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公开(公告)号：AU663194B2
公开(公告)日：1995-09-28
申请号：AU4102993
申请日：1993-04-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： YOERKIE CHARLES A , WELSH WILLIAM A , SHEEHY THOMAS W
IPC: B64C27/51 , B64C27/00 , F16F15/00 , F16F15/02 , G10K11/178
Abstract: An active noise control (ANC) system for a helicopter that is operative to effectively nullify one or more high frequency vibrations emanating from the main transmission gearbox thereof at the gearbox/airframe interface, thereby significantly reducing the interior noise levels of the helicopter, that is design optimized to minimize the number of actuators required, and that is design optimized to minimize contamination forces arising from operation of the system actuators. The ANC system includes modified transmission beams that are mechanically stiffened to function as rigid bodies with respect to the one or more of the high frequency vibrations, a plurality of actuators disposed in combination with the modified transmission beams, a plurality of sensors disposed in combination with the modified transmission beams in a collinear, spaced apart functional correlation with respective actuators, and controllers interconnecting individual actuators with respective functionally correlated sensors.
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公开(公告)号：AU673608B2
公开(公告)日：1996-11-14
申请号：AU6777894
申请日：1994-04-29
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FLEMMING ROBERT J JR , ROSEN KENNETH M , SHEEHY THOMAS W
Abstract: An unmanned aerial vehicle (UAV) having a toroidal fuselage and a rotor assembly including counter-rotating rotors coaxially mounted with respect to the toroidal fuselage incorporates ancillary aerodynamic structures aerodynamically configured and mounted in combination with the toroidal fuselage to provide a nose-down pitching moment to counteract the nose-up pitching moment generated by airflow over the toroidal fuselage during forward translational flight of the UAV. The ancillary aerodynamic structures have a cambered airfoil profile to provide high lifting forces. The ancillary aerodynamic structures may have centers of lift located significantly aft of the quarter-chord line of the airfoil, and are symmetrically mounted in combination with the lateral sides of the toroidal fuselage so that the centers of lift are located aftwardly of the fuselage axis of the toroidal fuselage in forward translational flight modes such that the ancillary aerodynamic structures generate a nose-down pitching moment to counteract the nose-up pitching moment due to airflow over the toroidal fuselage in forward translational flight. In a first embodiment, the ancillary aerodynamic structures are fixedly mounted in combination with the toroidal fuselage at a predetermined angle of incidence. In a second embodiment, the ancillary aerodynamic structures are rotatably mounted in combination with the toroidal fuselage to provide variable incidence ancillary aerodynamic structures for the UAV.
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公开(公告)号：CA2132198A1
公开(公告)日：1993-10-28
申请号：CA2132198
申请日：1993-04-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： WELSH WILLIAM A , YOERKIE CHARLES A , SHEEHY THOMAS W
Abstract: An active noise control (ANC) system for a helicopter that is operative to effectively nullify one or more high frequency vibrations emanating from the main transmission gearbox thereof at the gearbox/airframe interface, thereby significantly reducing the interior noise levels of the helicopter, that is design optimized to minimize the number of actuators required, and that is design optimized to minimize contamination forces arising from operation of the system actuators. The ANC system includes modified transmission beams that are mechanically stiffened to function as rigid bodies with respect to the one or more of the high frequency vibrations, a plurality of actuators disposed in combination with the modified transmission beams, a plurality of sensors disposed in combination with the modified transmission beams in a collinear, spaced apart functional correlation with respective actuators, and controllers interconnecting individual actuators with respective functionally correlated sensors.
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公开(公告)号：CA2010802A1
公开(公告)日：1990-10-18
申请号：CA2010802
申请日：1990-02-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SHEEHY THOMAS W , JENNEY DAVID S , MORDAUNT PHILLIP
Abstract: A helicopter (10) is roll vibration resistant having cantilever spring (40) supported masses (42) located at extreme outboard locations (30). The spring portion (40) extends substantially horizontally and is rigidly secured to rigid structure (28). This vibration absorber (34) is tuned to the forced frequency established by the normal rotor (14) RPM times the number of rotor blades (16).
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公开(公告)号：ES2095645T3
公开(公告)日：1997-02-16
申请号：ES93910595
申请日：1993-04-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： YOERKIE CHARLES A , WELSH WILLIAM A , SHEEHY THOMAS W
IPC: B64C27/51 , B64C27/00 , F16F15/00 , F16F15/02 , G10K11/178
Abstract: An active noise control (ANC) system for a helicopter that is operative to effectively nullify one or more high frequency vibrations emanating from the main transmission gearbox thereof at the gearbox/airframe interface, thereby significantly reducing the interior noise levels of the helicopter, that is design optimized to minimize the number of actuators required, and that is design optimized to minimize contamination forces arising from operation of the system actuators. The ANC system includes modified transmission beams that are mechanically stiffened to function as rigid bodies with respect to the one or more of the high frequency vibrations, a plurality of actuators disposed in combination with the modified transmission beams, a plurality of sensors disposed in combination with the modified transmission beams in a collinear, spaced apart functional correlation with respective actuators, and controllers interconnecting individual actuators with respective functionally correlated sensors.
