Implementation of a neural network state estimator-based autopilot for skid-to-turn missiles

Song, Ye‐Qiong; Koh, Giok; Hwang, Sungcheul

doi:10.2514/6.1997-3768

Cited by 3 publications

(8 citation statements)

References 7 publications

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“…The missile system described by (2) with the state observers (4) and (8), where the observer gains , , and satisfy (5), (6), and (9), and the observer-based control law in (11) combined with the compensator in (13) under Assumptions 2.1 through 2.6, 4.1, and 4.2 is stable in the sense that is uniformly ultimately bounded as where is a monotonically increasing function of , , , satisfying , which implies that also decreases to zero when the modeling errors , , the estimation error of bank angle , and decrease to zero. Proof: We first prove that converges to zero asymptotically and then boundedness of ; from this, will be shown to be bounded by the monotonically increasing function .…”

Section: Theorem 41 (Observer-based Control Law)mentioning

confidence: 99%

“…In [5], the autopilot design is based on the simplified aerodynamic model shown in [8]. The estimates for bank angle and total angle of attack, which are obtained from commanded accelerations, are used instead of actual ones.…”

Section: Introductionmentioning

confidence: 99%

“…Just as in the control law, the observer becomes effective only at each flight condition given in the aerodynamic look-up table. In [5]- [7], the influence of the estimation error is not considered in the design of the control law, nor is the stability of the overall control system analyzed.…”

Section: Introductionmentioning

confidence: 99%

“…Al- Manuscript though the estimates can be easily obtained in this manner, such values obviously overlook actual acceleration tracking errors. In [6], a state observer design method is proposed using functional approximation via a neural network. This method is applied to nonlinear missile dynamics valid for all flight conditions, but yields the observer with complex structures demanding large memory and processing time.…”

Section: Introductionmentioning

confidence: 99%

“…There have been many studies done on the state estimation of wind angles [5]- [7], but in actuality, it is quite difficult to estimate wind angles accurately due to the nonlinear aerodynamics and dynamics. In [5], the autopilot design is based on the simplified aerodynamic model shown in [8].…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

Observer-Based Control for Tail-Controlled Skid-to-Turn Missiles Using a Parametric Affine Model

Chwa

Choi

2004

IEEE Trans. Contr. Syst. Technol.

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This brief paper presents an observer-based control approach for the acceleration control of tail-controlled skid-to-turn (STT) missiles. The proposed approach provides a solution to overcoming the drawbacks of existing nonlinear missile controllers that it is needed to know the values of wind angles (angle of attack and sideslip angle). A nonlinear observer for wind angles is designed using a parametric affine missile model developed by the authors, where the coupling term between the lateral and longitudinal motion is also considered. Using the wind angle estimate, we can design the observer-based controller to show the desired acceleration tracking performance. The performance and stability of the resulting overall missile system are analyzed by taking into account the effects of the wind angle estimator. Simulation results are also included to show that the proposed approach provides satisfactory performance for missile dynamics.Index Terms-Nonlinear observer, observer-based control, parametric affine missile model, wind angles.

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Section: Theorem 41 (Observer-based Control Law)mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%