International Journal of Aeronautical and Space Sciences

  • 제18권2호
  • /
  • Pages.175-185
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  • 2017
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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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Calculating Dynamic Derivatives of Flight Vehicle with New Engineering Strategies

  • Mi, Baigang (School of Aeronautics, Northwestern Polytechnical University) ;
  • Zhan, Hao (School of Aeronautics, Northwestern Polytechnical University) ;
  • Chen, Baibing (Xi'an Modern Control Technology Research Institute)
  • 투고 : 2016.04.18
  • 심사 : 2017.05.24
  • 발행 : 2017.06.30
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초록

This paper presents new differential methods for computing the combined and single dynamic stability derivatives of flight vehicle. Based on rigid dynamic mesh technique, the combined dynamic stability derivative can be achieved by imposing the aircraft pitching to the same angle of attack with two different pitching angular velocities and also translating it to the same additional angle of attack with two different rates of angle of attack. As a result, the acceleration derivative is identified. Moreover, the rotating reference frame is adopted to calculate the rotary derivatives when simulating the steady pull-up with different pitching angular velocities. Two configurations, the Hyper Ballistic Shape (HBS) and Finner missile model, are considered as evaluations and results of all the cases agree well with reference or experiment data. Compared to traditional ones, the new differential methods are of high efficiency and accuracy, and potential to be extended to the simulation of combined and single stability derivatives of directional and lateral.

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참고문헌

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피인용 문헌

  1. Numerical Simulation of Support Interference in Wind Tunnel for Dynamic Stability Parameters vol.07, pp.01, 2019, https://doi.org/10.12677/IJFD.2019.71005