Design of Composite Feedback and Feedforward Control Law for Aircraft Inertially Stabilized Platforms
The design of the control systems of the inertially stabilized platforms (ISPs) as part of airborne equipment for the majority of aircraft has its peculiarity. The presence of rate gyros in the inertial measurement unit gives the possibility to measure the rotation rate of the ISP base, which is the...
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| Format: | Article |
| Language: | English |
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Wiley
2020-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2020/8853928 |
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| author | Valerii Azarskov Anatoly Tunik Olha Sushchenko |
| author_facet | Valerii Azarskov Anatoly Tunik Olha Sushchenko |
| author_sort | Valerii Azarskov |
| collection | DOAJ |
| description | The design of the control systems of the inertially stabilized platforms (ISPs) as part of airborne equipment for the majority of aircraft has its peculiarity. The presence of rate gyros in the inertial measurement unit gives the possibility to measure the rotation rate of the ISP base, which is the main disturbance interfering with the ISP accuracy. Inclusion of the feedforward disturbance gain in the control law with the simplest PI feedback significantly improves the accuracy of stabilization by the invariance theory. A combination of feedback and feedforward controllers produces a synergetic effect, thus, improving ISP accuracy. This article deals with the design of the airborne ISP control systems consisting of two stages: the parametric optimization of the PI feedback control based on composite “performance-robustness” criterion and the augmentation of the obtained system with feedforward gain. To prove the efficiency of the proposed control laws, the simulation of the ISP was undertaken. We have used a simulation of the heading-hold system of the commuter aircraft Beaver and the yaw rate output of this closed-loop system we have used as a source of the disturbance. The results of modeling proved the efficiency of the proposed design method. |
| format | Article |
| id | doaj-art-e554aa6cc55342f180fa951211949d01 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2020-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-e554aa6cc55342f180fa951211949d012025-02-03T06:46:37ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742020-01-01202010.1155/2020/88539288853928Design of Composite Feedback and Feedforward Control Law for Aircraft Inertially Stabilized PlatformsValerii Azarskov0Anatoly Tunik1Olha Sushchenko2Aerospace Control Systems Department, National Aviation University, Liubomyra Huzara, ave. 1, Kyiv 03058, UkraineAerospace Control Systems Department, National Aviation University, Liubomyra Huzara, ave. 1, Kyiv 03058, UkraineAerospace Control Systems Department, National Aviation University, Liubomyra Huzara, ave. 1, Kyiv 03058, UkraineThe design of the control systems of the inertially stabilized platforms (ISPs) as part of airborne equipment for the majority of aircraft has its peculiarity. The presence of rate gyros in the inertial measurement unit gives the possibility to measure the rotation rate of the ISP base, which is the main disturbance interfering with the ISP accuracy. Inclusion of the feedforward disturbance gain in the control law with the simplest PI feedback significantly improves the accuracy of stabilization by the invariance theory. A combination of feedback and feedforward controllers produces a synergetic effect, thus, improving ISP accuracy. This article deals with the design of the airborne ISP control systems consisting of two stages: the parametric optimization of the PI feedback control based on composite “performance-robustness” criterion and the augmentation of the obtained system with feedforward gain. To prove the efficiency of the proposed control laws, the simulation of the ISP was undertaken. We have used a simulation of the heading-hold system of the commuter aircraft Beaver and the yaw rate output of this closed-loop system we have used as a source of the disturbance. The results of modeling proved the efficiency of the proposed design method.http://dx.doi.org/10.1155/2020/8853928 |
| spellingShingle | Valerii Azarskov Anatoly Tunik Olha Sushchenko Design of Composite Feedback and Feedforward Control Law for Aircraft Inertially Stabilized Platforms International Journal of Aerospace Engineering |
| title | Design of Composite Feedback and Feedforward Control Law for Aircraft Inertially Stabilized Platforms |
| title_full | Design of Composite Feedback and Feedforward Control Law for Aircraft Inertially Stabilized Platforms |
| title_fullStr | Design of Composite Feedback and Feedforward Control Law for Aircraft Inertially Stabilized Platforms |
| title_full_unstemmed | Design of Composite Feedback and Feedforward Control Law for Aircraft Inertially Stabilized Platforms |
| title_short | Design of Composite Feedback and Feedforward Control Law for Aircraft Inertially Stabilized Platforms |
| title_sort | design of composite feedback and feedforward control law for aircraft inertially stabilized platforms |
| url | http://dx.doi.org/10.1155/2020/8853928 |
| work_keys_str_mv | AT valeriiazarskov designofcompositefeedbackandfeedforwardcontrollawforaircraftinertiallystabilizedplatforms AT anatolytunik designofcompositefeedbackandfeedforwardcontrollawforaircraftinertiallystabilizedplatforms AT olhasushchenko designofcompositefeedbackandfeedforwardcontrollawforaircraftinertiallystabilizedplatforms |