Study of Model Uncertainties Influence on the Impact Point Dispersion for a Gasodynamicaly Controlled Projectile

The article presents the analysis of the impact point dispersion reduction using lateral correction thrusters. Two types of control algorithms are used and four sources of uncertainties are taken into account: aerodynamic parameters, thrust curve, initial conditions and IMU errors. The Monte Carlo a...

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Autores principales: Jacewicz, Mariusz, Lichota, Piotr, Miedziński, Dariusz, Głębocki, Robert
Formato: Online Artículo Texto
Lenguaje:English
Publicado: MDPI 2022
Materias:
Article
Acceso en línea:https://www.ncbi.nlm.nih.gov/pmc/articles/PMC9099792/
https://www.ncbi.nlm.nih.gov/pubmed/35590947
http://dx.doi.org/10.3390/s22093257
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author Jacewicz, Mariusz
Lichota, Piotr
Miedziński, Dariusz
Głębocki, Robert
author_facet Jacewicz, Mariusz
Lichota, Piotr
Miedziński, Dariusz
Głębocki, Robert
author_sort Jacewicz, Mariusz
collection PubMed
description The article presents the analysis of the impact point dispersion reduction using lateral correction thrusters. Two types of control algorithms are used and four sources of uncertainties are taken into account: aerodynamic parameters, thrust curve, initial conditions and IMU errors. The Monte Carlo approach was used for simulations and Circular Error Probable was used as a measure of dispersion. Generic rocket mathematical and simulation model was created in MATLAB/Simulink 2020b environment. Results show that the use of control algorithms greatly reduces the impact point dispersion.
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spelling pubmed-90997922022-05-14 Study of Model Uncertainties Influence on the Impact Point Dispersion for a Gasodynamicaly Controlled Projectile Jacewicz, Mariusz Lichota, Piotr Miedziński, Dariusz Głębocki, Robert Sensors (Basel) Article The article presents the analysis of the impact point dispersion reduction using lateral correction thrusters. Two types of control algorithms are used and four sources of uncertainties are taken into account: aerodynamic parameters, thrust curve, initial conditions and IMU errors. The Monte Carlo approach was used for simulations and Circular Error Probable was used as a measure of dispersion. Generic rocket mathematical and simulation model was created in MATLAB/Simulink 2020b environment. Results show that the use of control algorithms greatly reduces the impact point dispersion. MDPI 2022-04-24 /pmc/articles/PMC9099792/ /pubmed/35590947 http://dx.doi.org/10.3390/s22093257 Text en © 2022 by the authors. https://creativecommons.org/licenses/by/4.0/Licensee MDPI, Basel, Switzerland. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license (https://creativecommons.org/licenses/by/4.0/).
spellingShingle Article
Jacewicz, Mariusz
Lichota, Piotr
Miedziński, Dariusz
Głębocki, Robert
Study of Model Uncertainties Influence on the Impact Point Dispersion for a Gasodynamicaly Controlled Projectile
title Study of Model Uncertainties Influence on the Impact Point Dispersion for a Gasodynamicaly Controlled Projectile
title_full Study of Model Uncertainties Influence on the Impact Point Dispersion for a Gasodynamicaly Controlled Projectile
title_fullStr Study of Model Uncertainties Influence on the Impact Point Dispersion for a Gasodynamicaly Controlled Projectile
title_full_unstemmed Study of Model Uncertainties Influence on the Impact Point Dispersion for a Gasodynamicaly Controlled Projectile
title_short Study of Model Uncertainties Influence on the Impact Point Dispersion for a Gasodynamicaly Controlled Projectile
title_sort study of model uncertainties influence on the impact point dispersion for a gasodynamicaly controlled projectile
topic Article
url https://www.ncbi.nlm.nih.gov/pmc/articles/PMC9099792/
https://www.ncbi.nlm.nih.gov/pubmed/35590947
http://dx.doi.org/10.3390/s22093257
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