Rotor Technology

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Terrence S. Birchette - One of the best experts on this subject based on the ideXlab platform.

  • Wind Tunnel Test of the SMART Active Flap Rotor
    Journal of the American Helicopter Society, 2018
    Co-Authors: Friedrich K Straub, Vaidyanathan R. Anand, Benton H. Lau, Terrence S. Birchette
    Abstract:

    Boeing and a team from NASA, the U. S. Army, DARPA, the U. S. Air Force, MIT, UCLA, and the University of Maryland have successfully completed a wind tunnel test of the Smart Material Actuated Rotor Technology (SMART) active flap Rotor in the 40- × 80-Foot Wind Tunnel of the National Full-Scale Aerodynamics Complex at NASA Ames Research Center. The Boeing SMART active flap Rotor is a full-scale, five-bladed bearingless MD900 helicopter Rotor modified with a piezoelectricactuated trailing-edge flap on each blade. The 11-week test program evaluated the forward flight characteristics of the active flap Rotor at speeds up to 155 kt, gathered data to validate state-of-the-art codes for Rotor aeroacoustic analysis, and quantified the effects of open- and closed-loop active flap control on Rotor loads, noise, and performance. The test demonstrated onblade smart material control of flaps on a full-scale Rotor for the first time in a wind tunnel. The effectiveness of the active flap control on noise and vibration was conclusively demonstrated. Results showed reductions up to 6 dB in blade–vortex interaction and in-plane noise, as well as reductions in vibratory hub loads of about 80%. Trailing-edge flap deflections were controlled with less than 0.2 deg rms error for commanded harmonic profiles of up to 3 deg amplitude. The impact of the active flap on control power, Rotor smoothing, and performance was also demonstrated. Finally, the reliability of the flap actuation system was successfully proven in more than 60 h of wind tunnel testing.

  • SMART Rotor Development and Wind Tunnel Test
    2009
    Co-Authors: Friedrich K Straub, Vaidyanathan R. Anand, Terrence S. Birchette
    Abstract:

    Boeing and a team from Air Force, NASA, Army, Massachusetts Institute of Technology, University of California at Los Angeles, and University of Maryland have successfully completed a wind-tunnel test of the smart material actuated Rotor Technology (SMART) Rotor in the 40- by 80-foot wind-tunnel of the National Full-Scale Aerodynamic Complex at NASA Ames Research Center, figure 1. The SMART Rotor is a full-scale, five-bladed bearingless MD 900 helicopter Rotor modified with a piezoelectric-actuated trailing-edge flap on each blade. The development effort included design, fabrication, and component testing of the Rotor blades, the trailing-edge flaps, the piezoelectric actuators, the switching power amplifiers, the actuator control system, and the data/power system. Development of the smart Rotor culminated in a whirl-tower hover test which demonstrated the functionality, robustness, and required authority of the active flap system. The eleven-week wind tunnel test program evaluated the forward flight characteristics of the active-flap Rotor, gathered data to validate state-of-the-art codes for Rotor noise analysis, and quantified the effects of open- and closed-loop active-flap control on Rotor loads, noise, and performance. The test demonstrated on-blade smart material control of flaps on a full-scale Rotor for the first time in a wind tunnel. The effectiveness and the reliability of the flap actuation system were successfully demonstrated in more than 60 hours of wind-tunnel testing. The data acquired and lessons learned will be instrumental in maturing this Technology and transitioning it into production. The development effort, test hardware, wind-tunnel test program, and test results will be presented in the full paper.

