Performance comparison of guidance algorithms for asteroid intercept

Erdem Turan, Chingiz Hajiyev

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

1 Citation (Scopus)

Abstract

Linear quadratic one-sided optimized guidance laws and particle swarm optimization guidance law are investigated for hypervelocity asteroid intercept mission. Also, this paper examines the effect of noise on the line of sight measurements. In order to extract the actual value of the line of sight rate, the Kalman filter algorithm is used for certain guidance laws. Homing loop simulation results based upon Monte Carlo method show the effectiveness and accuracy of the various guidance laws.

Original languageEnglish
Title of host publicationProceedings of 9th International Conference on Recent Advances in Space Technologies, RAST 2019
EditorsS. Menekay, O. Cetin, O. Alparslan
PublisherInstitute of Electrical and Electronics Engineers Inc.
Pages919-925
Number of pages7
ISBN (Electronic)9781538694480
DOIs
Publication statusPublished - Jun 2019
Event9th International Conference on Recent Advances in Space Technologies, RAST 2019 - Istanbul, Turkey
Duration: 11 Jun 201914 Jun 2019

Publication series

NameProceedings of 9th International Conference on Recent Advances in Space Technologies, RAST 2019

Conference

Conference9th International Conference on Recent Advances in Space Technologies, RAST 2019
Country/TerritoryTurkey
CityIstanbul
Period11/06/1914/06/19

Bibliographical note

Publisher Copyright:
© 2019 IEEE.

Keywords

  • guidance
  • intercept
  • kalman filter
  • navigation

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