초록 ▼

A vertical takeoff and landing (VTOL) aircraft design particularly suitable as a full-sized aircraft or remote controlled (RC) model aircraft is disclosed. The invention employs lightweight, high strength materials to reduce the power requirements of the propulsion plant. A preferred system of the i

A vertical takeoff and landing (VTOL) aircraft design particularly suitable as a full-sized aircraft or remote controlled (RC) model aircraft is disclosed. The invention employs lightweight, high strength materials to reduce the power requirements of the propulsion plant. A preferred system of the invention comprises one internal combustion engine able to spit shaft power to four fan units. The fan units further employ counter rotating fan blades for stability. Separate horizontal and vertical tilting mechanisms delivered to the fan units are additionally disclosed. A variation in design is further included wherein electric motors provide the necessary shaft power.

대표청구항 ▼

What is claimed is: 1. A vertical takeoff and landing (VTOL) aircraft, comprising: an elongated fuselage having forward and after sections and defining a longitudinal axis, the forward and after sections each having left and right quarter sections; a first forward structure beam extending outward f

What is claimed is: 1. A vertical takeoff and landing (VTOL) aircraft, comprising: an elongated fuselage having forward and after sections and defining a longitudinal axis, the forward and after sections each having left and right quarter sections; a first forward structure beam extending outward from the fuselage perpendicular to the longitudinal axis at the forward right quarter section; a second forward structure beam extending outward from the fuselage perpendicular to the longitudinal axis at the forward left quarter section; a first after structure beam extending outward from the fuselage perpendicular to the longitudinal axis at the after right quarter section; a second after structure beam extending outward from the fuselage perpendicular to the longitudinal axis at the after left quarter section; a first forward propulsion unit structurally connected to the first forward structure beam; a second forward propulsion unit structurally connected to the second forward structure beam; a first after propulsion unit structurally connected to the first forward structure beam; and a second after propulsion unit structurally connected to the second after structure beam, wherein each of the propulsion units is rotatable vertically about a horizontal axis relative to the fuselage, and wherein each of the propulsion units is shaft driven and wherein the first and second, forward and after structure beams each comprise a horizontal shaft, and wherein each of the after propulsion units comprise a rudder attached to a rear end of each of the after propulsion units, the rudder providing directional control of the aircraft, the aircraft further comprising: a hydraulic cylinder providing power to actuate the rudder; a hydraulic cylinder fairing encasing the hydraulic cylinder; a hydraulic fluid line contained within each of the after structure beams providing fluid pressure to the hydraulic cylinder; and a rudder anchor rod connecting the hydraulic cylinder to the rudder. 2. The vertical takeoff and landing aircraft (VTOL) of claim 1, wherein the aircraft comprises a control system, the control system comprising a torque split control switch for splitting torque between first and second, forward and after propulsion units. 3. The vertical takeoff and landing aircraft (VTOL) of claim 2, wherein split torque control is provided between forward and after propulsion units for balance during takeoff. 4. The vertical takeoff and landing (VTOL) aircraft of claim 1 further comprising: a first forward propulsion unit planetary gear assembly for transferring power from the first forward horizontal shaft to the first forward propulsion unit; a second forward propulsion unit planetary gear assembly for transferring power from the second forward horizontal shaft to the second forward propulsion unit; a first after propulsion unit planetary gear assembly for transferring power from the first after horizontal shaft to the first after propulsion unit; and a second after propulsion unit planetary gear assembly for transferring power from the second after horizontal shaft to the second after propulsion unit. 5. The vertical takeoff and landing (VTOL) aircraft of claim 1, each of the propulsion units comprising: a forward fan unit having one or more fan blades; and a counter rotating rearward fan unit having one or more fan blades to assist in stabilizing the aircraft. 6. The vertical takeoff and landing (VTOL) aircraft of claim 1, wherein each of the propulsion units are encased by a shroud, each of the shrouds comprised of clear polymer material. 7. A vertical takeoff and landing (VTOL) aircraft, comprising: an elongated fuselage having forward and after sections and defining a longitudinal axis, the forward and after sections each having left and right quarter sections; a first forward structure beam extending outward from the fuselage perpendicular to the longitudinal axis at the forward right quarter section; a second forward structure beam extending outward from the fuselage perpendicular to the longitudinal axis at the forward left quarter section; a first after structure beam extending outward from the fuselage perpendicular to the longitudinal axis at the after right quarter section; a second after structure beam extending outward from the fuselage perpendicular to the longitudinal axis at the after left quarter section; a first forward propulsion unit structurally connected to the first forward structure beam; a second forward propulsion unit structurally connected to the second forward structure beam; a first after propulsion unit structurally connected to the first forward structure beam; and a second after propulsion unit structurally connected to the second after structure beam, wherein each of the propulsion units is rotatable vertically about a horizontal axis relative to the fuselage, and wherein each of the propulsion units is shaft driven and wherein the first and second, forward and after structure beams each comprise a horizontal shaft, the aircraft further comprising: a main shaft substantially parallel to the longitudinal axis; and a forward torque transfer case that transfers shaft power from the main shaft to the first and second forward horizontal shafts, wherein the forward torque transfer case comprises a forward planetary gear assembly, the aircraft further comprising a plurality of U-joint linkages for connecting the after planetary gear assembly to the first and second after horizontal shafts, wherein each of the after propulsion units comprise a rudder attached to a rear end of each of the after propulsion units, the rudder providing directional control of the aircraft. 