Abstract
An adaptive fuzzy mixed H2 / H∞ lateral control of nonlinear missile systems with uncertain disturbances considered is proposed to achieve H2 quadratic tracking with H∞disturbance rejection. This approach can be applied to control the lateral directional dynamics of the missiles at high angle of attack or generate moments on missile operating in flight regimes where the effectiveness of conventional aerodynamic surfaces is reduced. Using an adaptive fuzzy approximation method, the uncertain nonlinear model of the missile system is estimated. Then, by a mixed H2 / H∞ control design, the effects of external disturbance and fuzzy approximation error as well as consumed energy of the controller is minimized. By the skew symmetric property of the missile system and adequate choice of state variable transformation, this problem can be reduced to solve two algebraic Riccati-like equations. Furthermore, a closed-form solution to these two algebraic equations can be obtained with very simple form for the preceding control design. This work was supported by National Science Council, Taiwan, R.O . C., under grant NSC 91-2213-E-007-014.
| Original language | English |
|---|---|
| Pages | 512-516 |
| Number of pages | 5 |
| Publication status | Published - 2003 Jul 11 |
| Event | The IEEE International conference on Fuzzy Systems - St. Louis, MO, United States Duration: 2003 May 25 → 2003 May 28 |
Other
| Other | The IEEE International conference on Fuzzy Systems |
|---|---|
| Country | United States |
| City | St. Louis, MO |
| Period | 03-05-25 → 03-05-28 |
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All Science Journal Classification (ASJC) codes
- Software
- Theoretical Computer Science
- Artificial Intelligence
- Applied Mathematics
Cite this
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Adaptive fuzzy mixed H2 / H∞ lateral control of nonlinear missile systems. / Chen, Yung-Yu; Chen, Bor Sen; Tseng, Chung Shi.
2003. 512-516 Paper presented at The IEEE International conference on Fuzzy Systems, St. Louis, MO, United States.Research output: Contribution to conference › Paper
TY - CONF
T1 - Adaptive fuzzy mixed H2 / H∞ lateral control of nonlinear missile systems
AU - Chen, Yung-Yu
AU - Chen, Bor Sen
AU - Tseng, Chung Shi
PY - 2003/7/11
Y1 - 2003/7/11
N2 - An adaptive fuzzy mixed H2 / H∞ lateral control of nonlinear missile systems with uncertain disturbances considered is proposed to achieve H2 quadratic tracking with H∞disturbance rejection. This approach can be applied to control the lateral directional dynamics of the missiles at high angle of attack or generate moments on missile operating in flight regimes where the effectiveness of conventional aerodynamic surfaces is reduced. Using an adaptive fuzzy approximation method, the uncertain nonlinear model of the missile system is estimated. Then, by a mixed H2 / H∞ control design, the effects of external disturbance and fuzzy approximation error as well as consumed energy of the controller is minimized. By the skew symmetric property of the missile system and adequate choice of state variable transformation, this problem can be reduced to solve two algebraic Riccati-like equations. Furthermore, a closed-form solution to these two algebraic equations can be obtained with very simple form for the preceding control design. This work was supported by National Science Council, Taiwan, R.O . C., under grant NSC 91-2213-E-007-014.
AB - An adaptive fuzzy mixed H2 / H∞ lateral control of nonlinear missile systems with uncertain disturbances considered is proposed to achieve H2 quadratic tracking with H∞disturbance rejection. This approach can be applied to control the lateral directional dynamics of the missiles at high angle of attack or generate moments on missile operating in flight regimes where the effectiveness of conventional aerodynamic surfaces is reduced. Using an adaptive fuzzy approximation method, the uncertain nonlinear model of the missile system is estimated. Then, by a mixed H2 / H∞ control design, the effects of external disturbance and fuzzy approximation error as well as consumed energy of the controller is minimized. By the skew symmetric property of the missile system and adequate choice of state variable transformation, this problem can be reduced to solve two algebraic Riccati-like equations. Furthermore, a closed-form solution to these two algebraic equations can be obtained with very simple form for the preceding control design. This work was supported by National Science Council, Taiwan, R.O . C., under grant NSC 91-2213-E-007-014.
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M3 - Paper
AN - SCOPUS:0038537485
SP - 512
EP - 516
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