  • SMART Rotor Development and Wind Tunnel Test
    Proceedings of the 35th European Rotorcraft Forum, 2009
    Co-Authors: Friedrich K Straub, Benton H. Lau, Terrence S. Birchette, Moffett Field
    Abstract:

    Boeing and a team from NASA, Army, DARPA, Air Force, MIT, UCLA, and U. of Maryland have successfully completed a wind tunnel test of the smart material actuated Rotor Technology (SMART) active flap Rotor in the 40- by 80-foot wind-tunnel of the National Full-Scale Aerodynamic Complex at NASA Ames Research Center. The Boeing SMART active flap Rotor is a full-scale, five-bladed bearingless MD 900 helicopter Rotor modified with a piezoelectric-actuated trailing edge flap on each blade. The eleven-week test program evaluated the forward flight characteristics of the active-flap Rotor at speeds up to 155 knots, gathered data to validate state-of-the-art codes for Rotor aero- acoustic analysis, and quantified the effects of open and closed-loop active flap control on Rotor loads, noise, and performance. The test demonstrated on-blade smart material control of flaps on a full- scale Rotor for the first time in a wind tunnel. The effectiveness of the active flap control on noise and vibration was conclusively demonstrated. Results showed reductions up to 6dB in blade-vortex- interaction and in-plane noise, as well as reductions in vibratory hub loads of about 80%. Trailing- edge flap deflections were controlled with less than 0.2 deg rms error for commanded harmonic profiles of up to 3 deg amplitude. The impact of the active flap on control power, Rotor smoothing, and performance was also demonstrated. Finally, the reliability of the flap actuation system was successfully proven in more than 60 hours of wind tunnel testing

  • smart material actuated Rotor Technology smart
    Journal of Intelligent Material Systems and Structures, 2004
    Co-Authors: Friedrich K Straub, David B. Domzalski, Dennis K. Kennedy, Ahmed A. Hassan, V. Anand, Terrence S. Birchette
    Abstract:

    Vibration, noise, and aerodynamic design compromises are primary barriers to further improvements in effectiveness of the helicopter. The MD900 light utility helicopter main Rotor system is modified to include in-blade smart material actuation for active control. A piezoelectric (PE)-driven trailing edge flap is used for vibration, noise, and aerodynamic performance improvements. A shape memory alloy (SMA)-driven trailing edge trim tab is used for in-flight blade tracking.Sizing and conceptual design of an active flap and trim tab system for the MD900 helicopter were completed. Several two-dimensional airfoil and flap/tab models were wind tunnel tested and an aerodynamic database was established. Structural samples of the flap actuator mounts, flap section, tab, and full-span flap were fabricated and successfully tested. Several prototype actuators were developed and extensively tested to establish their performance and robustness in the dynamic operating environment. The flap actuator uses two biaxial PE...

  • Smart Material-Actuated Rotor Technology – SMART
    Journal of Intelligent Material Systems and Structures, 2004
    Co-Authors: Friedrich K Straub, David B. Domzalski, Dennis K. Kennedy, Ahmed A. Hassan, V. Anand, Terrence S. Birchette
    Abstract:

    Vibration, noise, and aerodynamic design compromises are primary barriers to further improvements in effectiveness of the helicopter. The MD900 light utility helicopter main Rotor system is modified to include in-blade smart material actuation for active control. A piezoelectric (PE)-driven trailing edge flap is used for vibration, noise, and aerodynamic performance improvements. A shape memory alloy (SMA)-driven trailing edge trim tab is used for in-flight blade tracking.Sizing and conceptual design of an active flap and trim tab system for the MD900 helicopter were completed. Several two-dimensional airfoil and flap/tab models were wind tunnel tested and an aerodynamic database was established. Structural samples of the flap actuator mounts, flap section, tab, and full-span flap were fabricated and successfully tested. Several prototype actuators were developed and extensively tested to establish their performance and robustness in the dynamic operating environment. The flap actuator uses two biaxial PE...

Friedrich K Straub - One of the best experts on this subject based on the ideXlab platform.

