International Journal of Aeronautical and Space Sciences

  • 제17권3호
  • /
  • Pages.442-453
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  • 2016
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  • 2093-274X(pISSN)
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  • 2093-2480(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
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Test and Simulation of an Active Vibration Control System for Helicopter Applications

  • Kim, Do-Hyung (Rotorcraft Research Team, Korea Aerospace Research Institute) ;
  • Kim, Tae-Joo (Rotorcraft Research Team, Korea Aerospace Research Institute) ;
  • Jung, Se-Un (Rotary-Wing Flight Performance Team, Korea Aerospace Industry) ;
  • Kwak, Dong-Il (Rotary-Wing Flight Performance Team, Korea Aerospace Industry)
  • 투고 : 2016.05.02
  • 심사 : 2016.08.19
  • 발행 : 2016.09.30
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초록

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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참고문헌

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피인용 문헌

  1. A Time-Domain Active Vibration Control Algorithm for Helicopter Based on a Prior Error Channel Identification Strategy vol.2018, 2018, https://doi.org/10.1155/2018/2870896
  2. Development of Hardware-in-the-Loop Simulation Based on Gazebo and Pixhawk for Unmanned Aerial Vehicles vol.19, pp.1, 2018, https://doi.org/10.1007/s42405-018-0012-8