Minimal Exit Trajectories with Optimum Correctional Manoeuvres

Authors

  • T. N. Srivastava Directorate of Scientific Evaluation, New Delhi
  • A. K. Nangia Dte. of EDP. Sena Bhavan, New Delhi

DOI:

https://doi.org/10.14429/dsj.30.6451

Keywords:

Correctional manoeuvres, Noncoaxial elliptic orbits

Abstract

Minimal exit trajectories with optimum correctional manoeuvers to a rocket between two coplaner, noncoaxial elliptic orbits in an inverse square gravitational field have been investigated. Case of trajectories with no correctional manoeuvres has been analysed. In the end minimal exit trajectories through specified orbital terminals are discussed and problem of ref. (2) is derived as a particular case.

Author Biographies

T. N. Srivastava, Directorate of Scientific Evaluation, New Delhi

Directorate of Scientific Evaluation, New Delhi-110 001

A. K. Nangia, Dte. of EDP. Sena Bhavan, New Delhi

Dte. of EDP. Sena Bhavan, New Delhi-110 001

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Published

2014-02-21

How to Cite

Srivastava, T. N., & Nangia, A. K. (2014). Minimal Exit Trajectories with Optimum Correctional Manoeuvres. Defence Science Journal, 30(4), 183–186. https://doi.org/10.14429/dsj.30.6451

Issue

Vol. 30 No. 4

Section

General Papers

License

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