  • Wind Tunnel Test of the SMART Active Flap Rotor
    Journal of the American Helicopter Society, 2018
    Co-Authors: Friedrich K Straub, Vaidyanathan R. Anand, Benton H. Lau, Terrence S. Birchette
    Abstract:

    Boeing and a team from NASA, the U. S. Army, DARPA, the U. S. Air Force, MIT, UCLA, and the University of Maryland have successfully completed a wind tunnel test of the Smart Material Actuated Rotor Technology (SMART) active flap Rotor in the 40- × 80-Foot Wind Tunnel of the National Full-Scale Aerodynamics Complex at NASA Ames Research Center. The Boeing SMART active flap Rotor is a full-scale, five-bladed bearingless MD900 helicopter Rotor modified with a piezoelectricactuated trailing-edge flap on each blade. The 11-week test program evaluated the forward flight characteristics of the active flap Rotor at speeds up to 155 kt, gathered data to validate state-of-the-art codes for Rotor aeroacoustic analysis, and quantified the effects of open- and closed-loop active flap control on Rotor loads, noise, and performance. The test demonstrated onblade smart material control of flaps on a full-scale Rotor for the first time in a wind tunnel. The effectiveness of the active flap control on noise and vibration was conclusively demonstrated. Results showed reductions up to 6 dB in blade–vortex interaction and in-plane noise, as well as reductions in vibratory hub loads of about 80%. Trailing-edge flap deflections were controlled with less than 0.2 deg rms error for commanded harmonic profiles of up to 3 deg amplitude. The impact of the active flap on control power, Rotor smoothing, and performance was also demonstrated. Finally, the reliability of the flap actuation system was successfully proven in more than 60 h of wind tunnel testing.

  • SMART Rotor Development and Wind Tunnel Test
    2009
    Co-Authors: Friedrich K Straub, Vaidyanathan R. Anand, Terrence S. Birchette
    Abstract:

    Boeing and a team from Air Force, NASA, Army, Massachusetts Institute of Technology, University of California at Los Angeles, and University of Maryland have successfully completed a wind-tunnel test of the smart material actuated Rotor Technology (SMART) Rotor in the 40- by 80-foot wind-tunnel of the National Full-Scale Aerodynamic Complex at NASA Ames Research Center, figure 1. The SMART Rotor is a full-scale, five-bladed bearingless MD 900 helicopter Rotor modified with a piezoelectric-actuated trailing-edge flap on each blade. The development effort included design, fabrication, and component testing of the Rotor blades, the trailing-edge flaps, the piezoelectric actuators, the switching power amplifiers, the actuator control system, and the data/power system. Development of the smart Rotor culminated in a whirl-tower hover test which demonstrated the functionality, robustness, and required authority of the active flap system. The eleven-week wind tunnel test program evaluated the forward flight characteristics of the active-flap Rotor, gathered data to validate state-of-the-art codes for Rotor noise analysis, and quantified the effects of open- and closed-loop active-flap control on Rotor loads, noise, and performance. The test demonstrated on-blade smart material control of flaps on a full-scale Rotor for the first time in a wind tunnel. The effectiveness and the reliability of the flap actuation system were successfully demonstrated in more than 60 hours of wind-tunnel testing. The data acquired and lessons learned will be instrumental in maturing this Technology and transitioning it into production. The development effort, test hardware, wind-tunnel test program, and test results will be presented in the full paper.

  • SMART Rotor Development and Wind Tunnel Test
    Proceedings of the 35th European Rotorcraft Forum, 2009
    Co-Authors: Friedrich K Straub, Benton H. Lau, Terrence S. Birchette, Moffett Field
    Abstract:

    Boeing and a team from NASA, Army, DARPA, Air Force, MIT, UCLA, and U. of Maryland have successfully completed a wind tunnel test of the smart material actuated Rotor Technology (SMART) active flap Rotor in the 40- by 80-foot wind-tunnel of the National Full-Scale Aerodynamic Complex at NASA Ames Research Center. The Boeing SMART active flap Rotor is a full-scale, five-bladed bearingless MD 900 helicopter Rotor modified with a piezoelectric-actuated trailing edge flap on each blade. The eleven-week test program evaluated the forward flight characteristics of the active-flap Rotor at speeds up to 155 knots, gathered data to validate state-of-the-art codes for Rotor aero- acoustic analysis, and quantified the effects of open and closed-loop active flap control on Rotor loads, noise, and performance. The test demonstrated on-blade smart material control of flaps on a full- scale Rotor for the first time in a wind tunnel. The effectiveness of the active flap control on noise and vibration was conclusively demonstrated. Results showed reductions up to 6dB in blade-vortex- interaction and in-plane noise, as well as reductions in vibratory hub loads of about 80%. Trailing- edge flap deflections were controlled with less than 0.2 deg rms error for commanded harmonic profiles of up to 3 deg amplitude. The impact of the active flap on control power, Rotor smoothing, and performance was also demonstrated. Finally, the reliability of the flap actuation system was successfully proven in more than 60 hours of wind tunnel testing

