Adaptive Fuzzy Sliding Mode Guidance Law considering Available Acceleration and Autopilot Dynamics
Terminal guidance law for missiles intercepting high maneuvering targets considering the limited available acceleration and autopilot dynamics of interceptor is investigated. Conventional guidance laws based on adaptive sliding mode control theory were designed to intercept a maneuvering target. How...
Saved in:
| Main Authors: | , , , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
Wiley
2018-01-01
|
| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2018/6081801 |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
| _version_ | 1832558942361747456 |
|---|---|
| author | Yulin Wang Shengjing Tang Wei Shang Jie Guo |
| author_facet | Yulin Wang Shengjing Tang Wei Shang Jie Guo |
| author_sort | Yulin Wang |
| collection | DOAJ |
| description | Terminal guidance law for missiles intercepting high maneuvering targets considering the limited available acceleration and autopilot dynamics of interceptor is investigated. Conventional guidance laws based on adaptive sliding mode control theory were designed to intercept a maneuvering target. However, they demand a large acceleration for interceptor at the end of the terminal guidance, which may have acceleration saturation especially when the target acceleration is close to the available acceleration of interceptor. In this paper, a terminal guidance law considering the available acceleration and autopilot dynamics of interceptor is proposed. Then, a fuzzy system is utilized to approximate and replace the variable structure term, which can handle the unknown target acceleration. And an adaptive neural network system is adopted to compensate the effects caused by the designed overlarge acceleration of interceptor such that the interceptor with small available acceleration can intercept the high maneuvering target. Simulation results show that the guidance law with available acceleration and autopilot dynamics (AAADG) is highly effective for reducing the acceleration command and achieving a small final miss distance. |
| format | Article |
| id | doaj-art-83230591cb084f63ac5f312065b3cb17 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2018-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-83230591cb084f63ac5f312065b3cb172025-02-03T01:31:11ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742018-01-01201810.1155/2018/60818016081801Adaptive Fuzzy Sliding Mode Guidance Law considering Available Acceleration and Autopilot DynamicsYulin Wang0Shengjing Tang1Wei Shang2Jie Guo3School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, ChinaSchool of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, ChinaSystem Design Institute of Hubei Aerospace Technology Academy, Hubei, 430040, ChinaSchool of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, ChinaTerminal guidance law for missiles intercepting high maneuvering targets considering the limited available acceleration and autopilot dynamics of interceptor is investigated. Conventional guidance laws based on adaptive sliding mode control theory were designed to intercept a maneuvering target. However, they demand a large acceleration for interceptor at the end of the terminal guidance, which may have acceleration saturation especially when the target acceleration is close to the available acceleration of interceptor. In this paper, a terminal guidance law considering the available acceleration and autopilot dynamics of interceptor is proposed. Then, a fuzzy system is utilized to approximate and replace the variable structure term, which can handle the unknown target acceleration. And an adaptive neural network system is adopted to compensate the effects caused by the designed overlarge acceleration of interceptor such that the interceptor with small available acceleration can intercept the high maneuvering target. Simulation results show that the guidance law with available acceleration and autopilot dynamics (AAADG) is highly effective for reducing the acceleration command and achieving a small final miss distance.http://dx.doi.org/10.1155/2018/6081801 |
| spellingShingle | Yulin Wang Shengjing Tang Wei Shang Jie Guo Adaptive Fuzzy Sliding Mode Guidance Law considering Available Acceleration and Autopilot Dynamics International Journal of Aerospace Engineering |
| title | Adaptive Fuzzy Sliding Mode Guidance Law considering Available Acceleration and Autopilot Dynamics |
| title_full | Adaptive Fuzzy Sliding Mode Guidance Law considering Available Acceleration and Autopilot Dynamics |
| title_fullStr | Adaptive Fuzzy Sliding Mode Guidance Law considering Available Acceleration and Autopilot Dynamics |
| title_full_unstemmed | Adaptive Fuzzy Sliding Mode Guidance Law considering Available Acceleration and Autopilot Dynamics |
| title_short | Adaptive Fuzzy Sliding Mode Guidance Law considering Available Acceleration and Autopilot Dynamics |
| title_sort | adaptive fuzzy sliding mode guidance law considering available acceleration and autopilot dynamics |
| url | http://dx.doi.org/10.1155/2018/6081801 |
| work_keys_str_mv | AT yulinwang adaptivefuzzyslidingmodeguidancelawconsideringavailableaccelerationandautopilotdynamics AT shengjingtang adaptivefuzzyslidingmodeguidancelawconsideringavailableaccelerationandautopilotdynamics AT weishang adaptivefuzzyslidingmodeguidancelawconsideringavailableaccelerationandautopilotdynamics AT jieguo adaptivefuzzyslidingmodeguidancelawconsideringavailableaccelerationandautopilotdynamics |