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Information Journal Paper

Title

FINDING OPTIMAL SATELLITE LAUNCH TRAJECTORIES USING THE LINEAR TANGENT GUIDANCE LAW

Pages

  75-80

Keywords

Not Registered.

Abstract

 The problem studied in this paper consists of the optimal launch of a satellite to a circular orbit of the earth. The effect of the air resistance is also taken into consideration. The equations of optimal launch are first derived and the main problem is converted to a Two-Point Boundary Value Problem (TPBVP). A set of state and co-state variables, corresponding to the ideal case of planar earth with no air resistance, i.e. the case in which the linear tangent guidance law is, in fact, optimal, is used as an initial guess, in order to solve the TPBVP using the shooting algorithm. A gradual or step-by-step introduction of the air resistance effect is shown to make the numerical computations converge, thus, alleviating the problems caused by the shooting algorithm's sensitivity to the initial guess. Simulations reveal that the proposed method also has a satisfactory speed of convergence.

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  • Cite

    APA: Copy

    MARDANI, M., & MOUBED, M.. (2007). FINDING OPTIMAL SATELLITE LAUNCH TRAJECTORIES USING THE LINEAR TANGENT GUIDANCE LAW. INDUSTRIAL ENGINEERING & MANAGEMENT SHARIF (SHARIF: ENGINEERING), 23(38), 75-80. SID. https://sid.ir/paper/107755/en

    Vancouver: Copy

    MARDANI M., MOUBED M.. FINDING OPTIMAL SATELLITE LAUNCH TRAJECTORIES USING THE LINEAR TANGENT GUIDANCE LAW. INDUSTRIAL ENGINEERING & MANAGEMENT SHARIF (SHARIF: ENGINEERING)[Internet]. 2007;23(38):75-80. Available from: https://sid.ir/paper/107755/en

    IEEE: Copy

    M. MARDANI, and M. MOUBED, “FINDING OPTIMAL SATELLITE LAUNCH TRAJECTORIES USING THE LINEAR TANGENT GUIDANCE LAW,” INDUSTRIAL ENGINEERING & MANAGEMENT SHARIF (SHARIF: ENGINEERING), vol. 23, no. 38, pp. 75–80, 2007, [Online]. Available: https://sid.ir/paper/107755/en

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