한국항공우주학회지 (Journal of the Korean Society for Aeronautical & Space Sciences)

  • 제50권10호
  • /
  • Pages.709-716
  • /
  • 2022
  • /
  • 1225-1348(pISSN)
  • /
  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
권호 표지
DOI QR코드

DOI QR Code

위성발사체 상단의 고체로켓모터 유도를 위한 Gamma 유도 알고리듬 성능 분석

Performance Analysis of the Gamma Guidance Algorithm for Solid Rocket Kick Motors of Upper Stages of Space Launch Vehicles

  • 투고 : 2022.06.09
  • 심사 : 2022.08.10
  • 발행 : 2022.10.01
PDF 다운로드
⟨ 이전 논문 다음 논문 ⟩

초록

본 논문에서는 IUS (Inertial Upper Stage)에 사용된 Gamma 유도 방식을 상단이 고체모터로 구성된 위성발사체 유도를 위해 적용해 보았다. 알고리듬의 수렴성 및 고체모터의 속도 오차 보상을 위해 RCS(Reaction Control System)가 최상단 연소 종료 후 작동하는 것으로 두었다. 알고리듬 계산 과정 중 최종 궤도 투입 오차 예측을 위한 적분과정을 Keplerian 궤적으로 단순화함으로써 수치 적분과정이 없도록 알고리듬을 구성하였다. 유도 알고리듬 평가를 위해 비공칭 비행 조건에 대한 3-DOF 컴퓨터 시뮬레이션을 수행해 주어진 상단 유도 방식은 개루프 명령을 적용한 경우 대비 궤도 투입 오차를 줄일 수 있음을 보였다.

In this paper the Gamma guidance law, which was used for IUS (Inertial Upper Stage), is applied for solid-motor guidance of a upper stage of a satellite launch vehicle. The RCS (Reaction Control System), which activates after burnout of the upper stage, is employed for the convergence of the guidance algorithm and compensation of velocity errors induced by the solid motor. The algorithm is also simplified by replacing the time-consuming numerical integration process to predict final vehicle states with Keplerian trajectories. The performance of the algorithm is evaluated by conducting 3-DOF computer simulations for off-nominal flight conditions. The numerical results show that Gamma guidance can reduce the orbit injection accuracy in comparison with that obtained by applying open-loop commands.

키워드

참고문헌

  1. Hardtla, J. W., "Gamma Guidance for the Inertial Upper Stage (IUS)," Guidance and Control Conference, August 1978, pp. 357~362.
  2. Hardtla, J. W. and Schultz, L. A., "Inertial Upper Stage /IUS/ Multi-mission Adaptability via Gamma Guidance Software Menu Tables," Guidance and Control Conference, 30 January 1982, pp. 213~227.
  3. Kuhns, R. H. and Coomer, G. C., "Gamma Guidance - Design and Results for two Flights," Proceedings of the Seventh Annual Rocky Mountain Conference, February 1984, pp. 295~310.
  4. Dasgupta, S. and Ramakrishna, S., "Explicit VG Guidance Algorithm for a Solid Powered Closed Loop Guidance Mission," IFAC Proceedings, June 1985, pp. 189~195.
  5. Yokota, K., et al., "Development and Flight Results of Guidance and Control System for 4th Epsilon Launch Vehicle," 30th ISTS, June 2019.
  6. Song, E. J. and Roh, W. R., "Modified Gamma Guidance for Satellite Launch Vehicles," Korea Automatic Control Conference, October 2005, pp. 492~498.
  7. Battin, R. H., An Introduction to the Mathematics and Methods of Astrodynamics, AIAA Education Series, Revised Edition, 1999, pp. 128~131.
  8. Der, G. J., "An Elegant State Transition Matrix," The Journal of the Astronautical Sciences, Vol. 45, No. 4, 1997, pp. 371~390. https://doi.org/10.1007/BF03546398
  9. Press, W. H., et al., Numerical Recipes in C : The Art of Scientific Computing, Cambridge University Press, Vol. XXVII, No. 1, 1979, pp. 1~38.