  • smart material actuated Rotor Technology smart
    Journal of Intelligent Material Systems and Structures, 2004
    Co-Authors: Friedrich K Straub, David B. Domzalski, Dennis K. Kennedy, Ahmed A. Hassan, V. Anand, Terrence S. Birchette
    Abstract:

    Vibration, noise, and aerodynamic design compromises are primary barriers to further improvements in effectiveness of the helicopter. The MD900 light utility helicopter main Rotor system is modified to include in-blade smart material actuation for active control. A piezoelectric (PE)-driven trailing edge flap is used for vibration, noise, and aerodynamic performance improvements. A shape memory alloy (SMA)-driven trailing edge trim tab is used for in-flight blade tracking.Sizing and conceptual design of an active flap and trim tab system for the MD900 helicopter were completed. Several two-dimensional airfoil and flap/tab models were wind tunnel tested and an aerodynamic database was established. Structural samples of the flap actuator mounts, flap section, tab, and full-span flap were fabricated and successfully tested. Several prototype actuators were developed and extensively tested to establish their performance and robustness in the dynamic operating environment. The flap actuator uses two biaxial PE...

  • Smart Material-Actuated Rotor Technology – SMART
    Journal of Intelligent Material Systems and Structures, 2004
    Co-Authors: Friedrich K Straub, David B. Domzalski, Dennis K. Kennedy, Ahmed A. Hassan, V. Anand, Terrence S. Birchette
    Abstract:

    Vibration, noise, and aerodynamic design compromises are primary barriers to further improvements in effectiveness of the helicopter. The MD900 light utility helicopter main Rotor system is modified to include in-blade smart material actuation for active control. A piezoelectric (PE)-driven trailing edge flap is used for vibration, noise, and aerodynamic performance improvements. A shape memory alloy (SMA)-driven trailing edge trim tab is used for in-flight blade tracking.Sizing and conceptual design of an active flap and trim tab system for the MD900 helicopter were completed. Several two-dimensional airfoil and flap/tab models were wind tunnel tested and an aerodynamic database was established. Structural samples of the flap actuator mounts, flap section, tab, and full-span flap were fabricated and successfully tested. Several prototype actuators were developed and extensively tested to establish their performance and robustness in the dynamic operating environment. The flap actuator uses two biaxial PE...

John B Niemczuk - One of the best experts on this subject based on the ideXlab platform.

  • blade vortex interaction noise reduction with active twist smart Rotor Technology
    Smart Materials and Structures, 2001
    Co-Authors: Peter C Chen, James D Baeder, Robert A D Evans, John B Niemczuk
    Abstract:

    The results of this analytical feasibility study suggest that active blade twist Technology is a viable means to reduce blade-vortex interaction (BVI) noise in Rotorcraft systems. A linearized unsteady aerodynamics analysis was formulated and successfully validated with computation fluid dynamics (CFD) analysis. A simple control scheme with three control points was found to be effective for active BVI noise reduction. Based on current-day actuation Technology where one to two degrees of twist per blade activation span is expected, measurable noise reductions of 2-4 dB were predicted for the relatively strong, close vortex interactions. For weaker vortex interactions, reductions of 7-10 dB were predicted. The required twist actuation per blade span for complete unsteady loading cancellation, however, may be infeasible because of the large stroke and high-frequency activation requirements.

