Aug 25, 2026

US12716701 - Regulation of aerodynamic loads on aircraft and missiles using azimuthally-controllable, segmented aerodynamic forebody bleed actuation

The present disclosure generally relates to systems and methods for controlling aerodynamic loads on an aerostructure. The present disclosure can include a system including an outer shell, the outer shell including at least one aperture, and an inner shell having an aperture therethrough. The at least one aperture of the outer shell can be part of an array of apertures azimuthally distributed on the outer shell. The system can further include an actuator configured to control a rotational alignment of one of the inner shell and the outer shell to alter aerodynamic bleed through a portion of the at least one aperture of the outer shell. The actuator can be configured alter the rotational alignment of the inner shell and the outer shell based at least in part on a desired steering direction of the aerostructure.

Assignee: Georgia Tech Research Corporation
Inventors: Ari Glezer, Bojan Vukasinovic, Edward Lee
Filing date: 2024-11-18

This patent relates to a system designed to regulate aerodynamic loads on aerostructures by utilizing an outer shell with apertures and overlapping inner shells that feature their own apertures. An actuator is included to control the rotational alignment of the shells, allowing for adjustments in aerodynamic bleed based on the desired steering direction.

Claim 1

1 . A system for regulation of aerodynamic loads comprising: an outer shell comprising at least one aperture; a first inner shell having an aperture therethrough; a second inner shell having an aperture therethrough; and an actuator; wherein: the respective inner shell apertures extend azimuthally around a portion of the respective inner shell; the first inner shell and the second inner shell overlap, such that the inner shell apertures form a relative azimuthal aperture; and the actuator is configured to control a rotational alignment of the inner shells and the outer shell to alter aerodynamic bleed through at least a portion of at least one aperture of the outer shell. an outer shell comprising at least one aperture; a first inner shell having an aperture therethrough; a second inner shell having an aperture therethrough; and an actuator; wherein: the respective inner shell apertures extend azimuthally around a portion of the respective inner shell; the first inner shell and the second inner shell overlap, such that the inner shell apertures form a relative azimuthal aperture; and the actuator is configured to control a rotational alignment of the inner shells and the outer shell to alter aerodynamic bleed through at least a portion of at least one aperture of the outer shell. the respective inner shell apertures extend azimuthally around a portion of the respective inner shell; the first inner shell and the second inner shell overlap, such that the inner shell apertures form a relative azimuthal aperture; and the actuator is configured to control a rotational alignment of the inner shells and the outer shell to alter aerodynamic bleed through at least a portion of at least one aperture of the outer shell.

Google Patents

https://patents.google.com/patent/US12716701

USPTO PDF

https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/12716701