• Title/Summary/Keyword: minimum actuating force

Search Result 2, Processing Time 0.016 seconds

An analytical expression for a dynamic optimal design of the stewart platform (스튜어트 플랫폼의 동역학적 최적설계를 위한 해석적인 표현)

  • Kwon, Byung-Hee;Son, Kwon
    • 제어로봇시스템학회:학술대회논문집
    • /
    • 1997.10a
    • /
    • pp.175-178
    • /
    • 1997
  • This study was carried out to obtain an analytical expression for the specifications of the Stewart Platform that minimize the maximum force acting on the hydraulic cylinder. The position and orientation of the platform were calculated by means of the inverse kinematic analysis. The maximum force to be exerted on a cylinder was calculated using the Newton's second law for the case when the platform is moved along a horizontal axis with 0.6 g, the maximum translational acceleration possible. This paper suggests a mathematical model to minimize the maximum actuating force using radius and angle ratios as design variables. Finally, a fuzzy set for the minimum actuating force is proposed for this dynamic optimal design problem.

  • PDF

Rotor Hub Vibration Reduction Analysis Applying Individual Blade Control (개별 블레이드 조종을 통한 로터 허브 진동 저감 해석)

  • Kim, Taejoo;Wie, Seong-Yong;Kim, Minwoo;Lee, Dong-geon
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.49 no.8
    • /
    • pp.649-660
    • /
    • 2021
  • Through analytical method based on S-76 model, the level of rotor hub vibration reduction was analyzed according to higher harmonic actuating by individual blade control. The higher harmonic actuating method for individual blades was divided into a method of generating an additional actuating force from the pitch-link in the rotating part and generating actuating force through the active trailing edge flap control of the blade. In the 100kts forward flight conditions, the hub load analysis was performed by changing the phase angle of 15 degree for the 2P/3P/4P/5P harmonic actuation for individual blades. Through the harmonic actuation results, the sensitivity of the rotor system according to the actuating conditions was analyzed, and the T-matrix representing the characteristics of the rotor system was derived based on this analysis result. And through this T-matrix, optimal higher harmonic actuating condition was derived to minimize hub vibration level for flight condition. In addition, the effect on the performance of the rotor system and the pitch-link load under minimum hub vibration condition, as well as the noise influence through the noise analysis were confirmed.