  • Active twist smart Rotor Technology for blade-vortex interaction noise reduction
    Smart Structures and Materials 1999: Smart Structures and Integrated Systems, 1999
    Co-Authors: Peter C Chen, James D Baeder, Robert A D Evans, John B Niemczuk, Paul Ross
    Abstract:

    The results of this feasibility study suggest that active blade twist Technology is a viable means to reduce blade- vortex interaction (BVI) noise in Rotorcraft systems. A linearized unsteady aerodynamics analysis was formulated and successfully validated with computation fluid dynamics analysis. A simple control scheme with three control points was found to be effective for active BVI noise reduction. Based on current-day actuation Technology where 1 to 2 degrees of twist per blade activation span is expected, measurable noise reductions of 2 to 4 dB were predicted for the relatively strong, close vortex interactions. For weaker vortex interactions, reductions of 7 to 10 dB were predicted. The required twist actuation per blade span for complete unsteady loading cancellation, however, may be infeasible because of the large stroke and high frequency activation requirements.

Ahmed A. Hassan - One of the best experts on this subject based on the ideXlab platform.

  • smart material actuated Rotor Technology smart
    Journal of Intelligent Material Systems and Structures, 2004
    Co-Authors: Friedrich K Straub, David B. Domzalski, Dennis K. Kennedy, Ahmed A. Hassan, V. Anand, Terrence S. Birchette
    Abstract:

    Vibration, noise, and aerodynamic design compromises are primary barriers to further improvements in effectiveness of the helicopter. The MD900 light utility helicopter main Rotor system is modified to include in-blade smart material actuation for active control. A piezoelectric (PE)-driven trailing edge flap is used for vibration, noise, and aerodynamic performance improvements. A shape memory alloy (SMA)-driven trailing edge trim tab is used for in-flight blade tracking.Sizing and conceptual design of an active flap and trim tab system for the MD900 helicopter were completed. Several two-dimensional airfoil and flap/tab models were wind tunnel tested and an aerodynamic database was established. Structural samples of the flap actuator mounts, flap section, tab, and full-span flap were fabricated and successfully tested. Several prototype actuators were developed and extensively tested to establish their performance and robustness in the dynamic operating environment. The flap actuator uses two biaxial PE...

  • Smart Material-Actuated Rotor Technology – SMART
    Journal of Intelligent Material Systems and Structures, 2004
    Co-Authors: Friedrich K Straub, David B. Domzalski, Dennis K. Kennedy, Ahmed A. Hassan, V. Anand, Terrence S. Birchette
    Abstract:

    Vibration, noise, and aerodynamic design compromises are primary barriers to further improvements in effectiveness of the helicopter. The MD900 light utility helicopter main Rotor system is modified to include in-blade smart material actuation for active control. A piezoelectric (PE)-driven trailing edge flap is used for vibration, noise, and aerodynamic performance improvements. A shape memory alloy (SMA)-driven trailing edge trim tab is used for in-flight blade tracking.Sizing and conceptual design of an active flap and trim tab system for the MD900 helicopter were completed. Several two-dimensional airfoil and flap/tab models were wind tunnel tested and an aerodynamic database was established. Structural samples of the flap actuator mounts, flap section, tab, and full-span flap were fabricated and successfully tested. Several prototype actuators were developed and extensively tested to establish their performance and robustness in the dynamic operating environment. The flap actuator uses two biaxial PE...

  • Smart Material-Actuated Rotor Technology – SMART
    Journal of Intelligent Materials Systems and Structures, 2004
    Co-Authors: Friedrich K Straub, David B. Domzalski, Hieu Ngo, Dennis K. Kennedy, Ahmed A. Hassan, V. Anand, Terrence S. Birchette
    Abstract:

    Vibration, noise, and aerodynamic design compromises are primary barriers to further improvements in effectiveness of the helicopter. The MD900 light utility helicopter main Rotor system is modified to include in-blade smart material actuation for active control. A piezoelectric (PE)-driven trailing edge flap is used for vibration, noise, and aerodynamic performance improvements. A shape memory alloy (SMA)-driven trailing edge trim tab is used for in-flight blade tracking. Sizing and conceptual design of an active flap and trim tab system for the MD900 helicopter were completed. Several two-dimensional airfoil and flap/tab models were wind tunnel tested and an aerodynamic database was established. Structural samples of the flap actuator mounts, flap section, tab, and full-span flap were fabricated and successfully tested. Several prototype actuators were developed and extensively tested to establish their performance and robustness in the dynamic operating environment. The flap actuator uses two biaxial PE stack columns, operating in a push–pull mode, a column mid-support, and a stroke amplification mechanism. The tab actuator uses two biaxial SMA tubes for actuation/bias, an SMA-activated lock for power-off operation, and integrated microprocessor control electronics. Results to date confirm that smart material in-blade active control of a Rotor is feasible and offers significant performance and cost benefits. Projected payoffs from reduced vibrations and noise as well as in-flight tracking include improved component lives, reduced maintenance and improved crew, passenger, and community acceptance.

