3-point inscribed angle guidance law

Ronny Tsalik, Tal Shima

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

Abstract

A planar three-point trajectory shaping guidance law against stationary targets was developed based upon the principle of constant inscribed angles in a circle. The guidance controller was designed through linearization. Linear and non-linear dynamic models were compared through simulation, and results are shown for various scenarios of applied desired impact angles. Utilization of this guidance law requires simply the inscribed angle in order to effectively shape the missile trajectory, allowing to impose impact angles. Application of the proposed strategy can enhance penetration capabilities, reduce a missile's warhead size, and reduce collateral damage.

Original languageEnglish
Title of host publication53rd Israel Annual Conference on Aerospace Sciences 2013
Pages256-277
Number of pages22
StatePublished - 2013
Event53rd Israel Annual Conference on Aerospace Sciences 2013 - Tel-Aviv and Haifa, Israel
Duration: 6 Mar 20137 Mar 2013

Publication series

Name53rd Israel Annual Conference on Aerospace Sciences 2013
Volume1

Conference

Conference53rd Israel Annual Conference on Aerospace Sciences 2013
Country/TerritoryIsrael
CityTel-Aviv and Haifa
Period6/03/137/03/13

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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