8. A vertical takeoff and landing aircraft (VTOL), comprising: an elongated fuselage having forward and after sections and defining a longitudinal axis, the forward and after sections each having left and right quarter sections; a first forward structure beam extending outward from the fuselage perpendicular to the longitudinal axis at the forward right quarter section; a second forward structure beam extending outward from the fuselage perpendicular to the longitudinal axis at the forward left quarter section; a first after structure beam extending outward from the fuselage perpendicular to the longitudinal axis at the after right quarter section; a second after structure beam extending outward from the fuselage perpendicular to the longitudinal axis at the after left quarter section; a first forward propulsion unit structurally connected to the first forward structure beam; a second forward propulsion unit structurally connected to the second forward structure beam; a first after propulsion unit structurally connected to the first forward structure beam; and a second after propulsion unit structurally connected to the second after structure beam; wherein each of the propulsion units is rotatable vertically about a horizontal axis relative to the fuselage, and wherein each of the propulsion units is shaft driven and wherein the first and second, forward and after structure beams each comprise a horizontal shaft, wherein the aircraft further comprises a control system, the control system comprising a torque split control switch for splitting torque between first and second, forward and after propulsion units, wherein the torque split control switch comprises: a neutral position wherein a total torque is proportioned 25% between each of first and second, forward and after propulsion units; a 12 o'clock position wherein the total torque is proportioned 70% between the forward propulsion units, and 30% between the after propulsion units; a 6 o'clock position wherein the total torque is proportioned 30% between the forward propulsion units, and 70% between the after propulsion units; a 3 o'clock position wherein the total torque is proportioned 70% between the first propulsion units, and 30% between the second propulsion units; and a 9 o'clock position wherein the total torque is proportioned 30% between the first propulsion units, and 70% between the second propulsion units. 9. A vertical takeoff and landing (VTOL) aircraft, comprising: an elongated fuselage having forward and after sections and defining a longitudinal axis, the forward and after sections each having left and right quarter sections; a first forward structure beam extending outward from the fuselage perpendicular to the longitudinal axis at the forward right quarter section; a second forward structure beam extending outward from the fuselage perpendicular to the longitudinal axis at the forward left quarter section; a first after structure beam extending outward from the fuselage perpendicular to the longitudinal axis at the after right quarter section; a second after structure beam extending outward from the fuselage perpendicular to the longitudinal axis at the after left quarter section; a first forward propulsion unit structurally connected to the first forward structure beam; a second forward propulsion unit structurally connected to the second forward structure beam; a first after propulsion unit structurally connected to the first forward structure beam; and a second after propulsion unit structurally connected to the second after structure beam; wherein each of the propulsion units is rotatable vertically about a horizontal axis relative to the fuselage, and wherein each of the propulsion units is shaft driven and wherein the first and second, forward and after structure beams each comprise a horizontal shaft, the aircraft further comprising a tilting mechanism for each of the propulsion units, each of the tilting mechanisms comprising: an annular gear having teeth around an annulus; and an electric motor having teeth to engage the annular gear; wherein each of electric motors is connected to each of the first and second, forward and after structure beams, wherein actuating the electric motor causes the electric motor to rotate about the annular gear, wherein the structure beam rotates to provide vertical rotation of each of the propulsion units. 10. The vertical takeoff and landing (VTOL) aircraft of claim 9, wherein the first and second, forward and after structure beams define a horizontal plane and wherein each of the propulsion units comprises a horizontal tilting mechanism to allow for horizontal rotation of the propulsion unit. 11. The vertical takeoff and landing aircraft (VTOL) of claim 9, further comprising a hinged air brake connected approximately at a mid-section of a side of the fuselage, the hinged air brake having deployed and stowed positions, wherein the deployed positions are backwardly inclined. 12. The vertical takeoff and landing aircraft (VTOL) of claim 9, further comprising a hinged air brake connected underneath the fuselage, the hinged air brake having deployed and stowed positions, wherein the deployed positions are backwardly inclined. 13. The vertical takeoff and landing aircraft (VTOL) of claim 9, further comprising left and right wing control surfaces extending outwardly from the fuselage, the left and right wing sections generally in the shape of an airfoil and tiltable. 14. A remote controlled (RC) aircraft, comprising: an elongated fuselage portion defining a longitudinal axis; left and right wing sections extending outwardly from the fuselage, the left and right wing sections generally having a shape of an airfoil; a plurality of propulsion units connected to the left and right wing sections wherein the plurality of propulsion units are configured to receive power from a single internal combustion engine; a plurality of planetary gear assemblies wherein the single internal combustion engine provides shaft power to a main shaft and wherein the plurality of planetary gears split the shaft power to the plurality of propulsion units, and a tilting mechanism for each of the propulsion units, each of the tilting mechanisms comprising: an annular gear having teeth around an annulus; and an electric motor having teeth to engage the annular gear; wherein each of electric motors is connected to each of the first and second, forward and after structure beams, wherein actuating the electric motor causes the electric motor to rotate about the annular gear, wherein the structure beam rotates to provide vertical rotation of each of the propulsion units. 15. The remote controlled (RC) aircraft of claim 14, further comprising a plurality of secondary shafts coupled to the main shaft, the secondary shafts being contained within the left and right wing sections.