  • Smart material actuated Rotor Technology - SMART
    41st Structures Structural Dynamics and Materials Conference and Exhibit, 2000
    Co-Authors: Dennis Kennedy, Friedrich K Straub, David B. Domzalski, Hieu Ngo, Terrence S. Birchette, Dennis K. Kennedy, Hieu T Ngo, Ahmed A. Hassan, Ahmed Hassan, V. Anand
    Abstract:

    Vibration, noise, and aerodynamic design compromises are primary barriers to effectiveness of the helicopter. The MD900 light utility helicopter main Rotor system is modified to include in-blade smart material actuation for active control, A piezoelectric (PE) driven trailing edge flap is used for vibration, noise, and aerodynamic performance improvements. A shape memory alloy (SMA) driven trailing edge trim tab is used for in-flight blade tracking. Sizing and conceptual design of an active flap and trim tab system for the MD900 helicopter was completed. Several two-dimensional airfoil and flap/tab models were wind tunnel tested and an aerodynamic database was established. Structural samples of the flap actuator mounts, flap section, tab, and full span flap were fabricated and successfully tested. Several prototype actuators were developed and extensively tested to establish their performance and robustness in the dynamic operating environment. The flap actuator uses two biaxial PE stack columns, operating in a push-pull mode, a column mid-support, and a stroke amplification mechanism. The tab actuator uses two bi-axial SMA tubes for actuation/bias, an SMA activated lock for power off operation, and integrated microprocessor control electronics. Results to date confirm that smart material in-blade active control of a Rotor is feasible and offers significant performance and cost benefits. Projected payoffs from reduced vibrations and noise as well as inflight tracking include improved component lives, reduced maintenance and improved crew, passenger, and community acceptance. © 2000 by F.K. Straub.

Dennis K. Kennedy - One of the best experts on this subject based on the ideXlab platform.

  • smart material actuated Rotor Technology smart
    Journal of Intelligent Material Systems and Structures, 2004
    Co-Authors: Friedrich K Straub, David B. Domzalski, Dennis K. Kennedy, Ahmed A. Hassan, V. Anand, Terrence S. Birchette
    Abstract:

    Vibration, noise, and aerodynamic design compromises are primary barriers to further improvements in effectiveness of the helicopter. The MD900 light utility helicopter main Rotor system is modified to include in-blade smart material actuation for active control. A piezoelectric (PE)-driven trailing edge flap is used for vibration, noise, and aerodynamic performance improvements. A shape memory alloy (SMA)-driven trailing edge trim tab is used for in-flight blade tracking.Sizing and conceptual design of an active flap and trim tab system for the MD900 helicopter were completed. Several two-dimensional airfoil and flap/tab models were wind tunnel tested and an aerodynamic database was established. Structural samples of the flap actuator mounts, flap section, tab, and full-span flap were fabricated and successfully tested. Several prototype actuators were developed and extensively tested to establish their performance and robustness in the dynamic operating environment. The flap actuator uses two biaxial PE...

