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 language | English |
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Title of host publication | Proceedings of 9th International Conference on Recent Advances in Space Technologies, RAST 2019 |
Editors | S. Menekay, O. Cetin, O. Alparslan |
Publisher | Institute of Electrical and Electronics Engineers Inc. |
Pages | 919-925 |
Number of pages | 7 |
ISBN (Electronic) | 9781538694480 |
DOIs | |
Publication status | Published - Jun 2019 |
Event | 9th International Conference on Recent Advances in Space Technologies, RAST 2019 - Istanbul, Turkey Duration: 11 Jun 2019 → 14 Jun 2019 |
Publication series
Name | Proceedings of 9th International Conference on Recent Advances in Space Technologies, RAST 2019 |
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Conference
Conference | 9th International Conference on Recent Advances in Space Technologies, RAST 2019 |
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Country/Territory | Turkey |
City | Istanbul |
Period | 11/06/19 → 14/06/19 |
Bibliographical note
Publisher Copyright:© 2019 IEEE.
Keywords
- guidance
- intercept
- kalman filter
- navigation