Nonlinear <i><scp>H</scp></i><sub>2</sub> Lateral Control Design of Missiles

Chen, Yung-Yue

doi:10.1002/asjc.680

Cited by 3 publications

(3 citation statements)

References 15 publications

(26 reference statements)

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“…25 Nonlinear H2 Lateral Control Design of Missiles [44] In this work, authors have developed a nonlinear H2 lateral control law which has successfully helped in increasing the manoeuvrability for the later control of nonlinear missile systems.…”

Section: The H ∞ Controller Designmentioning

confidence: 99%

Comparative Account of Robust H∞ Techniques for Missile Autopilot Design

Sastry¹,

Ray²,

Rao³

et al. 2019

IJIGSP

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H∞ control techniques are prominently used as solutions for flight control problems. From the literature, a variety of techniques is reported in the last three decades with specific merits and demerits, which, when applied to multiple flight control scenarios, showing trade off in terms of performance and robustness. However, all these methods possess superior performance when compared with that of classical approaches. In this paper an attempt is made to provide an insight into the requirements and criticalities in the design of missile autopilot. This paper introduces some of the significant H∞ control techniques like H∞ mixed sensitivity, H∞ loop shaping and μ synthesis, with specific emphasis on analysis of autopilot design. A comparative account of modern control methods is presented on the basis of system performance and robustness, which will be helpful in the selection of the appropriate design method for specific application.

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Section: The H ∞ Controller Designmentioning

confidence: 99%

Comparative Account of Robust H∞ Techniques for Missile Autopilot Design

Sastry¹,

Ray²,

Rao³

et al. 2019

IJIGSP

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“…Considering the posture tracking error dynamics in equation (24), and giving some weighting matrices V ¼ V T > 0 and W ¼ W T > 0, the cost function of this posture tracking problem can be described as 21 follows…”

Section: I Design Objectivementioning

confidence: 99%

“…The analytical solution u Ã 2 of equations ( 22) and (25) can be found from Pðe 2 ; tÞ which satisfies the following timevarying Riccati-like equation 21 _ Pðe 2 ; tÞ þ Pðe 2 ; tÞDðe 2 ; tÞ þ D T ðe 2 ; tÞPðe 2 ; tÞ þ V À Pðe 2 ; tÞEðe 2 ; tÞW À1 E T ðe 2 ; tÞPðe 2 ; tÞ ¼ 0 with Pðe 2 ; tÞ ¼ Pðe 2 ; tÞ T ! 0 (27)…”

Section: Design Objectiveunclassified

Nonlinear hybrid control design of three-joint dual finger robots

Chen

Chang

Chen

et al. 2017

International Journal of Advanced Robotic Systems

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The difficulty of finger robot grasping control designs is the inevitable coupling in the dynamics of finger joints and finger tips because this dynamics coupling effect lets the overall motion of the finger robots to be constrained by the object states when they are controlled to manipulate an object's postures. Besides, from the practical implementation point of view, a stable and easy-to-implement control structure is also an important task for this topic. For solving these two design issues, an optimal hybrid control design which combines feedback linearization and nonlinear H 2 control concepts for grasping design of three-joint dual finger robots is investigated in this study. This investigation makes two main contributions to the finger robot grasping control design: (1) an effective and acceptable control performance for finger robot grasping control designs under the effect of dynamics coupling is delivered and (2) a really simple nonlinear optimal control scheme is obtained.

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Missile attitude control—A direct parametric approach

Duan

2014

Proceedings of the 33rd Chinese Control Conference

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In this paper, the dynamical model in a matrix second-order nonlinear form with respect to the three Euler angles is firstly established for the attitude system of a rigid missile, which is complete in the sense that no simplification via approximation is taken. It is revealed that this general model is a fully-actuated one without any further assumption. Then, with the help of a recently proposed general parametric design approach for general fully-actuated second-order nonlinear systems, a direct parametric approach for missile attitude control via proportional plus derivative feedback is proposed, which gives a complete parametrization of the pair of feedback gains, and allows usage of the established complete model but not a simplified one. The approach possesses two important features. Firstly, with the proposed controller parametrization, missile attitude systems, though highly nonlinear, can be turned into a constant linear system with desire eigenstructure. Secondly, in such a design there are still degrees of freedom which may be further utilized to improve the system performance. An example is considered to demonstrate the use of the proposed approach. ω z ω x sin γand then substituting the conversion relationship (5a) into (9) to eliminate ω x , ω y , ω z , and simplifying the result, producing the following equation:For the yaw channel, substituting the third equation in (3) into (7) to eliminateω z , we can easily obtainFurther, substituting conversion relationship (5a) into (11), givesThen substituting (5a) into (13), yields the following:

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Nonlinear H₂ Lateral Control Design of Missiles

Cited by 3 publications

References 15 publications

Comparative Account of Robust H∞ Techniques for Missile Autopilot Design

Comparative Account of Robust H∞ Techniques for Missile Autopilot Design

Nonlinear hybrid control design of three-joint dual finger robots

Missile attitude control—A direct parametric approach

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