Minimum time ascent phase trajectory optimization using steepest descent method

Diksha Diva Singh, Vishnu G. Nair, M. V. Dileep

Research output: Contribution to journalArticle

1 Citation (Scopus)

Abstract

In this paper, ascent phase gravity turn trajectory of a launch vehicle is taken into account. Minimum-time problem of optimization is considered for specified structural and propulsive data. The objective is to achieve the target in minimum time and minimum error at terminal point by taking into account all the constraints. Trajectory generation is done for a single stage rocket in 2-D plane and computed for a given initial and final conditions. Hamiltonian is formulated by converting the given problem into secure final flight path angle problem and Pontryagin minimum principle is used to find the necessary conditions. The non-linear equations are solved using gradient method. Ultimately, the numerical results are evaluated and validity of result is exhibited.

Original languageEnglish
Pages (from-to)71-76
Number of pages6
JournalInternational Journal of Control Theory and Applications
Volume9
Issue number39
Publication statusPublished - 2016
Externally publishedYes

Fingerprint

Steepest descent method
Trajectories
Hamiltonians
Flight paths
Gradient methods
Launch vehicles
Rockets
Nonlinear equations
Gravitation

All Science Journal Classification (ASJC) codes

  • Computer Science(all)

Cite this

Singh, Diksha Diva ; Nair, Vishnu G. ; Dileep, M. V. / Minimum time ascent phase trajectory optimization using steepest descent method. In: International Journal of Control Theory and Applications. 2016 ; Vol. 9, No. 39. pp. 71-76.
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Minimum time ascent phase trajectory optimization using steepest descent method. / Singh, Diksha Diva; Nair, Vishnu G.; Dileep, M. V.

In: International Journal of Control Theory and Applications, Vol. 9, No. 39, 2016, p. 71-76.

Research output: Contribution to journalArticle

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