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Volume 41 Issue 2
Feb.  2015
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Journal of Beijing University of Aeronautics and Astronautics  > 2015  >  41(2): 228-233.
ZHANG Hongli, LUO Qinqin, HAN Chaoet al. Application of UKF parameter estimation in the three-body Lambert problem[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(2): 228-233. doi: 10.13700/j.bh.1001-5965.2014.0120(in Chinese)
Citation: ZHANG Hongli, LUO Qinqin, HAN Chaoet al. Application of UKF parameter estimation in the three-body Lambert problem[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(2): 228-233. doi: 10.13700/j.bh.1001-5965.2014.0120(in Chinese)
shu

Application of UKF parameter estimation in the three-body Lambert problem

doi: 10.13700/j.bh.1001-5965.2014.0120
  • 1.

    School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • 2. Beijing Aerospace Technology Institute, Beijing 100074, China

  • Received Date: 12 Mar 2014
  • Publish Date: 20 Feb 2015
    Abstract
  • A new algorithm based on unscented Kalman filter (UKF) parameter estimation was proposed for the fast and efficient solution of the three-body Lambert problem. The algorithm was divided into two steps, guessing the initial solution and searching the exact solution. The initial solution of the three-body Lambert problem was generated using the two-body model of the Earth-Moon system. Then the two-point boundary value problem corresponding to the original three-body Lambert problem was converted to a parameter estimation problem. Through solving the converted problem using UKF, the converged exact solution was found. The algorithm was based on the theory of probability, so the derivation of the gradient matrixes required by traditional numerical methods was omitted. Moreover, the demand for the accuracy of the initial solutions for the three-body Lambert problem was modified. Therefore, the difficulty of solving the three-body Lambert problem was greatly reduced. Numerical examples indicate that the algorithm is of high efficiency and robustness and obtains a larger convergence domain compared with the differential-correction method and the second order differential-correction method.

     

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    • References(15)
  • [1]
    Bate R, Mueller D,White J.Fundamentals of astrodynamics[M].New York:Dover Publications,1971:177-275.
    [2]
    Battin R H, Vaughan R M.An elegant Lambert algorithm[J].Journal of Guidance,Control and Dynamics,1984,7(6):662-670.
    [3]
    Gooding R H. A procedure for the solution of Lambert's orbital boundary-value problem[J].Celestial Mechanics & Dynamical Astronomy,1990,48(2):145-165.
    [4]
    D'Amarion L, Byrnes D,Sackett L.Optimization of multiple flyby trajectories[C]//AAS/AIAA Astrodynamics Specialists Conference.Provincetown:AIAA Paper 1979:79-162.
    [5]
    Armellin R, Di Lizia P,Topputo F,et al.Gravity assist space pruning based on differential algebra[J].Celestial Mechanics and Dynamical Astronomy,2010,106(1):1-24.
    [6]
    Jesicak M, Ocampo C.Automated generation of symmetric lunar free-return trajectories[J].Journal of Guidance,Control and Dynamics,2011,34(1):98-106.
    [7]
    Luo Q, Yin J,Han C.Design of earth-moon free-return trajectories[J].Journal of Guidance,Control,and Dynamics,2012,36(1): 263-271.
    [8]
    Okutsu M, Longuski J.Mars free returns via gravity assist from Venus[J].Journal of Spacecraft and Rockets,2002,39(1):31-36.
    [9]
    Prado A F B A. Traveling between the Lagrangian points and the Earth[J].Acta Astronautica,1996,39(7):483-486.
    [10]
    Lian Y J, Jiang X Y,Tang G J.Halo-to-halo cost optimal transfer based on CMA-ES[C]//Proceedings of the 32nd Chinese Control Conference,CCC 2013.Piscataway,NJ:IEEE,2013:2468-2473.
    [11]
    Zazzera F B, Topputo F,Massari M.Assessment of mission design including utilization of libration points and weak stability boundaries, 18147/04/NL/mv[R].Frascati,Italy:ESA,2003.
    [12]
    Byrnes D V. Application of the pseudostate theory to the three-body Lambert problem[J].Journal of the Astronautical Sciences,1989,37:221-232.
    [13]
    Sukhanov A, Prado A F B A.Lambert problem solution in the Hill model of motion[J].Celestial Mechanics & Dynamical Astronomy,2004,90(3):331-354.
    [14]
    罗钦钦,韩潮. 包含引力辅助变轨的三体Lambert问题求解算法[J].北京航空航天大学学报,2013,39(5):679-687. Luo Q Q,Han C.Solution algorithm of the three-body Lambert problem with gravity assist maneuver[J].Journal of Beijing University of Aeronautics and Astronautics,2013,39(5):679-687(in Chinese).
    [15]
    Haykin S. Kalman filtering and neural networks[M].New York:John Wiley & Sons Inc,2002.
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