AGILE FLIGHT VEHICLE FIN FAILURE TOLERANT CONTROL USING INERTIAL MEASUREMENT UNIT DATA
In this paper, a new model-based fault detection method for an agile supersonic flight vehicle is presented. A nonlinear model, controlled by a classical closed loop controller an...
| Main Authors: | , |
|---|---|
| Format: | Article |
| Language: | fas |
| Published: |
Sharif University of Technology
2020-05-01
|
| Series: | مهندسی مکانیک شریف |
| Subjects: | |
| Online Access: | https://sjme.journals.sharif.edu/article_21645_ab58026202bd5cc40fc08dba97a8b3c5.pdf |
| _version_ | 1797404456083521536 |
|---|---|
| author | A. Ashrafifar Mohsen Fathi Jegarkandi |
| author_facet | A. Ashrafifar Mohsen Fathi Jegarkandi |
| author_sort | A. Ashrafifar |
| collection | DOAJ |
| description | In this paper, a new model-based fault detection method for an agile supersonic
flight vehicle is presented. A nonlinear model, controlled by a classical closed loop controller and proportional navigation guidance in interception scenario, describes the behavior of the vehicle. The proposed FDD method uses Inertial measurement unit (IMU) data and nonlinear dynamic model of the vehicle to inform fins damage to the controller before leading to an undesired performance or mission failure. Broken, burnt or not opening of control surfaces causes a drastic change in aerodynamic coefficients and thus dynamic model. Therefore, in addition to the changes in the control forces and moments, system dynamics will change too, leading to the failure detection process being encountered with difficulty. To this purpose, an equivalent aerodynamic model is proposed to represent the dynamics of the vehicle, and the health of each fin is monitored by the value of a parameter which is estimated using a nonlinear filter. To identify model changes after fin failure, the aerodynamics of body and control surfaces are modeled separately. A percentage of the fins which have the ability to generate aerodynamic force is modeled by a parameter and these parameters are estimated over time, using a nonlinear estimator. Parameters estimation through the filtering approach is an indirect procedure, consisting of transforming the problem into a state estimation problem. The value of these parameters will be between 0 and 1. Where value 1 corresponds to the health of the fin and value denotes whether the fin has not opened or has been destroyed completely. The proposed method detects and isolates fins damage in a few seconds with good accuracy. Simulation results show that the new failure diagnosis algorithm estimated fins health percentage with good accuracy. After estimating the parameters, they can be sent to the controller and the controller has changed control signal. |
| first_indexed | 2024-03-09T02:55:14Z |
| format | Article |
| id | doaj.art-90e52dcfb3b1482c966e36cd9c5c3c80 |
| institution | Directory Open Access Journal |
| issn | 2676-4725 2676-4733 |
| language | fas |
| last_indexed | 2024-03-09T02:55:14Z |
| publishDate | 2020-05-01 |
| publisher | Sharif University of Technology |
| record_format | Article |
| series | مهندسی مکانیک شریف |
| spelling | doaj.art-90e52dcfb3b1482c966e36cd9c5c3c802023-12-05T07:27:17ZfasSharif University of Technologyمهندسی مکانیک شریف2676-47252676-47332020-05-0136.31677510.24200/j40.2019.53009.150921645AGILE FLIGHT VEHICLE FIN FAILURE TOLERANT CONTROL USING INERTIAL MEASUREMENT UNIT DATAA. Ashrafifar0Mohsen Fathi Jegarkandi1Dept. of Aerospace Engineering Sharif University of TechnologyAerospace Engineering Department, Sharif University of Technology.In this paper, a new model-based fault detection method for an agile supersonic flight vehicle is presented. A nonlinear model, controlled by a classical closed loop controller and proportional navigation guidance in interception scenario, describes the behavior of the vehicle. The proposed FDD method uses Inertial measurement unit (IMU) data and nonlinear dynamic model of the vehicle to inform fins damage to the controller before leading to an undesired performance or mission failure. Broken, burnt or not opening of control surfaces causes a drastic change in aerodynamic coefficients and thus dynamic model. Therefore, in addition to the changes in the control forces and moments, system dynamics will change too, leading to the failure detection process being encountered with difficulty. To this purpose, an equivalent aerodynamic model is proposed to represent the dynamics of the vehicle, and the health of each fin is monitored by the value of a parameter which is estimated using a nonlinear filter. To identify model changes after fin failure, the aerodynamics of body and control surfaces are modeled separately. A percentage of the fins which have the ability to generate aerodynamic force is modeled by a parameter and these parameters are estimated over time, using a nonlinear estimator. Parameters estimation through the filtering approach is an indirect procedure, consisting of transforming the problem into a state estimation problem. The value of these parameters will be between 0 and 1. Where value 1 corresponds to the health of the fin and value denotes whether the fin has not opened or has been destroyed completely. The proposed method detects and isolates fins damage in a few seconds with good accuracy. Simulation results show that the new failure diagnosis algorithm estimated fins health percentage with good accuracy. After estimating the parameters, they can be sent to the controller and the controller has changed control signal.https://sjme.journals.sharif.edu/article_21645_ab58026202bd5cc40fc08dba97a8b3c5.pdffin failure detectionnonlinear kalman filterfin control agile vehicleparameter estimationaerodynamic coefficient estimation |
| spellingShingle | A. Ashrafifar Mohsen Fathi Jegarkandi AGILE FLIGHT VEHICLE FIN FAILURE TOLERANT CONTROL USING INERTIAL MEASUREMENT UNIT DATA مهندسی مکانیک شریف fin failure detection nonlinear kalman filter fin control agile vehicle parameter estimation aerodynamic coefficient estimation |
| title | AGILE FLIGHT VEHICLE FIN FAILURE TOLERANT CONTROL USING INERTIAL MEASUREMENT UNIT DATA |
| title_full | AGILE FLIGHT VEHICLE FIN FAILURE TOLERANT CONTROL USING INERTIAL MEASUREMENT UNIT DATA |
| title_fullStr | AGILE FLIGHT VEHICLE FIN FAILURE TOLERANT CONTROL USING INERTIAL MEASUREMENT UNIT DATA |
| title_full_unstemmed | AGILE FLIGHT VEHICLE FIN FAILURE TOLERANT CONTROL USING INERTIAL MEASUREMENT UNIT DATA |
| title_short | AGILE FLIGHT VEHICLE FIN FAILURE TOLERANT CONTROL USING INERTIAL MEASUREMENT UNIT DATA |
| title_sort | agile flight vehicle fin failure tolerant control using inertial measurement unit data |
| topic | fin failure detection nonlinear kalman filter fin control agile vehicle parameter estimation aerodynamic coefficient estimation |
| url | https://sjme.journals.sharif.edu/article_21645_ab58026202bd5cc40fc08dba97a8b3c5.pdf |
| work_keys_str_mv | AT aashrafifar agileflightvehiclefinfailuretolerantcontrolusinginertialmeasurementunitdata AT mohsenfathijegarkandi agileflightvehiclefinfailuretolerantcontrolusinginertialmeasurementunitdata |