A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) (100, 400, 1000, 1500) configured to control pitch, roll, and/or yaw via airfoils (141, 142, 1345, 1346) having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns (621, 622). Embodiments inc
A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) (100, 400, 1000, 1500) configured to control pitch, roll, and/or yaw via airfoils (141, 142, 1345, 1346) having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns (621, 622). Embodiments include one or more rudder elements (1045, 1046, 1145, 1146, 1245, 1345, 1346, 1445, 1446, 1545, 1546) which may be rotatably attached and actuated by an effector member (1049, 1149, 1249, 1349) disposed within the fuselage housing (1001) and extendible in part to engage the one or more rudder elements.
대표청구항▼
1. An aerial vehicle comprising: a fuselage, comprising a housing;a first airfoil, rotatably attached to the fuselage housing, the first airfoil comprising a first control surface resiliently mounted to the first airfoil, wherein the first control surface is articulated at a lineal joint about the f
1. An aerial vehicle comprising: a fuselage, comprising a housing;a first airfoil, rotatably attached to the fuselage housing, the first airfoil comprising a first control surface resiliently mounted to the first airfoil, wherein the first control surface is articulated at a lineal joint about the first airfoil; anda first actuator horn, disposed in the fuselage housing, the first actuator horn extendible via a first fuselage housing aperture, wherein the first actuator horn is extendible to oppose and contact the first control surface. 2. The aerial vehicle of claim 1, further comprising: a second airfoil, rotatably attached to the fuselage housing, the second airfoil comprising a second control surface resiliently mounted to the second airfoil, wherein the second control surface is articulated at a lineal joint about the second airfoil; anda second actuator horn, disposed in the fuselage housing, the second actuator horn extendible via a second fuselage housing aperture, wherein the second actuator horn is extendible to oppose the second control surface; andwherein the second airfoil opposes the first airfoil about the fuselage housing. 3. The aerial vehicle of claim 2, further comprising: a third airfoil, rotatably attached to the fuselage housing;a fourth airfoil, rotatably attached to the fuselage housing; andwherein the third airfoil opposes the fourth airfoil about an aft portion of the fuselage housing. 4. The aerial vehicle of claim 3, wherein the first airfoil and the second airfoil are disposed at a position distal from the position of the third airfoil and the fourth airfoil. 5. The aerial vehicle of claim 3, further comprising: a third control surface resiliently mounted to the third airfoil, wherein the third control surface is a trailing edge of the third airfoil articulated at a lineal joint about the third airfoil. 6. The aerial vehicle of claim 5, further comprising: a third actuator horn, disposed in the fuselage housing, the third actuator horn extendible via a third fuselage housing aperture, wherein the third actuator horn is extendible to oppose the third control surface. 7. The aerial vehicle of claim 6, further comprising: a fourth control surface resiliently mounted to the fourth airfoil, wherein the fourth control surface is a trailing edge of the fourth airfoil articulated at a lineal joint about the fourth airfoil. 8. The aerial vehicle of claim 7, further comprising: a fourth actuator horn, disposed in the fuselage housing, the fourth actuator horn extendible via a fourth fuselage housing aperture, wherein the fourth actuator horn is extendible to oppose the fourth control surface. 9. The aerial vehicle of claim 2, wherein the aerial vehicle is unmanned during operation. 10. The aerial vehicle of claim 2, wherein the first airfoil is a port airfoil and the second airfoil is a starboard airfoil. 11. The aerial vehicle of claim 3, wherein the first airfoil and the third airfoil are port airfoils, and wherein the second airfoil and the fourth airfoil are starboard airfoils. 12. The aerial vehicle of claim 1, wherein the first fuselage housing aperture is located on a bottom of the fuselage housing, and wherein the first actuator horn is extendible through the first fuselage housing aperture to contact a top surface of the first control surface. 13. The aerial vehicle of claim 2, wherein the second fuselage housing aperture is located on a bottom of the fuselage housing proximate to the first fuselage housing aperture, and wherein the second actuator horn is extendible through the second fuselage housing aperture to contact a top surface of the second control surface. 14. The aerial vehicle of claim 1, wherein the lineal joint about the first airfoil further comprises a coating to fill a lineal gap between the first airfoil and the first control surface. 15. The aerial vehicle of claim 2, wherein the lineal joint about the second airfoil further comprises a coating to fill a lineal gap between the second airfoil and the second control surface. 16. The aerial vehicle of claim 1, wherein the first control surface is a trailing edge of the first airfoil articulated at the lineal joint about the first airfoil. 17. The aerial vehicle of claim 1, wherein the first control surface is a leading edge of the first airfoil articulated at the lineal joint about the first airfoil. 18. The aerial vehicle of claim 2, wherein the second control surface is a trailing edge of the first airfoil articulated at the lineal joint about the first airfoil. 19. The aerial vehicle of claim 2, wherein the second control surface is a leading edge of the first airfoil articulated at the lineal joint about the first airfoil. 20. The aerial vehicle of claim 3, wherein the first airfoil, the second airfoil, the third airfoil, and the fourth airfoil are rotatable between a retracted position disposed on a bottom portion of the fuselage housing and a deployed position perpendicular to a longitudinal axis of the fuselage housing.
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이 특허에 인용된 특허 (22)
Kendall G. Young ; Steven L. Pauletti, Aerodynamic control surface system.
Nicholas Paul H. (Burbank CA) Lipera Larry (Lancaster CA) Justice Stephen G. (Santa Clarita CA) Wurts Joseph M. (Valencia CA), Airborne vehicle with wing extension and roll control.
Tribe Alex E. (Thousand Oaks CA) Bottorff Marion R. (Ventura CA) Cottrell Ronald G. (Thousand Oaks CA) Ranes Richard L. (Simi Valley CA) Whistler William B. (Thousand Oaks CA), Aircraft.
Richard T. Martorana ; Jamie Anderson ; Simon Mark Spearing ; Seth Kessler ; Brent Appleby ; Edward Bergmann ; Sean George ; Steven Jacobson ; Donald Fyler ; Mark Drela ; Gregory Kirkos ; , Flyer assembly.
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