Online Trajectory Reshaping for a Launch Vehicle to Minimize the Final Error Caused by Navigation and Guidance

  • Tessy Thomas Advanced Systems Laboratory, Hyderabad
  • D. R. Jahagirdar Research Center Imarat, Hyderabad
  • Iyyanki V. Murali Krishna Jawaharlal Nehru Technological University, Hyderabad
  • L. Varaprasad Advanced Systems Laboratory, Hyderabad
DOI: https://doi.org/10.14429/dsj.63.2414
Keywords: Trajectory reshaping, launch vehicle, navigation, guidance errors

Abstract

Autonomous launch vehicles, once lifted off from the launch pad, equipped with an onboard intelligence which aids in achieving the mission objectives with high accuracy. The accuracy of the mission depends basically on navigation and guidance errors caused at burnout condition, after which the vehicle follows an elliptical path upto impact. The paper describes how to handle the final impact and injection error caused by these navigation and guidance errors. In the current work the initial burnout conditions are tuned and corrected such that the terminal impact point is achieved within the desired tolerance bounds. A two point boundary value problem is solved using the gradient method, for determining the impact errors. The algorithm is validated by simulation studies for various burnout conditions.

Defence Science Journal, 2013, 63(3), pp.254-261, DOI:http://dx.doi.org/10.14429/dsj.63.2414

Author Biographies

Tessy Thomas, Advanced Systems Laboratory, Hyderabad

Mrs Tessy Thomas received her BTech (Electrical) from the Calicut University, in 1985, ME (Guided Missiles) from the Poona University, in 1986 and MBA in Operations Management. She is presently working as Scientist ‘G’ and Project Director at the Advanced Systems Laboratory, Hyderabad. She is a fellow member of Indian National Academy of Engineering and life member of ASI&AeSI. She has received Agni Award for Excellence in Self-reliance - 2001, DRDO award for path breaking research/outstanding technology development - 2007, DRDO Scientist of the year Award - 2008, Suman Sharma Award - 2009, DRDO performance excellence award - 2011. Her research area includes: Missile guidance, mission design and trajectory simulation for long range missile systems.

D. R. Jahagirdar, Research Center Imarat, Hyderabad
Dr D R Jahagirdar received his BE (Electronics Engineering) from Govt. College of Engineering, Amravati University, in 1990; MTech (Microwave Engineering) from IIT, Kharagpur, in 1992 and PhD from Department of Electronics and Computer Science from Southampton, UK in 1997. He is presently working as Scientist in Research Center Imarat, DRDO, Hyderabad. He received Professor SK Mitra memorial award for best research oriented paper from IEEE - 2002, IETE-IRSI Young scientist award - 2005, and DRDO Scientist of the year award - 2010.
Iyyanki V. Murali Krishna, Jawaharlal Nehru Technological University, Hyderabad
Dr I V Murali Krishna received his MTech from IIT Madras and PhD from IISc, Bangalore in 1977. He is presently working as Director, Institute of Science and Technology and Coordinator of Centre for Atmospheric Sciences and Weather Modification Technologies at Jawaharlal Nehru Technological University, Hyderabad. He worked as a Lecturer, Guest Scientist and Professor in many universities. His areas of interest include: Geospatial technology, data mining, soft computing technologies, disaster management, satellite meteorology and weather informatics.
L. Varaprasad, Advanced Systems Laboratory, Hyderabad
Mr L Varaprasad received his BTech (Electronics & Instrumentation) from Jawaharlal Nehru Technological University, Hyderabad, in 2002 and ME (Aerospace Engineering) from Indian Institute of Science, Bangalore, in 2009. He is presently working as Scientist in Advanced Systems Laboratory, Hyderabad. He is a member of ASI, INSARM. He has been awarded DRDO Lab Scientist of the year - 2012. His areas of interest includes: Missile guidance, trajectory optimisation.
Published
2013-05-16
How to Cite
Thomas, T., Jahagirdar, D., Krishna, I., & Varaprasad, L. (2013). Online Trajectory Reshaping for a Launch Vehicle to Minimize the Final Error Caused by Navigation and Guidance. Defence Science Journal, 63(3), 254-261. https://doi.org/10.14429/dsj.63.2414
Issue
Vol 63 No 3
Section
Aeronautical Systems
Copyright (c) 2016 Defence Science Journal

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