RECONFIGURATION OF THE AIRCRAFT INTEGRATED CONTROL SYSTEM REGARDING CONTROL CONSTRAINTS UNDER ACTUATOR FAILURES
The aircraft integrated control system reconfiguration laws under failures of actuators, calculated disregarding physical constraints on control surfaces saturation, can lead to a complete loss of aircraft controllability and stability. Despite the large number of scientific publications in this fie...
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| Format: | Article |
| Language: | Russian |
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Moscow State Technical University of Civil Aviation
2018-12-01
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| Series: | Научный вестник МГТУ ГА |
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| Online Access: | https://avia.mstuca.ru/jour/article/view/1404 |
| _version_ | 1797882981764825088 |
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| author | A. M. Kulchak V. V. Kosyanchuk E. Yu. Zybin |
| author_facet | A. M. Kulchak V. V. Kosyanchuk E. Yu. Zybin |
| author_sort | A. M. Kulchak |
| collection | DOAJ |
| description | The aircraft integrated control system reconfiguration laws under failures of actuators, calculated disregarding physical constraints on control surfaces saturation, can lead to a complete loss of aircraft controllability and stability. Despite the large number of scientific publications in this field, practical systematic results have been obtained only for SISO (single input – single output) systems. Problems of the convergence of iterative algorithms restricting the set of admissible solutions and the conservatism of the reconfiguration laws designed using weight matrices do not allow solving this problem in general. For complex MIMO (multi input – multi output) systems there is still no widely accepted universal approach. In this work, control surfaces constraints are regarded in terms of the power of reconfiguration control. It is shown that by slight modification of pseudoinverse (optimal) solution it is possible to obtain approximate pseudoinverse (suboptimal) solutions with priory known minimum power (compensation matrix norm) and error (residual matrix norm) of the reconfiguration for a given degree of approximation. This allows for a multistep consistent reduction in power and increasing in error of reconfiguration, until an acceptable solution is obtained. By providing the greater reconfiguration error at each step we have additional freedom in reducing the reconfiguration power. This leads to a decrease in the amplitude of the deviations of the control surfaces, to which the signals from the failed control channels are redistributed. The simulation example of the aircraft integrated control system reconfiguration under the stabilizer’s actuator failure is presented. It is shown that the pseudoinverse reconfiguration problem solution leads to the significant ailerons’ constraints violation and the loss of aircraft controllability. Regarding control constraints solution reduces several times the deviation of the control surfaces and provides an effective problem solution in the permissible power and error reconfiguration range. |
| first_indexed | 2024-04-10T03:43:25Z |
| format | Article |
| id | doaj.art-f06f261062f84eff95f8ea8e3a22e86b |
| institution | Directory Open Access Journal |
| issn | 2079-0619 2542-0119 |
| language | Russian |
| last_indexed | 2024-04-10T03:43:25Z |
| publishDate | 2018-12-01 |
| publisher | Moscow State Technical University of Civil Aviation |
| record_format | Article |
| series | Научный вестник МГТУ ГА |
| spelling | doaj.art-f06f261062f84eff95f8ea8e3a22e86b2023-03-13T07:19:19ZrusMoscow State Technical University of Civil AviationНаучный вестник МГТУ ГА2079-06192542-01192018-12-01216657810.26467/2079-0619-2018-21-6-65-781271RECONFIGURATION OF THE AIRCRAFT INTEGRATED CONTROL SYSTEM REGARDING CONTROL CONSTRAINTS UNDER ACTUATOR FAILURESA. M. Kulchak0V. V. Kosyanchuk1E. Yu. Zybin2Федеральное государственное унитарное предприятие «Государственный научно-исследовательский институт авиационных систем»Федеральное государственное унитарное предприятие «Государственный научно-исследовательский институт авиационных систем»Федеральное государственное унитарное предприятие «Государственный научно-исследовательский институт авиационных систем»The aircraft integrated control system reconfiguration laws under failures of actuators, calculated disregarding physical constraints on control surfaces saturation, can lead to a complete loss of aircraft controllability and stability. Despite the large number of scientific publications in this field, practical systematic results have been obtained only for SISO (single input – single output) systems. Problems of the convergence of iterative algorithms restricting the set of admissible solutions and the conservatism of the reconfiguration laws designed using weight matrices do not allow solving this problem in general. For complex MIMO (multi input – multi output) systems there is still no widely accepted universal approach. In this work, control surfaces constraints are regarded in terms of the power of reconfiguration control. It is shown that by slight modification of pseudoinverse (optimal) solution it is possible to obtain approximate pseudoinverse (suboptimal) solutions with priory known minimum power (compensation matrix norm) and error (residual matrix norm) of the reconfiguration for a given degree of approximation. This allows for a multistep consistent reduction in power and increasing in error of reconfiguration, until an acceptable solution is obtained. By providing the greater reconfiguration error at each step we have additional freedom in reducing the reconfiguration power. This leads to a decrease in the amplitude of the deviations of the control surfaces, to which the signals from the failed control channels are redistributed. The simulation example of the aircraft integrated control system reconfiguration under the stabilizer’s actuator failure is presented. It is shown that the pseudoinverse reconfiguration problem solution leads to the significant ailerons’ constraints violation and the loss of aircraft controllability. Regarding control constraints solution reduces several times the deviation of the control surfaces and provides an effective problem solution in the permissible power and error reconfiguration range.https://avia.mstuca.ru/jour/article/view/1404реконфигурациякомплексная система управленияотказы приводовограничения на управлениеприближенное псевдообратное решениемощность реконфигурацииошибка реконфигурации |
| spellingShingle | A. M. Kulchak V. V. Kosyanchuk E. Yu. Zybin RECONFIGURATION OF THE AIRCRAFT INTEGRATED CONTROL SYSTEM REGARDING CONTROL CONSTRAINTS UNDER ACTUATOR FAILURES Научный вестник МГТУ ГА реконфигурация комплексная система управления отказы приводов ограничения на управление приближенное псевдообратное решение мощность реконфигурации ошибка реконфигурации |
| title | RECONFIGURATION OF THE AIRCRAFT INTEGRATED CONTROL SYSTEM REGARDING CONTROL CONSTRAINTS UNDER ACTUATOR FAILURES |
| title_full | RECONFIGURATION OF THE AIRCRAFT INTEGRATED CONTROL SYSTEM REGARDING CONTROL CONSTRAINTS UNDER ACTUATOR FAILURES |
| title_fullStr | RECONFIGURATION OF THE AIRCRAFT INTEGRATED CONTROL SYSTEM REGARDING CONTROL CONSTRAINTS UNDER ACTUATOR FAILURES |
| title_full_unstemmed | RECONFIGURATION OF THE AIRCRAFT INTEGRATED CONTROL SYSTEM REGARDING CONTROL CONSTRAINTS UNDER ACTUATOR FAILURES |
| title_short | RECONFIGURATION OF THE AIRCRAFT INTEGRATED CONTROL SYSTEM REGARDING CONTROL CONSTRAINTS UNDER ACTUATOR FAILURES |
| title_sort | reconfiguration of the aircraft integrated control system regarding control constraints under actuator failures |
| topic | реконфигурация комплексная система управления отказы приводов ограничения на управление приближенное псевдообратное решение мощность реконфигурации ошибка реконфигурации |
| url | https://avia.mstuca.ru/jour/article/view/1404 |
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