Actuator Saturation in Individual Blade Control of Rotorcraft

Padthe, Ashwani K.; Friedmann, Peretz P.; Bernstein, Dennis S.

doi:10.2514/6.2012-1477

Cited by 2 publications

(3 citation statements)

References 17 publications

(23 reference statements)

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“…A similar approach is also described in (Ref. 76) where it is compared to three other approaches for limiting saturation.…”

Section: Flap Phase (Deg) 3p Flap Moment Amplitude (Inch-lb)mentioning

confidence: 91%

“…A detailed study comparing four different approaches to constraining the maximum control surface deflection operated using a HHC control algorithm was conducted in Ref. 76. A constrained optimization-based approach, in which the saturation constraints are combined with the minimization of the HHC cost function, given in Eq.…”

Section: Implementation Of the Hhc Algorithm For Vibration And Noise mentioning

confidence: 99%

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On-Blade Control of Rotor Vibration, Noise, and Performance: Just Around the Corner? The 33rd Alexander Nikolsky Honorary Lecture

Friedmann¹

2014

j am helicopter soc

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A concise review of the active control approaches for vibration reduction in rotorcraft is presented. Next, the evolution and status of higher harmonic control and pitch link actuated individual blade control is presented since these serve as the foundations of on blade control. Despite the success of these approaches, demonstrated by both full-scale wind tunnel and flight tests, higher harmonic control and pitch link actuated individual blade control have not managed to earn their way onto a production helicopter. An alternative, on blade control, is defined as a special implementation of individual blade control, where the control surfaces are located on the rotating blade and each blade has its own controller. A concise description of four on blade devices: (1) the actively controlled flap, (2) the active twist rotor, (3) the active tip rotor, and the (4) deployable Gurney flap, or microflap, is presented. An outline of an aeroelastic response modeling capability used to simulate active vibration and noise reduction using flaps or microflaps is presented. The simulation is a thread that links the various parts of the paper. Next, selected results from simulations and scale wind tunnel model tests on active flaps are used to provide insight on the operational and modeling aspects of these systems. Full-scale wind tunnel and flight tests are presented as culmination of the research effort invested in active flap rotors. Then, the evolution and application of the active twist rotor, and deployable Gurney flaps, or microflaps, is presented. The paper concludes with lessons learned and speculation about the potential implementation of on blade control on production rotorcraft.

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“…A similar approach is also described in (Ref. 76) where it is compared to three other approaches for limiting saturation.…”

Section: Flap Phase (Deg) 3p Flap Moment Amplitude (Inch-lb)mentioning

confidence: 91%

Section: Implementation Of the Hhc Algorithm For Vibration And Noise mentioning

confidence: 99%

On-Blade Control of Rotor Vibration, Noise, and Performance: Just Around the Corner? The 33rd Alexander Nikolsky Honorary Lecture

Friedmann¹

2014

j am helicopter soc

View full text Add to dashboard Cite

show abstract

“…Comparison of the saturation approaches using various flap and microflap configurations at various flight conditions can be found in Ref. 49.…”

Section: Effect Of Actuator Saturationmentioning

confidence: 99%

Simultaneous Blade–Vortex Interaction Noise and Vibration Reduction in Rotorcraft Using Microflaps, Including the Effect of Actuator Saturation

Padthe¹,

Friedmann²

2015

j am helicopter soc

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The effectiveness of a sliding microflap to simultaneously reduce rotorcraft vibrations and noise was examined at a descending flight condition of advance ratio 0.15 with significant blade-vortex interactions (BVI). Two configurations, namely dual and a five-microflap configuration, were considered. Closed-loop control studies were conducted on a hingeless rotor configuration resembling MBB BO-105, using the adaptive higher harmonic control algorithm. The performance of the microflap was also compared to a conventional trailing-edge plain flap. The results demonstrate the effectiveness and control authority of the microflap for simultaneous BVI noise and vibration reduction in rotorcraft. Finally, a new saturation control algorithm is developed for limiting the microflap or flap deflections such that the best utilization of on-blade controllers implemented through multiple control surfaces is achieved. The performance of the new algorithm is compared to the existing ones on the dual and five-microflap configurations.

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Actuator Saturation in Individual Blade Control of Rotorcraft

Cited by 2 publications

References 17 publications

On-Blade Control of Rotor Vibration, Noise, and Performance: Just Around the Corner? The 33rd Alexander Nikolsky Honorary Lecture

On-Blade Control of Rotor Vibration, Noise, and Performance: Just Around the Corner? The 33rd Alexander Nikolsky Honorary Lecture

Simultaneous Blade–Vortex Interaction Noise and Vibration Reduction in Rotorcraft Using Microflaps, Including the Effect of Actuator Saturation

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