A jet aircraft includes an aircraft integrated, fluid vectoring, exhaust nozzle system. Implementation of this disclosure may eliminate or reduce the size of the aircraft vertical stabilizer and rudder assembly, thereby potentially improving aircraft survivability and increasing aircraft thrust-to-w
A jet aircraft includes an aircraft integrated, fluid vectoring, exhaust nozzle system. Implementation of this disclosure may eliminate or reduce the size of the aircraft vertical stabilizer and rudder assembly, thereby potentially improving aircraft survivability and increasing aircraft thrust-to-weight ratio.
대표청구항▼
1. An aircraft comprising a body anda fluid-vectoring system coupled to the body and configured to control movement of the body as the body moves along a flight path during flight of the aircraft, the fluid-vectoring system including a first fluid passageway arranged to extend along an axis of the b
1. An aircraft comprising a body anda fluid-vectoring system coupled to the body and configured to control movement of the body as the body moves along a flight path during flight of the aircraft, the fluid-vectoring system including a first fluid passageway arranged to extend along an axis of the body and to define a first fluid cavity therein, an environmental fluid passageway defining an environmental cavity and arranged to communicate a first flow of environmental fluid in a downstream direction from an environment surrounding the aircraft through the environmental cavity into the first fluid passageway, and a first fluid-control unit coupled to the body to move between a retracted configuration in which the first flow of environmental fluid moves downstream from the environment surrounding the aircraft through the environmental cavity, through the first fluid cavity, and to the environment and an engaged configuration in which the first fluid-control unit blocks the first flow of environmental fluid from flowing through the first fluid cavity,wherein the first fluid-control unit includes a first control door coupled to the body to move between an opened position in which the first flow of environmental fluid is communicated through the first fluid cavity and a closed position in which the first control door extends into the first fluid cavity to block communication of the first flow of environmental fluid through the first fluid cavity,wherein the body includes a first bypass passageway defining a first bypass cavity, the first bypass passageway is arranged to communicate a first bypass flow of environmental fluid in the downstream direction from the environment surrounding the aircraft through the first bypass cavity into the first fluid passageway, andwherein the first control door is spaced apart in the downstream direction from an inlet of the environmental fluid passageway, spaced apart in the downstream direction from an inlet of the first bypass passageway, and spaced apart in the upstream direction from an outlet of the first fluid passageway. 2. The aircraft of claim 1, wherein the first fluid-control unit further includes a second control door coupled to the body to move between an opened position in which the first flow of environmental fluid is communicated into the first fluid cavity and a closed position in which the second control door extends into the first fluid cavity to block communication of the first flow of environmental fluid into the first fluid cavity. 3. The aircraft of claim 2, wherein the first fluid-control unit further includes a third control door coupled to the body to move between an opened position in which the first flow of environmental fluid is communicated past the first control door and into the first fluid cavity and a closed position in which the third control door forms an additional cavity in the first fluid cavity when the first control door in the closed position. 4. The aircraft of claim 3, wherein the first control door is movable relative to and independent of the second control door or the third control door. 5. The aircraft of claim 1, wherein the fluid-vectoring system further includes a second fluid passageway arranged to extend along the axis of the body and to define a second fluid cavity therein and a second fluid-control unit coupled to the body to move between a retracted configuration in which a second flow of environmental fluid moves downstream along the axis from the environment surrounding the aircraft, through the second fluid cavity, and to the environment and an engaged configuration in which the second fluid-control unit blocks the second flow of environmental fluid from flowing through the second fluid cavity. 6. The aircraft of claim 5, wherein the fluid-vectoring system is arranged in a forward-flight arrangement when the first fluid-control unit and the second fluid-control unit are in the retracted configurations which causes the aircraft to move at a first velocity in a forward direction. 7. The aircraft of claim 6, wherein the fluid-vectoring system is arranged in an in-flight left-turn arrangement when the first fluid-control unit is in the retracted configuration and the second fluid-control unit is in the engaged configuration which causes the aircraft to turn away from the forward direction in a left-turn direction. 8. The aircraft of claim 7, wherein the fluid-vectoring system is arranged in an in-flight right-turn arrangement when the first fluid-control unit is in the engaged configuration and the second fluid-control unit is in the retracted configuration which causes the aircraft to turn away from the forward direction in a right-turn direction. 9. The aircraft of claim 8, wherein the fluid-vectoring system is arranged in an in-flight braking arrangement when the first fluid-control unit and the second fluid-control unit are in an in-flight braking configuration when the first and second flows of environmental fluid are blocked from flowing downstream through the first and second fluid cavities to cause the aircraft to decelerate to a relatively smaller second velocity. 