IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0623042
(2007-01-12)
|
등록번호 |
US-8657226
(2014-02-25)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
Cherskov Flaynik & Gurda, LLC
|
인용정보 |
피인용 횟수 :
5 인용 특허 :
12 |
초록
▼
Multiple initiatives are applied to achieve synergistic control enhancement and drag reduction benefits in an aircraft having independent airfoils producing downward force opposite to wing lift in normal flight, which are supported in specific wingtip locations. A method is disclosed teaching the ex
Multiple initiatives are applied to achieve synergistic control enhancement and drag reduction benefits in an aircraft having independent airfoils producing downward force opposite to wing lift in normal flight, which are supported in specific wingtip locations. A method is disclosed teaching the exemplary stall resistance and control at high angles of attack demonstrated by preferred embodiments of the invention.
대표청구항
▼
1. An apparatus forming an aircraft which is designed for flight by movement through the air, said aircraft having front and rear portions and a center of mass, said aircraft having left and right sides when divided by a central plane of reference, said aircraft having thereby inboard portions close
1. An apparatus forming an aircraft which is designed for flight by movement through the air, said aircraft having front and rear portions and a center of mass, said aircraft having left and right sides when divided by a central plane of reference, said aircraft having thereby inboard portions closer to said central plane of reference and outboard portions farther from said central plane of reference, comprising: at least one aerodynamic lifting surface configured to affect the flow of air near said at least one aerodynamic lifting surface when said aircraft is appropriately moving forward, said at least one aerodynamic lifting surface thereby configured to create positive lift when said aircraft is appropriately moving forward, said at least one aerodynamic lifting surface thereby forming at least one wing, said at least one wing having a center of lift which is rearward of said center of mass of said aircraft in flight;at least one airfoil structure comprising a means for creating aerodynamic force when said aircraft is appropriately moving forward, said at least one airfoil structure positioned predominantly rearward of said at least one wing and entirely above said at least one wing, said at least one airfoil structure having a direction of aerodynamic force generally opposite that of said at least one wing when compared to said at least one wing, thus providing the aircraft with positive pitch stability when the aircraft is in trimmed level flight, wherein said means for creating downward aerodynamic force by said at least one airfoil structure is said at least one airfoil structure having an inverted angle of attack when compared to said at least one wing in trimmed level flight, said at least one airfoil structure spaced from said flow of air near said at least one wing, said at least one airfoil structure occurring on both said left and right sides of said central plane of reference, said at least one airfoil structure having at least one center of aerodynamic force which is rearward of said center of lift, said at least one airfoil structure is of sturdy construction appropriate with regard to said aerodynamic force, said at least one airfoil structure is adjustable to vary said aerodynamic force of said at least one airfoil structure to thereby provide at least partial control of said aircraft when said aircraft is appropriately moving forward;wherein said at least one airfoil structure is constructed so as to have outboard portions thereof positioned outward of said central plane of reference to a distance at least four-fifths of the distance from said central plane of reference to a tip end of said at least one wing and wherein the aircraft center of gravity is forward of said center of wing lift. 2. An apparatus according to claim 1 wherein the at least one airfoil structure is spaced from the at least one wing without direct structural connection to a fuselage. 3. An apparatus according to claim 1 wherein the at least one airfoil structure is mounted upon the at least one wing. 4. An apparatus according to claim 1 wherein the at least one airfoil structure is mounted upon the at least one wing and spaced above the at least one wing tip. 5. An apparatus according to claim 1 wherein the at least one airfoil structure is mounted upon the at least one wing using a plurality of upwardly extending airfoil supports extending from said at least one wing to said at least one airfoil structure. 6. An apparatus according to claim 1 wherein the at least one airfoil structure has at least one unadjustable portion configured with respect to said at least one airfoil structure. 7. An apparatus according to claim 1 wherein the at least one airfoil structure pivots upon a generally spanwise axis. 8. An apparatus according to claim 1 wherein the aircraft may be controlled by means of adjustable positioning of at least part of the at least one airfoil structure; said at least one airfoil structure thereby providing at least partial control of said aircraft when said aircraft is appropriately moving forward. 9. An apparatus according to claim 1 wherein the center of mass is behind the center of lift when the aircraft is inappropriately loaded. 10. An apparatus according to claim 1 wherein the center of mass is behind the center of lift when the aircraft is empty. 11. The apparatus of claim 1, wherein said at least one downforce airfoil structure extends substantially perpendicular to said central plane when said apparatus is viewed from the front portion. 12. An apparatus forming an aircraft which is designed for flight by movement through the air, said aircraft having front and rear portions and a center of mass, said aircraft having left and right sides when divided by a central plane of reference, said aircraft having thereby inboard portions closer to said central plane of reference and outboard portions farther from said central plane of reference, said aircraft configured with respect to a downward direction and an upward direction, comprising: at least one aerodynamic lifting surface configured to affect the flow of air near said at least one aerodynamic lifting surface when said aircraft is appropriately moving forward, said at least one aerodynamic lifting surface thereby configured to create positive upward lift when said aircraft is appropriately moving forward, said at least one aerodynamic lifting surface having a center of lift which is rearward of said center of mass of said aircraft in flight;at least one downforce airfoil structure comprising a means for creating downward aerodynamic force when said aircraft is appropriately moving forward, said at least one downforce airfoil structure positioned predominantly rearward of said at least one aerodynamic lifting surface and entirely above said at least one aerodynamic lifting surface, said at least at least one downforce airfoil structure having a direction of said downward aerodynamic force generally opposite to the direction of said positive lift of said at least one aerodynamic lifting surface, said at least one downforce airfoil structure configured to create a magnitude of said downward aerodynamic force sufficient to thus provide the aircraft with positive pitch stability when the aircraft is is in trimmed level flight, wherein said means for creating positive pitch stability when the aircraft is in trimmed level flight is said at least one downforce airfoil structure having an inverted angle of attack when compared to the at least one aerodynamic lifting surface in trimmed level flight, said at least one downforce airfoil structure spaced from said flow near said at least one aerodynamic lifting surface, said at least one downforce airfoil structure occurring on both said left and right sides of said central plane of reference, said at least one downforce airfoil structure having at least one center of said downward aerodynamic force in which said at least one center is rearward of said center of lift, said at least one downforce airfoil structure is of sturdy construction appropriate with regard to said aerodynamic force; wherein said at least one downforce airfoil structure is constructed so as to have outboard portions thereof positioned outward of said central plane of reference to a distance at least four-fifths of the distance from said central plane of reference to a tip end of said at least one aerodynamic lifting surface andwherein the aircraft center of mass is forward of said center of positive aerodynamic lift. 13. The apparatus of claim 12, wherein said at least one downforce airfoil structure extends substantially perpendicular to said central plane when said apparatus is viewed from the front portion. 14. The apparatus of claim 1, wherein the means for creating downward aerodynamic force by said at least one airfoil structure further comprises the provision of negative camber relative to said at least one wing. 15. The apparatus of claim 14, wherein said at least one airfoil structure further comprises a fixed portion and a moving portion, wherein said moving portion can be moved relative to the fixed portion to vary the said at least one airfoil structure's camber and angle of attack. 16. The apparatus of claim 12, wherein the means for creating downward aerodynamic force by said at least one downforce airfoil structure further comprises the provision of negative camber relative to said at least one wing. 17. The apparatus of claim 16, wherein said at least one downforce airfoil structure further comprises a fixed portion and a moving portion, wherein said moving portion can be moved relative to the fixed portion to vary the said at least one downforce airfoil structure's camber and angle of attack.
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