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Tentative Solutions for Indirect Optimization of Spacecraft Trajectories

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Space Engineering

Part of the book series: Springer Optimization and Its Applications ((SOIA,volume 114))

Abstract

In this chapter, the problem of improving convergence and finding suitable tentative solutions for the indirect optimization of spacecraft trajectories is discussed. The application of theory of optimal control to spacecraft trajectories transforms the optimal control problem into a multi-point boundary value problem, which is usually solved by means of an iterative procedure. The convergence radius of the problem may be small and convergence to the optimal solution is only obtained if the tentative solution, which is used to start the procedure, is sufficiently close to the optimum. The definition of a suitable solution is often the hardest part of the solution procedure for the optimization problem. Several cases and examples are presented in this chapter to illustrate the measures that could be adopted for the most common difficulties, which may be found during the optimization of space trajectories.

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Author information

Authors and Affiliations

  1. Università di Roma “Sapienza”, Via Eudossiana, 18, Roma, Italy

    Guido Colasurdo

  2. Politecnico di Torino, Corso Duca degli Abruzzi, 24, Torino, Italy

    Lorenzo Casalino

Authors
  1. Guido Colasurdo
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  2. Lorenzo Casalino
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Corresponding author

Correspondence to Guido Colasurdo .

Editor information

Editors and Affiliations

  1. Exploration and Science Thales Alenia Space, Turin, Italy

    Giorgio Fasano

  2. PCS Inc., Halifax, NS, Canada

    János D. Pintér

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Colasurdo, G., Casalino, L. (2016). Tentative Solutions for Indirect Optimization of Spacecraft Trajectories. In: Fasano, G., Pintér, J.D. (eds) Space Engineering. Springer Optimization and Its Applications, vol 114. Springer, Cham. https://doi.org/10.1007/978-3-319-41508-6_3

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