IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0867114
(2004-06-14)
|
발명자
/ 주소 |
- Englar,Robert J.
- Bushnell,Dennis M.
|
출원인 / 주소 |
- Georgia Tech Research Corp.
|
대리인 / 주소 |
Thomas, Kayden, Horstemeyer &
|
인용정보 |
피인용 횟수 :
8 인용 특허 :
12 |
초록
▼
An aircraft comprising a Channel Wing having blown channel circulation control wings (CCW) for various functions. The blown channel CCW includes a channel that has a rounded or near-round trailing edge. The channel further has a trailing-edge slot that is adjacent to the rounded trailing edge of th
An aircraft comprising a Channel Wing having blown channel circulation control wings (CCW) for various functions. The blown channel CCW includes a channel that has a rounded or near-round trailing edge. The channel further has a trailing-edge slot that is adjacent to the rounded trailing edge of the channel. The trailing-edge slot has an inlet connected to a source of pressurized air and is capable of tangentially discharging pressurized air over the rounded trailing edge. The aircraft further has a propeller that is located in the channel and ahead of the rounded trailing edge of the channel. The propeller provides a propeller thrust exhaust stream across the channel wing to propel the aircraft through the air and to provide high lift. The pressurized air being discharged over the rounded trailing edge provides a high lift that is obtained independent of an aircraft angle of attack, thus preventing the asymmetry, separated flow, and stall experienced by the CC wing at the high angle of attack it required for high lift generation. The aircraft can further include blown outboard circulation control wings (CCW) that are synergistically connected to the blown channel CCWs. The blown outboard CCWs provide additional high lift, control thrust/drag interchange, and can provide all three aerodynamic moments when differential blowing is applied front-to-rear or left-to-right. Both the blown channel CCW and the outboard CCW also have leading-edge blowing slots to prevent flow separation or to provide aerodynamic moments for control.
대표청구항
▼
The invention claimed is: 1. An aircraft comprising: a channel wing having a blown channel circulation control wing (CCW), the blown channel CCW having a channel that has a substantially rounded trailing edge, the channel further having a trailing-edge slot that is adjacent to the substantially rou
The invention claimed is: 1. An aircraft comprising: a channel wing having a blown channel circulation control wing (CCW), the blown channel CCW having a channel that has a substantially rounded trailing edge, the channel further having a trailing-edge slot that is adjacent to the substantially rounded trailing edge of the channel, the trailing-edge slot having an inlet connected to a source of pressurized air and the trailing-edge slot being capable of tangentially discharging pressurized air at a blowing rate over the substantially rounded trailing edge; and a propeller being located in the channel and being ahead of the substantially rounded trailing edge and aft of a leading edge of the blown channel CCW, the propeller providing a propeller thrust and increased inflow velocity in a near-circular flow stream across the channel wing, wherein the propeller thrust in the near-circular flow stream across the channel wing is deflected by the pressurized air being discharged over the substantially rounded trailing edge, which provides a high lift that is obtained independent of an aircraft angle of attack, thus preventing the asymmetry, separated flow, and stall typically experienced by an unblown channel wing at the high angle of attack it required for high lift generation. 2. The aircraft as defined in claim 1, wherein the pressurized air that is discharged from the trailing-edge slot over the rounded trailing edge remains attached to the channel rounded trailing edge of the channel by balancing reduced static pressure with centrifugal force, the pressurized air being capable of discharging at various blowing rates, the propeller thrust being capable of deflecting pneumatically, due to entrainment from the pressurized air of the trailing-edge slot of the channel, to thrust angles from 0째 to 85째 from the horizontal, thus providing high lift of much higher magnitude than just vectored thrust, thus allowing SuperSTOL at low angle of attack, due to entrainment by the blown channel of the nearly round propeller exhaust stream. 3. The aircraft as defined in claim 2, wherein the propeller thrust is deflected pneumatically, due to entrainment from the pressurized air of the trailing-edge slot, to thrust angles of approximately 90 degrees from a horizontal plane, thus allowing Vertical Takeoff and Landing (VTOL) operation at low angle of attack. 4. The aircraft as defined in claim 2, wherein the blowing rate of the trailing-edge slot is increased to yield higher propeller thrust deflection up to 165째 and thus the capability for in-flight thrust reversal. 