Modeling of a Rotor System Incorporating Active Tab and Analysis of BVI Noise Reduction Characteristics

Kim, Do-Hyung; Kang, Hyun Jeong; Wie, Seong-Yong; Kim, Seung‐Ho

doi:10.5139/jksas.2013.41.11.855

Cited by 2 publications

(1 citation statement)

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“…Active trailing edge flap demonstrated its capability for vibration reduction in wind tunnels and flight tests [3][4][5][6], but it has not been approved as being airworthy. The active twist [7][8][9][10] and active tab [11][12][13] approaches have also demonstrated potential, but their technologies have not matured for flyable devices.…”

Section: Introductionmentioning

confidence: 99%

Test and Simulation of an Active Vibration Control System for Helicopter Applications

Kim¹,

Kim²,

Jung³

et al. 2016

International Journal of Aeronautical and Space Sciences

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A significant source of vibration in helicopters is the main rotor system, and it is a technical challenge to reduce the vibration in order to ensure the comfort of crew and passengers. Several types of passive devices have been applied to conventional helicopters in order to reduce the vibration. In recent years, helicopter manufacturers have increasingly adopted active vibration control systems (AVCSs) due to their superior performance with lower weight compared with passive devices. AVCSs can also maintain their performance over aircraft configuration and flight condition changes. As part of the development of AVCS software for light civil helicopter (LCH) applications, a test bench is constructed and vibration control tests and simulations are performed in this study. The test bench, which represents the airframe, is excited using a pair of counter rotating force generators (CRFGs) and a multiple input single output (MISO) AVCS that consists of three accelerometer sensors and a pair of CRFGs; a filtered-x least mean square (LMS) algorithm is applied for the vibration reduction. First, the vibration control tests are performed with uniform sensor weights; then, the change in the control performance according to changes in the sensor weight is investigated and compared with the simulation results. It is found that the vibration control performance can be tuned through adjusting the weights of the three sensors, even if only one actuator is used.

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Section: Introductionmentioning

confidence: 99%

Test and Simulation of an Active Vibration Control System for Helicopter Applications

Kim¹,

Kim²,

Jung³

et al. 2016

International Journal of Aeronautical and Space Sciences

Self Cite

View full text Add to dashboard Cite

show abstract

Application and Performance Evaluation of Helicopter Active Vibration Control System for Surion

Kim¹,

Kim²,

Paek³

et al. 2015

Journal of the Korean Society for Aeronautical & Space Scie

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The most decisive factor of major sources of a helicopter is the main rotor system and the rotor-induced vibration is one of the technical challenges which should be resolved to ensure comfort for crews and passengers. Passive vibration reduction devices are adopted in conventional helicopters and several types of passive devices are also used in Surion.In recent years, foreign helicopter manufactures have increasingly applied the application of AVCS (active vibration control system) because of their superior performance with lower weight compared to passive device. In addition to weight reduction, AVCS has advantages maintaining its performance over aircraft configuration changes and flight condition changes. The technology demonstration program was performed in order to validate the performance of AVCS when applied to Surion, and optimization process for finding optimal configuration of sensors and actuators. Optimal configuration was produced using ground and flight test data, and its performance was evaluated and compared with flight test result.

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Modeling of a Rotor System Incorporating Active Tab and Analysis of BVI Noise Reduction Characteristics

Abstract: ABSTRACT

Cited by 2 publications

References 1 publication

Test and Simulation of an Active Vibration Control System for Helicopter Applications

Test and Simulation of an Active Vibration Control System for Helicopter Applications

Application and Performance Evaluation of Helicopter Active Vibration Control System for Surion

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