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US 11,459,085 B2Granted
Energy attenuation stabilizers and methods
AssigneeTextron Innovations Inc.
InventorsEric Sinusas, Guillaume Noiseux-Boucher, Olivier Boisvert, Nicolas Doyon, Sebastien Duval
Life of this patent
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Abstract
According to one implementation of the present disclosure, a stabilizer of an aircraft includes an energy attenuating portion. The energy attenuating portion includes first and second edge sections separated by an adaptable section. The adaptable section may be rigid in a first range of directions and compressible in a second range of directions.
Claims12
A stabilizer of an aircraft comprising:
- an energy attenuating portion comprising:
- first and second edge sections separated by a lattice structure, the lattice structure including, a substrate that defines a plurality of cells, each configured to attenuate energy upon deformation, and comprising
- one or more nodes having a first thickness to transfer aerodynamic loads, and
- one or more free walls having a second thickness that is different from the first thickness to attenuate an impact load;
- wherein the substrate has a first stiffness value in a first direction and a second stiffness value in a second direction, the first direction is substantially perpendicular to the second section, and the first stiffness value is different than the second stiffness value.
2 more elements
A stabilizer of an aircraft comprising:
- an energy attenuating portion comprising:
- a fiber-laid skin;
- and
- a lattice structure enclosed within the fiber-laid skin, including a substrate that defines a plurality of cells, each configured to attenuate energy upon deformation, and comprising
- one or more nodes having a first thickness to transfer aerodynamic loads, and
- one or more free walls having a second thickness that is different from the first thickness to attenuate an impact load;
- wherein the substrate has a first stiffness value in a first direction and a second stiffness value in a second direction, the first direction is substantially perpendicular to the second section, and the first stiffness value is different than the second stiffness value.
4 more elements
Dependencies are inferred from the claim text.