Damping of the limited perturbations in the system of the aircraft control when landing
A linear model of the aircraft control system in the landing mode is consid- ered in the presence of limited external perturbations. The method of lin- ear matrix inequalities is implemented in the generalized H∞-optimization problem in order to evaluate and reduce the influence of external and i...
Збережено в:
| Дата: | 2020 |
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| Автори та афіліації: |
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| Ключові слова: | keywords |
| Автори: | , , , , , |
| Формат: | Стаття |
| Мова: | Українська |
| Опубліковано: |
Інститут математики НАН України
2020
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| Онлайн доступ: | https://trim.imath.kiev.ua/index.php/trim/article/view/427 |
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| Назва журналу: | Transactions of Institute of Mathematics of NAS of Ukraine |
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Репозитарії
Transactions of Institute of Mathematics of NAS of Ukraine| Резюме: | A linear model of the aircraft control system in the landing mode is consid- ered in the presence of limited external perturbations. The method of lin- ear matrix inequalities is implemented in the generalized H∞-optimization problem in order to evaluate and reduce the influence of external and ini- tial disturbances on qualitative characteristics of the system. In particular, influence of weight coefficients of the generalized quality criteria on the sta- bility factor and the transient process time of a closed system have been investigated.
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