An optimization approach to vibration reduction in helicopter rotors with multiple active trailing edge flaps

Viswamurthy, Sathyamangalam Ramanarayanan; Ganguli, Ranjan

doi:10.1016/j.ast.2003.10.003

Cited by 49 publications

(31 citation statements)

References 17 publications

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“…Comparing the above studies by Min et al (2009, and Bae and Gandhi (2012), to the ones conducted by Milgram et al (1998), and Viswamurthy and Ganguli (2004) it seems that a gurney flap can have a similar effect on the vibratory loads of the rotor hub like a conventional trailing edge flap. A typical flap is suggested by Viswamurthy and Ganguli (2004) on a soft hingeless rotor leading to a 72% reduction of the vibratory loads.…”

mentioning

confidence: 93%

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Computational aeroelastic analysis of a hovering W3 Sokol blade with gurney flap

Pastrikakis

Steijl

Barakos

et al. 2015

Journal of Fluids and Structures

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This paper demonstrates the potential effect of a gurney flap on the performance of the W3-Sokol rotor blade in hover. A rigid blade was first considered and the calculations were conducted at several thrust settings. The gurney flap was extended from 46%R to 66%R and it was located at the trailing edge of the main rotor blade. Four different sizes of gurney flaps were studied, 2%, 1%, 0.5% and 0.3% of the chord. The biggest flap proved to be the most effective. A second study considered elastic blades with and without the gurney flap. The results were trimmed at the same thrust values as the rigid blade and indicate an increase of aerodynamic performance when the gurney flap is used, especially for high thrust cases. Keywords

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mentioning

confidence: 93%

“…A typical flap is suggested by Viswamurthy and Ganguli (2004) on a soft hingeless rotor leading to a 72% reduction of the vibratory loads. However, the advantage of using a gurney flap compared to a trailing edge flap is on the amount of energy required for the actuation and the ease of the implementation of the gurney flap.…”

mentioning

confidence: 99%

Computational aeroelastic analysis of a hovering W3 Sokol blade with gurney flap

Pastrikakis

Steijl

Barakos

et al. 2015

Journal of Fluids and Structures

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“…The position of the flaps along the rotor has a great influence on the final performances of the mechanism. Although the optimum positioning of the flap depends on the application objective, studies show that multiple flaps achieve a better vibration reduction that a single flap [18,27,62]. These flaps only need a few degrees of deflection to affect the system dynamics [15,28].…”

Section: Active Trailing Edge Flapsmentioning

confidence: 99%

“…A schematic of a trailing edge flap for a helicopter blade taken from Koratkar [28] is shown in Figure 4. Although research has been conducted to study the possibility to use them for control in a swashplateless configuration [49], most of the studies focus on their ability to reduce the vibrations of helicopter blades [1,15,18,27,28,35,62]. The angle of the flap directly relates to a change of the bending of the blade during rotation Blade Flap Actuation mechanism Figure 4.…”

Section: Active Trailing Edge Flapsmentioning

confidence: 99%

Smart Actuation for Helicopter Rotorblades

Paternoster¹,

Loendersloot²,

Boer³

et al. 2012

Smart Actuation and Sensing Systems - Recent Advances and Future Challenges

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“…This is a work of the U.S. Government and is not subject to copyright protection in the U.S. the merits of employing two TEFs for rotor vibration control [8][9][10] . Kim et al have demonstrated blade loads reduction using two TEFs 11 and recently Gagliardi and Barakos have examined the use of two TEFs to improve hover performance 12 .…”

mentioning

confidence: 99%

Analysis of a Multiflap Control System for a Swashplateless Rotor

Sekula¹,

Wilbur²

2012

j am helicopter soc

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An analytical study was conducted examining the feasibility of a swashplateless rotor controlled through two trailing edge flaps (TEF), where the cyclic and collective controls were provided by separate TEFs. This analysis included a parametric study examining the impact of various design parameters on TEF deflections. Blade pitch bearing stiffness; blade pitch index; and flap chord, span, location, and control function of the inboard and outboard flaps were systematically varied on a utility-class rotorcraft trimmed in steady level flight. Gradient-based optimizations minimizing flap deflections were performed to identify single-and two-TEF swashplateless rotor designs. Steady, forward and turning flight analyses suggest that a two-TEF swashplateless rotor where the outboard flap provides cyclic control and inboard flap provides collective control can reduce TEF deflection requirements without a significant impact on power, compared to a single-TEF swashplateless rotor design.

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An optimization approach to vibration reduction in helicopter rotors with multiple active trailing edge flaps

Cited by 49 publications

References 17 publications

Computational aeroelastic analysis of a hovering W3 Sokol blade with gurney flap

Computational aeroelastic analysis of a hovering W3 Sokol blade with gurney flap

Smart Actuation for Helicopter Rotorblades

Analysis of a Multiflap Control System for a Swashplateless Rotor

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