Fluidic split flap systems for yaw control in forward flight
AssigneeTextron Innovations Inc.
InventorsDaniel Bryan Robertson, Kirk Landon Groninga, Matthew Edward Louis
Life of this patent
Estimating the term…
Abstract
An active flow control system for generating yaw control moments for an aircraft during forward flight. The system includes right and left yaw effectors disposed proximate the right and left wingtips of the wing. A pressurized air system includes a pressurized air source and a plurality of injectors operably associated with the right and left yaw effectors that influence the path of airflow above and below the yaw effectors. Based upon which of the injectors is injecting pressurized air, the right and left yaw effectors generate no yaw control moment, generate a yaw right control moment or generate a yaw left control moment.
Claims20
An active flow control system for generating yaw control moments during forward flight of an aircraft having a wing with left and right wingtips, the system comprising:
- a right yaw effector disposed proximate the right wingtip and a left yaw effector disposed proximate the left wingtip;
- and
- a pressurized air system including a pressurized air source coupled to a plurality of injectors, the plurality of injectors including a first injector configured to selectively inject pressurized air substantially transverse to airflow over the right yaw effector, a second injector configured to selectively inject pressurized air substantially transverse to airflow under the right yaw effector, a third injector configured to selectively inject pressurized air substantially transverse to airflow over the left yaw effector and a fourth injector configured to selectively inject pressurized air substantially transverse to airflow under the left yaw effector;
- wherein, when none of the injectors are injecting pressurized air, the right and left yaw effectors are configured to generate no yaw control moment;
- wherein, when the first and second injectors are injecting pressurized air, the right yaw effector is configured to generate a yaw right control moment;
- and
- wherein, when the third and fourth injectors are injecting pressurized air, the left yaw effector is configured to generate a yaw left control moment.
An aircraft comprising:
- a wing with left and right wingtips;
- and
- an active flow control system including:
- a right yaw effector disposed proximate the right wingtip and a left yaw effector disposed proximate the left wingtip;
- and
- a pressurized air system including a pressurized air source coupled to a plurality of injectors, the plurality of injectors including a first injector configured to selectively inject pressurized air substantially transverse to airflow over the right yaw effector, a second injector configured to selectively inject pressurized air substantially transverse to airflow under the right yaw effector, a third injector configured to selectively inject pressurized air substantially transverse to airflow over the left yaw effector and a fourth injector configured to selectively inject pressurized air substantially transverse to airflow under the left yaw effector;
- wherein, when none of the injectors are injecting pressurized air, the right and left yaw effectors are configured to generate no yaw control moment;
- wherein, when the first and second injectors are injecting pressurized air, the right yaw effector is configured to generate a yaw right control moment;
- and
- wherein, when the third and fourth injectors are injecting pressurized air, the left yaw effector is configured to generate a yaw left control moment.
Dependencies are inferred from the claim text.