Prescribed Performance Guidance Law with Multiple Constraints
In the terminal guidance phase of intercepting aerial target, a guidance law, satisfying impact angle constraint, acceleration constraint, and second-order dynamic characteristic of interceptor autopilot, is designed based on the prescribed performance control and dynamic surface control method. Fir...
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| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
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Wiley
2022-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2022/5191568 |
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| _version_ | 1832563447100866560 |
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| author | Xu Li Jikun Ye Chijun Zhou Xiao Tang |
| author_facet | Xu Li Jikun Ye Chijun Zhou Xiao Tang |
| author_sort | Xu Li |
| collection | DOAJ |
| description | In the terminal guidance phase of intercepting aerial target, a guidance law, satisfying impact angle constraint, acceleration constraint, and second-order dynamic characteristic of interceptor autopilot, is designed based on the prescribed performance control and dynamic surface control method. Firstly, a two-dimensional plane interception model considering the dynamic characteristics of autopilot and input constraints is established. Furthermore, for the nonconstrained system, based on the dynamic surface control, the prescribed performance reaching law is used to ensure that the line-of-sight angle and the line-of-sight angle rate can converge to the prescribed range in finite time. At the same time, an adaptive law is used to estimate the uncertainty caused by target maneuver and autopilot. Then, aiming at the acceleration constraint, an auxiliary system is established to convert the restricted system into a nonrestricted system. The finite-time convergence of the terminal line-of-sight tracking error, the line-of-sight rate, and the uniform ultimate boundedness of the system are rigorously proved by Lyapunov stability theory. Finally, the simulation results show that the proposed guidance law can make the interceptor have better interception performance when attacking targets with different maneuvering forms. |
| format | Article |
| id | doaj-art-a3633c2e54c341969cb1edc434e436f9 |
| institution | Kabale University |
| issn | 1687-5974 |
| language | English |
| publishDate | 2022-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-a3633c2e54c341969cb1edc434e436f92025-02-03T01:20:09ZengWileyInternational Journal of Aerospace Engineering1687-59742022-01-01202210.1155/2022/5191568Prescribed Performance Guidance Law with Multiple ConstraintsXu Li0Jikun Ye1Chijun Zhou2Xiao Tang3Air and Missile Defense CollegeAir and Missile Defense CollegeAir and Missile Defense CollegeAir and Missile Defense CollegeIn the terminal guidance phase of intercepting aerial target, a guidance law, satisfying impact angle constraint, acceleration constraint, and second-order dynamic characteristic of interceptor autopilot, is designed based on the prescribed performance control and dynamic surface control method. Firstly, a two-dimensional plane interception model considering the dynamic characteristics of autopilot and input constraints is established. Furthermore, for the nonconstrained system, based on the dynamic surface control, the prescribed performance reaching law is used to ensure that the line-of-sight angle and the line-of-sight angle rate can converge to the prescribed range in finite time. At the same time, an adaptive law is used to estimate the uncertainty caused by target maneuver and autopilot. Then, aiming at the acceleration constraint, an auxiliary system is established to convert the restricted system into a nonrestricted system. The finite-time convergence of the terminal line-of-sight tracking error, the line-of-sight rate, and the uniform ultimate boundedness of the system are rigorously proved by Lyapunov stability theory. Finally, the simulation results show that the proposed guidance law can make the interceptor have better interception performance when attacking targets with different maneuvering forms.http://dx.doi.org/10.1155/2022/5191568 |
| spellingShingle | Xu Li Jikun Ye Chijun Zhou Xiao Tang Prescribed Performance Guidance Law with Multiple Constraints International Journal of Aerospace Engineering |
| title | Prescribed Performance Guidance Law with Multiple Constraints |
| title_full | Prescribed Performance Guidance Law with Multiple Constraints |
| title_fullStr | Prescribed Performance Guidance Law with Multiple Constraints |
| title_full_unstemmed | Prescribed Performance Guidance Law with Multiple Constraints |
| title_short | Prescribed Performance Guidance Law with Multiple Constraints |
| title_sort | prescribed performance guidance law with multiple constraints |
| url | http://dx.doi.org/10.1155/2022/5191568 |
| work_keys_str_mv | AT xuli prescribedperformanceguidancelawwithmultipleconstraints AT jikunye prescribedperformanceguidancelawwithmultipleconstraints AT chijunzhou prescribedperformanceguidancelawwithmultipleconstraints AT xiaotang prescribedperformanceguidancelawwithmultipleconstraints |