  • Smart Material-Actuated Rotor Technology – SMART
    Journal of Intelligent Material Systems and Structures, 2004
    Co-Authors: Friedrich K Straub, David B. Domzalski, Dennis K. Kennedy, Ahmed A. Hassan, V. Anand, Terrence S. Birchette
    Abstract:

    Vibration, noise, and aerodynamic design compromises are primary barriers to further improvements in effectiveness of the helicopter. The MD900 light utility helicopter main Rotor system is modified to include in-blade smart material actuation for active control. A piezoelectric (PE)-driven trailing edge flap is used for vibration, noise, and aerodynamic performance improvements. A shape memory alloy (SMA)-driven trailing edge trim tab is used for in-flight blade tracking.Sizing and conceptual design of an active flap and trim tab system for the MD900 helicopter were completed. Several two-dimensional airfoil and flap/tab models were wind tunnel tested and an aerodynamic database was established. Structural samples of the flap actuator mounts, flap section, tab, and full-span flap were fabricated and successfully tested. Several prototype actuators were developed and extensively tested to establish their performance and robustness in the dynamic operating environment. The flap actuator uses two biaxial PE...

  • Smart Material-Actuated Rotor Technology – SMART
    Journal of Intelligent Materials Systems and Structures, 2004
    Co-Authors: Friedrich K Straub, David B. Domzalski, Hieu Ngo, Dennis K. Kennedy, Ahmed A. Hassan, V. Anand, Terrence S. Birchette
    Abstract:

    Vibration, noise, and aerodynamic design compromises are primary barriers to further improvements in effectiveness of the helicopter. The MD900 light utility helicopter main Rotor system is modified to include in-blade smart material actuation for active control. A piezoelectric (PE)-driven trailing edge flap is used for vibration, noise, and aerodynamic performance improvements. A shape memory alloy (SMA)-driven trailing edge trim tab is used for in-flight blade tracking. Sizing and conceptual design of an active flap and trim tab system for the MD900 helicopter were completed. Several two-dimensional airfoil and flap/tab models were wind tunnel tested and an aerodynamic database was established. Structural samples of the flap actuator mounts, flap section, tab, and full-span flap were fabricated and successfully tested. Several prototype actuators were developed and extensively tested to establish their performance and robustness in the dynamic operating environment. The flap actuator uses two biaxial PE stack columns, operating in a push–pull mode, a column mid-support, and a stroke amplification mechanism. The tab actuator uses two biaxial SMA tubes for actuation/bias, an SMA-activated lock for power-off operation, and integrated microprocessor control electronics. Results to date confirm that smart material in-blade active control of a Rotor is feasible and offers significant performance and cost benefits. Projected payoffs from reduced vibrations and noise as well as in-flight tracking include improved component lives, reduced maintenance and improved crew, passenger, and community acceptance.

  • Smart material actuated Rotor Technology - SMART
    41st Structures Structural Dynamics and Materials Conference and Exhibit, 2000
    Co-Authors: Dennis Kennedy, Friedrich K Straub, David B. Domzalski, Hieu Ngo, Terrence S. Birchette, Dennis K. Kennedy, Hieu T Ngo, Ahmed A. Hassan, Ahmed Hassan, V. Anand
    Abstract:

    Vibration, noise, and aerodynamic design compromises are primary barriers to effectiveness of the helicopter. The MD900 light utility helicopter main Rotor system is modified to include in-blade smart material actuation for active control, A piezoelectric (PE) driven trailing edge flap is used for vibration, noise, and aerodynamic performance improvements. A shape memory alloy (SMA) driven trailing edge trim tab is used for in-flight blade tracking. Sizing and conceptual design of an active flap and trim tab system for the MD900 helicopter was completed. Several two-dimensional airfoil and flap/tab models were wind tunnel tested and an aerodynamic database was established. Structural samples of the flap actuator mounts, flap section, tab, and full span flap were fabricated and successfully tested. Several prototype actuators were developed and extensively tested to establish their performance and robustness in the dynamic operating environment. The flap actuator uses two biaxial PE stack columns, operating in a push-pull mode, a column mid-support, and a stroke amplification mechanism. The tab actuator uses two bi-axial SMA tubes for actuation/bias, an SMA activated lock for power off operation, and integrated microprocessor control electronics. Results to date confirm that smart material in-blade active control of a Rotor is feasible and offers significant performance and cost benefits. Projected payoffs from reduced vibrations and noise as well as inflight tracking include improved component lives, reduced maintenance and improved crew, passenger, and community acceptance. © 2000 by F.K. Straub.

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