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Patent Agency Ranking
公开(公告)号：DE69004730T2
公开(公告)日：1994-03-31
申请号：DE69004730
申请日：1990-04-05
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SHEEHY THOMAS W , JENNEY DAVID S , MORDAUNT PHILLIP
Abstract: A helicopter (10) is roll vibration resistant having cantilever spring (40) supported masses (42) located at extreme outboard locations. The spring portion (40) extends substantially horizontally and is rigidly secured to rigid structure (28). This vibration absorber (34) is tuned to the forced frequency established by the normal rotor (14) RPM times the number of rotor blades (16).
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公开(公告)号：AU6777894A
公开(公告)日：1994-12-12
申请号：AU6777894
申请日：1994-04-29
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FLEMMING ROBERT J JR , ROSEN KENNETH M , SHEEHY THOMAS W
Abstract: An unmanned aerial vehicle (UAV) having a toroidal fuselage and a rotor assembly including counter-rotating rotors coaxially mounted with respect to the toroidal fuselage incorporates ancillary aerodynamic structures aerodynamically configured and mounted in combination with the toroidal fuselage to provide a nose-down pitching moment to counteract the nose-up pitching moment generated by airflow over the toroidal fuselage during forward translational flight of the UAV. The ancillary aerodynamic structures have a cambered airfoil profile to provide high lifting forces. The ancillary aerodynamic structures may have centers of lift located significantly aft of the quarter-chord line of the airfoil, and are symmetrically mounted in combination with the lateral sides of the toroidal fuselage so that the centers of lift are located aftwardly of the fuselage axis of the toroidal fuselage in forward translational flight modes such that the ancillary aerodynamic structures generate a nose-down pitching moment to counteract the nose-up pitching moment due to airflow over the toroidal fuselage in forward translational flight. In a first embodiment, the ancillary aerodynamic structures are fixedly mounted in combination with the toroidal fuselage at a predetermined angle of incidence. In a second embodiment, the ancillary aerodynamic structures are rotatably mounted in combination with the toroidal fuselage to provide variable incidence ancillary aerodynamic structures for the UAV.
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公开(公告)号：CA2161113A1
公开(公告)日：1994-11-24
申请号：CA2161113
申请日：1994-04-29
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FLEMMING ROBERT J JR , ROSEN KENNETH M , SHEEHY THOMAS W
Abstract: An unmanned aerial vehicle (UAV) (100) having a toroidal fuselage (120) and a rotor assembly (170) including counter-rotating rotors coaxially mounted with respect to the toroidal fuselage incorporates ancillary aerodynamic structures (18) having a cambered airfoil profile to provide a nose-down pitching moment to counteract the nose-up pitching moment generated by airflow over the toroidal fuselage during forward translational flight of the UAV The ancillary aerodynamic structures are symmetrically mounted in combination with the lateral sides of the toroidal fuselage so that the centers of lift are located aftwardly of the fuselage axis of the toroidal fuselage in forward translational flight modes. In a first embodiment, the ancillary aerodynamic structures (18) are fixedly mounted in combination with the toroidal fuselage (10) at a predetermined angle of incidence. In a second embodiment, the ancillary aerodynamic structures (19) are rotatably mounted in combination with the toroidal fuselage (10') to provide variable incidence ancillary aerodynamic structures for the UAV.
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公开(公告)号：DE69004730D1
公开(公告)日：1994-01-05
申请号：DE69004730
申请日：1990-04-05
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SHEEHY THOMAS W , JENNEY DAVID S , MORDAUNT PHILLIP
Abstract: A helicopter (10) is roll vibration resistant having cantilever spring (40) supported masses (42) located at extreme outboard locations. The spring portion (40) extends substantially horizontally and is rigidly secured to rigid structure (28). This vibration absorber (34) is tuned to the forced frequency established by the normal rotor (14) RPM times the number of rotor blades (16).
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公开(公告)号：AU4102993A
公开(公告)日：1993-11-18
申请号：AU4102993
申请日：1993-04-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： YOERKIE CHARLES A , WELSH WILLIAM A , SHEEHY THOMAS W
IPC: B64C27/51 , B64C27/00 , F16F15/00 , F16F15/02 , G10K11/178
Abstract: An active noise control (ANC) system for a helicopter that is operative to effectively nullify one or more high frequency vibrations emanating from the main transmission gearbox thereof at the gearbox/airframe interface, thereby significantly reducing the interior noise levels of the helicopter, that is design optimized to minimize the number of actuators required, and that is design optimized to minimize contamination forces arising from operation of the system actuators. The ANC system includes modified transmission beams that are mechanically stiffened to function as rigid bodies with respect to the one or more of the high frequency vibrations, a plurality of actuators disposed in combination with the modified transmission beams, a plurality of sensors disposed in combination with the modified transmission beams in a collinear, spaced apart functional correlation with respective actuators, and controllers interconnecting individual actuators with respective functionally correlated sensors.
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