International Journal of Aeronautical and Space Sciences

  • 제4권2호
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  • Pages.1-8
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  • 2003
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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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A New Method of determining Initial Conditions for Satellite Formation Flying

  • 발행 : 2003.11.30
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초록

Satellite formation flying is the placing micro-satellites with the same mission into nearby orbits to form a cluster. Clohessy-Wiltshire equations are used to describe the relative motion and control strategies between satellites within a cluster, which are known as Hill's equations. Even though Hill's equations are powerful in determining initial conditions for the satellite formation flying, they can not accurately express the relative motion under J2 perturbation. Some methods have been developed for the determination of initial conditions to avoid limits of Hill's equation. This paper gives a new method of determining initial conditions using mean elements. For this research mean elements were transformed to osculating elements using Brouwer's theory and the orbit was propaeated with the consideration of J2-J8 to get a relative position. The results show that satellites within a cluster are maintained in the desired boundary for long period and the method is effective on a fuel saving for satellite formation flying.

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참고문헌

  1. Folta, D.C. and Newman, L., 1996, "Foundations of Formation Flying for Mission to Planet Earth and New Millennium", AIAA 96- 3645, AIAA Guidance, Navigation, and Control Conference and Exhibit, San Diego, CA.
  2. Schaub, H., Alfriend, K. T., 1999, "J2 lnvariant Reference Orbits for Spacecraft Formations", Flight Mechanics Symposium, NASA Goddard Space Flight Center, May 18-20, Paper No. 11.
  3. Vadali, S. R., Vaddi, S. S. and Alfriend, K. T., 2002, "An intelligent Control Concept for Formation Flying Satellites", Intemational Journal of Robust and Nonlinear Control, Vol. 12, pp. 97-115. https://doi.org/10.1002/rnc.678
  4. Schweighart, S. A. and Sedwick, R. J., 2002, "High- Fidelity Linearized J2 Model for Satellite Formation Flight", Journal of Guidance, Control and Dynamics, Vol. 25, No. 6, pp. 1073-1080. https://doi.org/10.2514/2.4986
  5. Vaddi， S. S., Vadali, S. R. and Alfriend, K. T., 2003, "Formation Flying:Accommodating Nonlinearity and Eccentricity Perturbations", Joumal of Guidance, Control and Dynamics, Vol. 26, No. 2, pp. 214-223 https://doi.org/10.2514/2.5054
  6. Melton, R. G., 2000, "Time Explicit Representation of Relative Motion Between Elliptical Orbits", Joumal of Guidance, Control and Dynamics, Vol. 23, No. 4, pp. 604-610. https://doi.org/10.2514/2.4605
  7. Gim, D-W. and Alfriend, K. T., 2001, "The State Transition Matrix of Relative Motion for the Perturbed Non-circular Reference Orbit", AAS paper 01-222, AAS/AIAA Space Flight Mechanics Conference, Santa Barbara, CA, February 11-16
  8. Brouwer, D., 1959, "Solution of the Problem of Artificial Satellite Theory Without Drag", The Astronautical Journal, Vol. 64, No. 1274, pp. 378-397.
  9. Lyddane, R. H., 1963, "Small Eccentricities or lnclinations in the Brouwer Theory of the Artificial Satellite", The Astronomical Juournal, Vol. 68, No. 8, pp. 555-558. https://doi.org/10.1086/109179
  10. Felix R. H., 1981, "Reformulation of the Brouwer Geopotential Theory for Irnproved Computational Efficiency" Celestial Mechanics, Vol. 24, pp. 367-375. https://doi.org/10.1007/BF01230396
  11. Alfriend, K. T., Schaub, S. and Gim, D-W, 2000, "Gravitational Perturbations, Nonlinearity and Circular Orbit Assumption Effects on Formation Flying Control Strategies", AAS paper 00-12, 23rd Annual AAS guidance and Control Conference, Breckenridge, CO, February 2-6
  12. Vadali, S. R., Alfriend K. T. and Vaddi S. S., 2000, "Hill's Equations, Mean Orbital Elements, and Formatíon Flying of Satellites." AAS Paper 00-258, Presented at the R.H. Battin Astrodynamics Conference College Station, TX, March 20-21