge point positioned away from the first chord line, the first hinge point having a first hinge axis, the second portion having a second chord line and being rotatably coupled to the first flow body at a second hinge point positioned away from the second chord line, the second hinge point having a second hinge axis, the second flow body being rotatable about a hinge line between a stowed position and a deployed position, the hinge line being positioned to be swept relative to a longitudinal axis of the aerospace vehicle when the first flow body is coupled to the aerospace vehicle, the hinge line being nonparallel with the first hinge axis; and
at least one self-aligning mechanism coupled between the first flow body and the second flow body at the first hinge point, the at least one self-aligning mechanism including a non-cylindrical interface between a first surface connected to the first flow body and a second surface connected to the second flow body, at least one of the first and second surfaces being rotatable relative to the other to allow the second flow body to rotate about the hinge line and the first and second hinge axes along a generally conical motion path between the stowed position and the deployed position.
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Accused Products
Abstract
Flow body systems and associated methods, including aerospace vehicle control surface systems are disclosed herein. One aspect of the invention is directed toward an aerospace vehicle system that includes a first flow body that can be coupleable to an aerospace vehicle. The system can further included a second flow body that includes a chord line and can be rotatably coupled to the first flow body at a hinge point positioned away from the chord line. The hinge point can have a hinge axis. The hinge line can extend through the hinge point, but being nonparallel with the hinge axis. The system can still further include at least one self-aligning mechanism coupled between the first flow body and the second flow body. The at least one self-aligning mechanism can be positioned to allow the second flow body to rotate about the hinge line and the hinge axis.
329 Citations
22 Claims
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1. An aerospace vehicle system, comprising:
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a first flow body coupleable to an aerospace vehicle; a second flow body having a first portion rigidly connected to a second portion, the second portion of the second flow body being laterally disposed from the first portion of the second flow body, the first portion having a first chord line and being rotatably coupled to the first flow body at a first hinge point positioned away from the first chord line, the first hinge point having a first hinge axis, the second portion having a second chord line and being rotatably coupled to the first flow body at a second hinge point positioned away from the second chord line, the second hinge point having a second hinge axis, the second flow body being rotatable about a hinge line between a stowed position and a deployed position, the hinge line being positioned to be swept relative to a longitudinal axis of the aerospace vehicle when the first flow body is coupled to the aerospace vehicle, the hinge line being nonparallel with the first hinge axis; and at least one self-aligning mechanism coupled between the first flow body and the second flow body at the first hinge point, the at least one self-aligning mechanism including a non-cylindrical interface between a first surface connected to the first flow body and a second surface connected to the second flow body, at least one of the first and second surfaces being rotatable relative to the other to allow the second flow body to rotate about the hinge line and the first and second hinge axes along a generally conical motion path between the stowed position and the deployed position. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
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9. An aerospace vehicle system, comprising:
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a first flow body that includes a wing connected to an aerospace vehicle; a second flow body that includes a flap having a chord line and being rotatably coupled to the first flow body at two hinge points positioned away from the chord line, each hinge point having a hinge axis, the second flow body being rotatable about a hinge line between a first position and a second position, the hinge line extending through the hinge points, but being nonparallel with the hinge axes; and at least one self-aligning mechanism coupled between the first flow body and the second flow body at each of the two hinge points, the at least one self-aligning mechanism including a non-cylindrical interface between a first surface connected to the first flow body and a second surface connected to the second flow body, at least one of the first and second surfaces being rotatable relative to the other as the second flow body rotates about the hinge line and the hinge axes along a generally conical motion path between the first position and the second position. - View Dependent Claims (10, 11, 12, 13, 14, 15)
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16. A method for making an aerospace vehicle system, comprising:
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rotatably coupling a flap to a wing at two hinge points positioned away from a chord line of the flap, each hinge point having a hinge axis, the first flow body being coupleable to an aerospace vehicle; and coupling at least one self-aligning mechanism between the wing and the flap so that the second flow body simultaneously rotates about a hinge line and the hinge axes as the flap moves between a first position and a second position, the hinge line extending through the hinge points, but being nonparallel with the hinge axes, the self-aligning mechanism including a non-cylindrical interface between a first surface connected to the wing and a second surface connected to the flap, at least one of the first and second surfaces being rotatable relative to the other as the flap moves relative to the wing along a generally conical motion path between the first and second positions. - View Dependent Claims (17, 18, 19, 20, 21)
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22. An aerospace vehicle system, comprising:
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a first flow body connected to an aerospace vehicle, the first flow body including an airfoil section; a second flow body that includes a flap section, the second flow body having a first portion rigidly connected to a second portion, the second portion of the second flow body being laterally disposed from the first portion of the second flow body, the first portion having a first chord line and being rotatably coupled to the first flow body at a first hinge point positioned away from the first chord line, the first hinge point having a first hinge axis, the second portion having a second chord line and being rotatably coupled to the first flow body at a second hinge point positioned away from the second chord line, the second hinge point having a second hinge axis, the second flow body being rotatable about a hinge line between a first position and a second position, the hinge line being positioned to be swept relative to a longitudinal axis of the aerospace vehicle when the first flow body is coupled to the aerospace vehicle, the hinge line being nonparallel with the first hinge axis; first, second and third self-aligning mechanisms coupled between the first flow body and the second flow body, the self-aligning mechanisms being positioned to allow the second flow body to rotate about the hinge line and the first and second hinge axes; a drive device having a first portion and a second portion movable relative to the first portion of the drive device, the first portion of the drive device being connected directly to the airfoil section and the second portion of the drive device being connected directly to the flap section, the drive device being positioned so that the first and second portions of the drive device move relative to one another in a plane having an axis that runs at least approximately parallel to the longitudinal axis of the aerospace vehicle when the airfoil section is coupled to the aerospace vehicle; a support having a first portion coupled to the airfoil section and a second portion; a first link having a first portion and second portion, the first portion of the first link being structurally coupled to the first portion of the flap section via only the first self-aligning mechanism; and a second link having a first portion, a second portion, and a third portion, the first portion of the second link being structurally coupled to the second portion of the first link and the second portion of the support via only the second self-aligning mechanism, the second self-aligning mechanism being positioned to create at least a portion of the first hinge point, the second portion of the second link being structurally coupled to the first portion of the flap section via only the third self-aligning mechanism, the third portion of the second link being coupled to the second portion of the drive device.
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Specification