초록 ▼

An aircraft control structure can be utilized for purposes of drag management, noise control, or aircraft flight maneuvering. The control structure includes a high pressure engine nozzle, such as a bypass nozzle or a core nozzle of a turbofan engine. The nozzle exhausts a high pressure fluid stream,

An aircraft control structure can be utilized for purposes of drag management, noise control, or aircraft flight maneuvering. The control structure includes a high pressure engine nozzle, such as a bypass nozzle or a core nozzle of a turbofan engine. The nozzle exhausts a high pressure fluid stream, which can be swirled using a deployable swirl vane architecture. The control structure also includes a variable geometry pylon configured to be coupled between the nozzle and the aircraft. The variable geometry pylon has a moveable pylon section that can be deployed into a deflected state to maintain or alter a swirling fluid stream (when the swirl vane architecture is deployed) for drag management purposes, or to assist in the performance of aircraft flight maneuvers.

대표청구항 ▼

1. An aircraft control structure comprising: a nozzle assembly configured to exhaust a swirling fluid stream; anda pylon configured to be coupled between the nozzle assembly and an aircraft support structure, the pylon comprising a moveable pylon section positioned proximate an exit end of the nozzl

1. An aircraft control structure comprising: a nozzle assembly configured to exhaust a swirling fluid stream; anda pylon configured to be coupled between the nozzle assembly and an aircraft support structure, the pylon comprising a moveable pylon section positioned proximate an exit end of the nozzle assembly such that when deployed into a deflected state the moveable pylon section maintains the swirling fluid stream. 2. The aircraft control structure of claim 1, wherein the nozzle assembly comprises: a nozzle; anda plurality of swirl vanes positioned in the nozzle to produce the swirling fluid stream. 3. The aircraft control structure of claim 2, wherein the plurality of swirl vanes and the moveable pylon section are deployed to assist in drag management. 4. The aircraft control structure of claim 2, wherein the plurality of swirl vanes and the moveable pylon section are actuated in concert. 5. The aircraft control structure of claim 2, wherein the nozzle is a bypass nozzle of a turbofan engine. 6. The aircraft control structure of claim 2, wherein the nozzle is a core nozzle of a turbofan engine. 7. The aircraft control structure of claim 1, wherein the moveable pylon section is moveably coupled at a trailing end of the pylon. 8. The aircraft control structure of claim 1, further comprising a fence structure positioned overlying the moveable pylon section and configured to cover an opening between the pylon and the moveable pylon section when the moveable pylon section is deployed. 9. An aircraft subsystem comprising: a first engine configured to exhaust a first high pressure fluid stream;a first variable geometry deployable pylon configured to be coupled between the first engine and an aircraft, the first variable geometry deployable pylon comprising a first moveable pylon section positioned proximate an exit end of the first engine to influence a primary component of thrust of the first high pressure fluid stream; anda control system to actuate the first moveable pylon section into a deflected state to redirect the first high pressure fluid stream and alter its primary component of thrust in accordance with a flight maneuver command for the aircraft. 10. The aircraft subsystem of claim 9, further comprising: a second engine configured to exhaust a second high pressure fluid stream; anda second variable geometry deployable pylon configured to be coupled between the second engine and the aircraft, the second variable geometry deployable pylon comprising a second moveable pylon section positioned proximate an exit end of the second engine to influence a primary component of thrust of the second high pressure fluid stream;wherein the control system actuates the second moveable pylon section into a deflected state to redirect the second high pressure fluid stream and alter its primary component of thrust in accordance with the flight maneuver command. 11. The aircraft subsystem of claim 10, wherein: the first engine, the first variable geometry deployable pylon, and the first moveable pylon section are associated with a port side engine of the aircraft; andthe second engine, the second variable geometry deployable pylon, and the second moveable pylon section are associated with a starboard side engine of the aircraft. 12. The aircraft subsystem of claim 10, wherein the control system actuates the first moveable pylon section and the second moveable pylon section in concert with one another. 13. The aircraft subsystem of claim 10, wherein the control system actuates the first moveable pylon section and the second moveable pylon section independently. 14. The aircraft subsystem of claim 9, further comprising a fence structure positioned overlying the first moveable pylon section and configured to cover an opening between the first variable geometry pylon and the first moveable pylon section when the first moveable pylon section is deployed. 15. An aircraft subsystem comprising: a first nozzle and a first swirl vane assembly configured to exhaust a first swirling fluid stream;a first variable geometry deployable pylon configured to be coupled between the first nozzle and an aircraft, the first variable geometry deployable pylon comprising a first moveable pylon section positioned proximate an exit end of the first nozzle such that when deployed into a deflected state the first moveable pylon section influences the first swirling fluid stream;a second nozzle and a second swirl vane assembly configured to exhaust a second swirling fluid stream;a second variable geometry deployable pylon configured to be coupled between the second nozzle and the aircraft, the second variable geometry deployable pylon comprising a second moveable pylon section positioned proximate an exit end of the second nozzle such that when deployed into a deflected state the second moveable pylon section influences the second swirling fluid stream; anda control system to regulate deployment of the first swirl vane assembly, deployment of the second swirl vane assembly, and deflected positions of the first moveable pylon section and the second moveable pylon section in accordance with a drag management command for the aircraft. 16. The aircraft subsystem of claim 15, wherein: the first nozzle, the first swirl vane assembly, the first variable geometry deployable pylon, and the first moveable pylon section are associated with a port side engine of the aircraft; andthe second nozzle, the second swirl vane assembly, the second variable geometry deployable pylon, and the second moveable pylon section are associated with a starboard side engine of the aircraft. 17. The aircraft subsystem of claim 15, wherein the control system deploys the first swirl vane assembly, the first moveable pylon section, the second swirl vane assembly, and the second moveable pylon section in concert with one another. 18. The aircraft subsystem of claim 15, wherein the control system moves the first moveable pylon section and the second moveable pylon section into deflected positions aligned with the first swirling fluid stream and the second swirling fluid stream, respectively, to maintain swirling of the first swirling fluid stream and the second swirling fluid stream. 19. The aircraft subsystem of claim 15, wherein the control system moves the first moveable pylon section and the second moveable pylon section into deflected positions misaligned with the first swirling fluid stream and the second swirling fluid stream, respectively, to reduce swirling of the first swirling fluid stream and the second swirling fluid stream.