5. The aircraft as defined in claim 1, wherein the wing further comprises a blown outboard Circulation Control Wing (CCW), wherein the trailing-edge slot and the rounded trailing edge extends to the outboard CCW, the trailing-edge slot of the outboard CCW being capable of tangentially discharging pressurized air over the rounded trailing edge, wherein the pressurized air of the trailing-edge slot provides aerodynamic lift, drag change, and moments for trim and for stability & control. 6. The aircraft as defined in claim 5, wherein the aircraft comprises a left blown outboard CCW and a right blown outboard CCW, the aircraft having differential blowing of the trailing-edge slots of the left and right blown outboard CCWs, wherein the differential blowing is the blowing rate of the left blown outboard CCWs being different from the blowing rate of the right blown outboard CCWs, wherein the differential blowing rate yields aerodynamic moments. 7. The aircraft as defined in claim 5, further comprising a spanwise variation in the blowing rate of the trailing-edge slot of the outboard CC wing to tailor a spanwise lift distribution, and thus minimize the induced drag on the outboard CC wing, without any moving surfaces. 8. The aircraft as defined in claim 5, further comprising a spanwise variation in the blowing rate of the trailing-edge slot of both the channel and the outboard CC wing so that spanwise control of lift distribution and drag across the entire lifting wing is achieved. 9. The aircraft as defined in claim 1, wherein either the discharging-pressurized-air rate or propeller thrust is adjustable so that the lift and thrust deflection can be changed, and not by changing aircraft angle of attack, so that no moving surfaces other than the propeller are necessary to yield either high lift or thrust deflection. 10. The aircraft as defined in claim 9, wherein the pressurized air from a section of the trailing-edge slot along the channel is selectively discharged to yield side forces or lateral and directional moment control, and/or pitching moment control. 11. The aircraft as defined in claim 10, wherein the pressurized air from the trailing-edge slot of the channel is differentially or partially discharged to vary the spanwise lift distribution and thus the induced drag. 12. The aircraft as defined in claim 1, wherein the channel wing further comprises a leading-edge slot that discharges pressurized air tangentially at a leading edge of the channel wing to control the leading-edge flow separation so as to facilitate eliminating leading-edge stall of the channel, flow asymmetry into the propeller and the resulting instability. 13. The aircraft as defined in claim 12, wherein the leading-edge slot extends from the channel to the outboard along to the leading edge of the channel wing so as to facilitate preventing leading-edge separation as well as generating lift. 14. The aircraft as defined in claim 12, wherein the leading-edge slot discharges pressurized air at the leading edge, wherein the discharging pressurized air from the leading-edge slot creates a suction at the leading edge and thus provides a nose-up pitching moment to trim out a nose-down moment that is caused by the discharging pressurized air at the trailing edge of the CC wing. 15. The aircraft as defined in claim 14, wherein the discharging pressurized air from both the leading-edge and trailing-edge slots varies the lift, drag, thrust deflection and aerodynamic moments that can be made to occur very rapidly, and thus yield rapid response for flight and control of the aircraft because the aircraft does not depend on any moving external surfaces, but only on air pressure flow variation into the CC wing surfaces. 16. The aircraft as defined in claims 4, wherein the propeller thrust can be varied so that the variation of propeller thrust plus the discharging rate of pressurized air of the trailing-edge slots can interchange thrust and drag as needed during takeoff and landing, without any moving parts other than the propeller. 17. The aircraft as defined in claim 1, wherein the location of the propeller in the channel between the aft trailing edge and the forward leading edge substantially eliminates perceived propeller noise on the ground and substantially eliminates the possibility of contact between passengers and the propellers when the aircraft is on the ground during loading or unloading. 18. The aircraft as defined in claims 1, wherein the aircraft is one of a combined, synergistic, integrated Pneumatic (blown) Channel Wing VSTOL and Super Short Takeoff and Landing (Super STOL) aircraft, varying all aerodynamic and powered-lift characteristics, forces and moments merely by varying blowing air pressure, blowing air flow and/or propeller thrust, without any other external moving parts, wherein the aircraft combines the unblown channel wing, the blown channel wing CCW, and the blown outboard CCW to give far greater lift and control then any of the individual wing elements and is controlled by blowing air without any moving parts other than the propeller in the channel.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.