IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0654323
(2007-01-16)
|
등록번호 |
US-8764397
(2014-07-01)
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발명자
/ 주소 |
|
출원인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
7 |
초록
▼
A rotor system is provided wherein coaxial, closely spaced multi-bladed rotors counter-rotate at extremely low RPMs while their pitches are controlled to account for wind gusts and velocity conditions, thereby eliminating many of the deficiencies of conventional helicopters. The embodiments can dram
A rotor system is provided wherein coaxial, closely spaced multi-bladed rotors counter-rotate at extremely low RPMs while their pitches are controlled to account for wind gusts and velocity conditions, thereby eliminating many of the deficiencies of conventional helicopters. The embodiments can dramatically decrease the power required to lift a given quantity of weight, even beyond the level required by a typical airplane.
대표청구항
▼
1. A rotor system comprising: a) A first hub for rotation about a first axis;b) a plurality of blade assemblies attached to said first hub, each of said blade assemblies comprising 1) a rotor blade; 2) an actuator for rotating the rotor blade; 3) a position sensor for measuring an angle of attack of
1. A rotor system comprising: a) A first hub for rotation about a first axis;b) a plurality of blade assemblies attached to said first hub, each of said blade assemblies comprising 1) a rotor blade; 2) an actuator for rotating the rotor blade; 3) a position sensor for measuring an angle of attack of the rotor blade; and 4) a sensor for measuring a lift force acting on the rotor blade; andc) a computer for collecting data of the angle of attack and the lift force and outputting a signal to the actuator based on the data. 2. The rotor system of claim 1, further comprising a second plurality of blade assemblies attached to a second hub for rotation about a second axis approximately coincident with the first axis. 3. The rotor system of claim 2, wherein said first and second hubs are connected via an electric motor. 4. The rotor system of claim 2, wherein the sensing is performed by at least one force sensor measuring a lift force on a second rotor blade on the first rotor. 5. The rotor system of claim 2, wherein the first rotor is rotating with a tip speed of less than 100 mph. 6. The rotor system of claim 2, wherein no substantial net torque is applied to the airframe by the first and second rotors. 7. The rotor system of claim 2, wherein the first rotor is rotated by blown air. 8. The rotor system of claim 7, wherein the blown air is generated by a propeller attached to the first rotor. 9. The rotor system of claim 8, wherein the propeller is driven by an electric motor. 10. The rotor system of claim 2, wherein the first and second rotors each have a plurality of rotor blades and the number of rotor blades of the first rotor differs from the number of rotor blades of the second rotor. 11. The method rotor system of claim 2, wherein an airfoil of the rotor blade operates with a Reynolds number of less than 1 million as the second rotor is rotated. 12. The rotor system of claim 1, further comprising at least one vane for directing airflow generated by the rotor system. 13. The rotor system of claim 1, further comprising a propeller for driving the first hub and the plurality of blade assemblies about the first axis. 14. A method of controlling a helicopter rotor system comprising the steps of: a) providing a first rotor having a first plurality of blades;b) providing a second rotor having a second plurality of blades and mounted approximately coaxial to the first rotor;c) driving said first and second rotors to turn in opposite directions;d) sensing a loss of lift on a first section of the first rotor; ande) increasing lift on a second section of the second rotor that overlaps with at least a portion of the first section of the first rotor. 15. The method of claim 14, wherein the first rotor has a tip speed while being driven, wherein the first rotor is driven such that the tip speed of the first rotor is less than 100 mph. 16. The method of claim 15, wherein the first rotor is driven such that the tip speed of the first rotor is less than 40 mph. 17. A method of compensating for a retreating blade stall on a pair of substantially coaxial, counter-rotating rotors having a plurality of blades comprising: a) Dividing the area swept by said counter-rotating rotors into a plurality of sectors;b) Determining the lift generated by each rotor of said counter-rotating rotors at each sector;c) Increasing the effective angle of attack of at least one of said blades on a first rotor of said pair of counter-rotating rotors due to a loss of lift on a second rotor of said pair of counter-rotating rotors. 18. A method of operating a helicopter having an airframe and first and second substantially coaxial rotors, comprising: a) rotating the first rotor clockwise;b) rotating the second rotor counterclockwise;c) sensing a loss of lift on a portion of the first rotor; andd) increasing the angle of attack of a rotor blade of the second rotor as it overlaps the portion of the first rotor where the loss of lift was sensed. 19. A directional control system for a helicopter comprising: a) an airframe;b) a rotor rotably connected to the airframe, the rotor having an approximately vertical axis of rotation, the rotor for generating an approximately vertical airflow, andc) a movable vane connected to the airframe, the movable vane having a surface extending in an approximately vertical direction, the movable vane for tilting from the approximately vertical direction so as to redirect the approximately vertical airflow generated by the rotor,wherein the movable vane is positioned on a first side of the airframe, the system further comprising a second movable vane connected to the airframe on a second side of the airframe approximately opposite the first side relative to the axis of rotation, the second movable vane having a second surface extending in an approximately vertical direction, the second movable vane for tilting from the approximately vertical direction so as to redirect the approximately vertical airflow generated by the rotor, whereby tilting the movable vane and the second movable vane in opposite directions redirects the approximately vertical airflow in opposite directions, providing yaw control of the airframe. 20. The system of claim 19, wherein the movable vane is rotable. 21. The system of claim 20, wherein the movable vane is rotable about a first axis and the second movable vane is rotable about a second axis and the first and second axes are parallel and substantially coincident. 22. A helicopter rotor system comprising: a) A first hub for rotation about a first axis;b) a first blade assembly attached to said first hub, the first blade assembly comprising 1) a first rotor blade for generating a first lift force; 2) a first actuator for adjusting the first lift force generated by the first rotor blade;c) a second blade assembly attached to said first hub, the second blade assembly comprising 1) a second rotor blade for generating a second lift force; 2) a second actuator for adjusting the second lift force generated by the second rotor blade;d) a computer for outputting a first signal to the first actuator to adjust the first lift force and a second signal to the second actuator to adjust the second lift force, ande) a sensor connected to the first rotor blade for measuring the first lift force generated by the first rotor blade. 23. The helicopter rotor system of claim 22, wherein the first actuator adjusts the first lift force generated by the first rotor blade by tilting the first rotor blade. 24. The helicopter rotor system of claim 22, further comprising: A second hub for rotation about the first axis;a third blade assembly attached to said second hub, the third blade assembly comprising 1) a third rotor blade for generating a third lift force; 2) a third actuator for adjusting the third lift force generated by the third rotor blade;a fourth blade assembly attached to said second hub, the fourth blade assembly comprising 1) a fourth rotor blade for generating a fourth lift force; 2) a fourth actuator for adjusting the fourth lift force generated by the fourth rotor blade, wherein the computer outputs a third signal to the third actuator to adjust the third lift force and a fourth signal to the fourth actuator to adjust the fourth lift force. 25. The system of claim 22, wherein the sensor is a force sensor. 26. A method comprising the steps of: a) Providing a first rotor;b) Providing a second rotor coaxial to the first rotor;c) Providing an airframe, the airframe connected to the first rotor and to the second rotor;d) Rotating the first rotor in a first direction;e) Rotating the second rotor in a second direction, the second direction being opposite the first direction;f) Sensing a decrease in lift force on a first portion of the first rotor; andg) Increasing lift force on a second portion of the second rotor to compensate for the decrease in lift force on the first portion of the first rotor.
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