초록 ▼

A seat support having a clevis having an annular base and upper and lower arms rotatably mounted on and extending radially outward from the annular base; at least a first support column extending downwardly from the annular base; seat mounting ball bushings having at least a first laterally extendin

A seat support having a clevis having an annular base and upper and lower arms rotatably mounted on and extending radially outward from the annular base; at least a first support column extending downwardly from the annular base; seat mounting ball bushings having at least a first laterally extending tongue, the at least first tongue being received by the clevis; and at least a first clevis pin attaching the at least first tongue to the clevis.

대표청구항 ▼

A seat support having a clevis having an annular base and upper and lower arms rotatably mounted on and extending radially outward from the annular base; at least a first support column extending downwardly from the annular base; seat mounting ball bushings having at least a first laterally extendin

A seat support having a clevis having an annular base and upper and lower arms rotatably mounted on and extending radially outward from the annular base; at least a first support column extending downwardly from the annular base; seat mounting ball bushings having at least a first laterally extending tongue, the at least first tongue being received by the clevis; and at least a first clevis pin attaching the at least first tongue to the clevis. of the fuselage; first and second counter-rotating, variable pitch rotor assemblies coaxially mounted within the duct of the fuselage; and at least one canard wing secured to the toroidal fuselage and having a leading edge positioned out of the duct of the fuselage and axially forward of the leading edge of the fuselage, wherein at least a portion of the at least one canard wing comprises a control surface having a variable angle of attack, wherein the at least one canard wing includes a trailing edge positioned out of the duct of the fuselage and axially forward of the leading edge of the fuselage. 2. An aerial vehicle according to claim 1, wherein the entire at least one canard wing comprises a control surface. 3. An aerial vehicle according to claim 1, further comprising an actuator operatively connected to the at least one movable canard wing for varying the angle of attack. 4. An aerial vehicle according to claim 1, wherein the at least one canard wing comprises four canard wings radially extending from the longitudinal axis of the fuselage. 5. An aerial vehicle according to claim 1, further comprising a central pod extending beyond the leading edge of the fuselage coaxially along the longitudinal axis and outer pods extending from the leading edge of the fuselage parallel with the longitudinal axis, and wherein the at least one canard wing comprises four canard wings radially extending with respect to the longitudinal axis from the central pod to the outer pods. 6. An aerial vehicle according to claim 5, wherein the outer pods contain fuel cells. 7. An aerial vehicle according to claim 6, wherein the fuel cells comprise batteries. 8. An aerial vehicle according to claim 5, wherein the outer pods contain actuators operatively connected to the movable canard wing for varying the angles of attack of the wings. 9. An aerial vehicle according to claim 5, wherein distal ends of the outer pods comprise landing gear. 10. An aerial vehicle according to claim 5, wherein the central pod contains an avionics bay. 11. An aerial vehicle according to claim 5, wherein the central pod contains a payload bay. 12. An aerial vehicle according to claim 5, wherein the central pod contains an actuator operatively connected to the rotor assemblies for varying the pitch of the rotor assemblies. 13. An aerial vehicle according to claim 1, wherein the fuselage includes an internal toroidal fuel bladder positioned against the leading edge of the fuselage. 14. An aerial vehicle according to claim 1, further comprising at least one engine mounted within the fuselage, and a drive train operatively connecting the engine to the first and the second rotor assemblies. 15. An aerial vehicle according to claim 14, wherein the drive train includes a gearbox located between the rotor assemblies, a rotatable drive shaft operatively connected between the engine and the gearbox, and the rotor assemblies include rotatable propeller hubs operatively connected between the gearbox and propeller blades of the rotor assemblies. 16. An aerial vehicle according to claim 15, wherein the drive shaft and the propeller hubs are operatively connected to the gearbox through bevel gears. 17. An aerial vehicle according to claim 16, wherein the bevel gears operatively connecting the gear box comprise straight bevel gears. 18. An aerial vehicle according to claim 15, wherein the drive shaft includes substantially parallel primary and secondary drive shafts connected by a connecting drive shaft, wherein the primary drive shaft extends between the engine and the connecting drive shaft and the secondary drive shaft extends between the connecting drive shaft and the gear box. 19. An aerial vehicle according to claim 18, wherein the drive shafts are operatively connected through bevel gears. 20. An aerial vehicle according to claim 19, wherein the bevel gears operatively connecting the drive shafts comprise straight bevel gears. 21. An aerial vehicle according to claim 19, wherei