10. The aircraft of claim 5, wherein the first fluid-control unit includes a first control door coupled to the body to move between an opened position in which the first flow of environmental fluid is communicated through the first fluid cavity and a closed position in which the first control door extends into the first fluid cavity to block communication of the first flow of environmental fluid through the first fluid cavity, a second control door coupled to the body to move between an opened position in which the first flow of environmental fluid is communicated into the first fluid cavity and a closed position in which the second control door extends into the first fluid cavity to block communication of the first flow of environmental fluid into the first fluid cavity, and, a third control door coupled to the body to move between an opened position in which the first flow of environmental fluid is communicated past the first control door and into the first fluid cavity and a closed position in which the third control door forms an additional cavity in the first fluid cavity when the first control door is in the closed position. 11. The aircraft of claim 10, wherein the second fluid-control unit includes a first control door coupled to the body to move between an opened position in which the second flow of environmental fluid is communicated through the second fluid cavity and a closed position in which the first control door of the second fluid-control unit extends into the second fluid cavity to block communication of the second flow of environmental fluid through the second fluid cavity, a second control door coupled to the body to move between an opened position in which the second flow of environmental fluid is communicated into the second fluid cavity and a closed position in which the second control door of the second fluid-control unit extends into the second fluid cavity to block communication of the second flow of environmental fluid into the second fluid cavity, and, a third control door coupled to the body to move between an opened position in which the second flow of environmental fluid is communicated past the first control door of the second fluid-control unit and into the second fluid cavity and a closed position in which the third control door of the second fluid-control unit forms an additional cavity in the second fluid cavity when the first control door of the second fluid-control unit is in the closed position. 12. The aircraft of claim 11, wherein the fluid-vectoring system is in a forward-flight arrangement when all of the control doors are in the opened position. 13. The aircraft of claim 12, wherein the fluid-vectoring system is in an in-flight left-turn arrangement when all of the control doors of the first fluid-control unit are in the opened position and all of the control doors of the second fluid-control unit are in the closed position. 14. The aircraft of claim 13, wherein the fluid-vectoring system is in an in-flight right-turn arrangement when all control doors of the first fluid-control unit are in the closed position and all the control doors of the second fluid-control unit are in the opened position. 15. The aircraft of claim 14, wherein the fluid-vectoring system is in an in-flight braking arrangement when the first control doors of both the first and second fluid-control units are in the closed position and the second and third control doors of both the first and second fluid-control units are in the opened position. 16. The aircraft of claim 1, wherein the fluid-vectoring system further includes a second fluid passageway arranged to extend along the axis of the body and to define a second fluid cavity therein and a second fluid-control unit coupled to the body to move between a retracted configuration in which a second flow of environmental fluid moves downstream along the axis from the environment surrounding the aircraft, through the second fluid cavity, and to the environment and an engaged configuration in which the second fluid-control unit blocks the second flow of environmental fluid from flowing through the second fluid cavity. 17. The aircraft of any preceding claim, wherein the body lacks a vertical stabilizer. 18. A method of controlling movement of an aircraft, the method comprising the steps of providing a craft including a fluid-vectoring system comprising a first fluid passageway controlled by a first fluid-control unit and a second fluid passageway controlled by a second fluid-control unit and lacking a vertical stabilizer, the fluid-vectoring system further comprising a first environmental fluid passageway connected to the first fluid passageway, a first bypass passageway connected to the first fluid passageway, a second environmental fluid passageway connected to the second fluid passageway, and a second bypass passageway connected to the second fluid passageway, the first fluid-control unit including a first control door being spaced apart from an inlet of the first environmental fluid passageway, spaced apart from an inlet of the first bypass passageway, and spaced apart from an outlet of the first fluid passageway, and the second fluid-control unit including a second control door being spaced apart from an inlet of the second environmental fluid passageway, spaced apart from an inlet of the second bypass passageway, and spaced apart from an outlet of the second fluid passageway,arranging the fluid-vectoring system in a forward-flight arrangement to cause a flow of environmental fluid to communicate through the first fluid passageway and a flow of environmental fluid to communicate through the second fluid passageway,arranging the fluid-vectoring system in an in-flight left-turn arrangement to cause a left yaw turn by allowing a flow of environmental fluid to communicate through the first fluid passageway and by blocking a flow of environmental fluid from communicating through the second fluid passageway,arranging the fluid-vectoring system in a right-turn arrangement to cause a right yaw turn by blocking a flow of environmental fluid from communicating through the first fluid passageway and by allowing a flow of environmental fluid to communicate through the second fluid passageway, andarranging the fluid-vectoring system in an in-flight braking arrangement by preventing a flow of environmental fluid through the first fluid passage way and by preventing a flow of environmental fluid through the second fluid passage way.
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이 특허에 인용된 특허 (8)
Thayer Edward B. (Palm Beach Gardens FL), Gas turbine vectoring exhaust nozzle.
Walker, Alan Richard; Wooten, Jr., William Harvey; Sutherland, William Van; Holowach, Joseph, Infrared suppressing two dimensional vectorable single expansion ramp nozzle.
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