A main rotor system of an aircraft is provided including a first rotor coupled to a transmission and configured to rotate about an axis in a first direction. A second rotor is similarly coupled to the transmission and is configured to rotate about the axis in a second direction. At least the first r
A main rotor system of an aircraft is provided including a first rotor coupled to a transmission and configured to rotate about an axis in a first direction. A second rotor is similarly coupled to the transmission and is configured to rotate about the axis in a second direction. At least the first rotor includes an individual blade control system (IBCS) configured to adjust a pitch of each of a plurality of blade of the first rotor independently. A standpipe is fixedly attached to the aircraft. The standpipe is arranged such that the first rotor and the second rotor rotate relative to the standpipe. At least one slip ring is configured to transmit electrical power and/or a control signal to the at least one IBCS.
대표청구항▼
1. A main rotor system of an aircraft comprising: a first rotor coupled to a transmission and configured to rotate about a first axis in a first direction;a second rotor coupled to the transmission, the second rotor being configured to rotate about the first axis in a second direction, wherein at le
1. A main rotor system of an aircraft comprising: a first rotor coupled to a transmission and configured to rotate about a first axis in a first direction;a second rotor coupled to the transmission, the second rotor being configured to rotate about the first axis in a second direction, wherein at least the first rotor includes an individual blade control system (IBCS) configured to adjust a pitch of each of a plurality of blades of the first rotor independently;a standpipe fixedly attached to the aircraft, the standpipe being arranged such that the first rotor and the second rotor rotate relative to the standpipe; andat least one slip ring configured to transmit at least one of electrical power or a control signal to the at least one IBCS. 2. The main rotor system according to claim 1, wherein a first slip ring is connected to the first rotor adjacent the transmission and a second slip ring is connected to the second rotor near the transmission. 3. The main rotor system according to claim 2, wherein the first rotor includes a first IBCS and the second rotor includes a second IBCS. 4. The main rotor system according to claim 3, wherein the first slip ring is configured to transmit at least one of electrical power or a first control signal to the first IBCS and the second slip ring is configured to transmit at least one of electrical power or a second control signal to the second IBCS. 5. The main rotor system according to claim 1, wherein the standpipe is arranged generally concentrically between the first rotor and the second rotor and the at least one slip is ring mounted to the standpipe. 6. The main rotor system according to claim 5, wherein the first rotor includes a first IBCS and the second rotor includes a second IBCS. 7. The main rotor system according to claim 1, wherein the at least one IBCS further comprises: a plurality of actuators, each of which is configured to rotate one of the plurality of rotor blades about a pitch axis, the pitch axis being arranged at an angle to the first axis; andat least one controller having a plurality of channels, each actuator being operably coupled to one of the plurality of channels such that the at least one controller is configured to operate the actuators in response to a control signal. 8. The main rotor system according to claim 7, wherein the at least one slip ring is configured to transmit at least one of electrical power or the control signal to the at least one controller via one or more wires. 9. The main rotor system according to claim 7, wherein the at least one slip ring is configured to transmit at least one of electrical power or the control signal to the at least one controller wirelessly. 10. The main rotor system according to claim 7, wherein the at least one controller of the IBCS is configured to receive the control signal optically. 11. A rotary wing aircraft comprising: an airframe having one or more engines mounted thereto;a main rotor system including: a first rotor including a first rotor hub and a plurality of first blades extending outwardly therefrom, the first rotor being coupled to a transmission and configured to rotate about an axis in a first direction;a second rotor including a second rotor hub and a plurality of second blades extending outwardly therefrom, the second rotor being coupled to the transmission and configured to rotate about the axis in a second direction, wherein the first rotor includes a first individual blade control system (IBCS) configured to adjust a pitch of each of the plurality of first blades independently and the second rotor includes a second IBCS configured to adjust the pitch of each of the plurality of second blades independently;a standpipe rotationally fixed relative to the airframe such that the first rotor and the second rotor rotate relative to the standpipe; andat least one slip ring configured to transmit at least one of electrical power or a control signal to the first IBCS and the second IBCS. 12. The rotary wing aircraft according to claim 11, wherein power from the engine is converted to electrical energy in a generator before being supplied to the at least one slip ring. 13. The rotary wing aircraft according to claim 12, further comprising an energy storage device configured to receive a portion of the electrical energy converted by the generator, wherein the energy storage device is configured to transmit power to at least one of the first IBCS and the second IBCS. 14. The rotary wing aircraft according to claim 11, wherein a first slip ring is connected to the first rotor adjacent the transmission and a second slip ring is connected to the second rotor near the transmission. 15. The rotary wing aircraft according to claim 12, wherein the first slip ring is configured to transmit at least one of electrical power or a first control signal to the first IBCS and the second slip ring is configured to transmit at least one of electrical power or a second control signal to the second IBCS. 16. The rotary wing aircraft according to claim 11, wherein each of the first IBCS and the second IBCS further comprises: a plurality of actuators, each of which is configured to rotate one of the plurality of rotor blades about a pitch axis, the pitch axis being arranged at an angle to the first axis; andat least one controller having a plurality of channels, each actuator being operably coupled to one of the plurality of channels such that the at least one controller is configured to operate the actuators in response to a control signal. 17. The rotary wing aircraft according to claim 11, further comprising a control system configured to generate the control signal, the control signal including waveform coefficients. 18. The rotary wing aircraft according to claim 17, wherein the waveform coefficients transmitted to the control system are determined using inceptor data and sensor data. 19. The rotary wing aircraft according to claim 17, wherein the waveform coefficients include a higher harmonic control signal. 20. The rotary wing aircraft according to claim 11, wherein the standpipe is arranged generally concentrically between the first rotor and the second rotor and the at least one slip is ring mounted to the standpipe. 21. The rotary wing aircraft according to claim 20, further comprising: a generator mounted to the first rotor, the generator including an engagement mechanism configured to engage a portion of the standpipe such that power is generated by the generator as the first rotor is rotated about the axis. 22. The rotary wing aircraft according to claim 21, further comprising another generator such that a generator is mounted to both the first rotor and the second rotor. 23. The rotary wing aircraft according to claim 22, wherein power generated by the one of the generators is configured to operate the first IBCS, and power generated by another of the generators is configured to operate the second IBCS.
Sun, Fanping; Chaudhry, Zaffir A.; Yeh, Jimmy Lih-Min; O'Callaghan, Michael G.; Jonsson, Ulf J.; Wake, Brian E.; Dold, Robert H., Hybrid actuator for helicopter rotor blade control flaps.
Petersen, Bruce L., Rotorcraft having coaxial counter-rotating rotors which produce both vertical and horizontal thrust and method of controlled flight in all six degrees of freedom.
Bigbee-Hansen, William J.; Clingman, Dan J.; Mabe, James H., Shape memory alloy-actuated propeller blades and shape memory alloy-actuated propeller assemblies.
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