Optimization of three-loop missile autopilot gain under crossover frequency constraint

Abdelatif, Mohamed; Longjun, Qian; Bo, Yuming

doi:10.1016/j.dt.2015.08.006

Cited by 10 publications

(9 citation statements)

References 8 publications

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“…The ISE is chosen as the command tracking performance index of the autopilot with the consideration of obtaining its analytical expression [14]. Referring to (3), with partial fraction expansion, the unit step response is expressed as…”

Section: A Design Objectivementioning

confidence: 99%

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Optimal Design for Three-loop Autopilot Using Multi-Constraint Optimization

Abdelatif¹,

Longjun²

2017

JOACE

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One challenging control problem is that of modern tactical missile systems in pursuit of achieving large scale of maneuverability and sufficient stability. The optimal autopilot for practical systems should provide the fastest possible performance under constraints on applicable system dynamics. The quadratic performance index with weightings adjustment cannot easily and clearly handle such constraints. This paper introduces an optimal autopilot design technique based on the constrained optimization. The tracking performance is formed analytically as the design objective. The open-loop crossover frequency and the maximum demand of the actuator fin-deflection rate are introduced as analytical inequality constraints. The design process is handled into the space of stable poles parameters of the autopilot closed loop characteristic. The introduced autopilot design is self-consistent technique and is easily fulfilled with an optimization algorithm. Numerical simulation results are illustrated to demonstrate the effectiveness and feasibility of the proposed approach.  Index Terms-three loop autopilot, optimal gain design, crossover frequency constraint, control effort constraint

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Section: A Design Objectivementioning

confidence: 99%

“…(20) is solved to minimize the objective function (10) within the validation of the constraint functions Eq. (14) and Eq. (19).…”

Section: Numirical Analysismentioning

confidence: 99%

Optimal Design for Three-loop Autopilot Using Multi-Constraint Optimization

Abdelatif¹,

Longjun²

2017

JOACE

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“…Moreover, since the proposed autopilot was based on the nonlinear control methodology, the autopilot can automatically adjust the control gains according to the changes of flight operating conditions. In addition, the physical meaning of control commands can be analyzed intuitively using the error equation, proposed in [14], since the apparent structure of the proposed autopilot can be rearranged in the same way as the well-known three-loop control structure [1], [14]- [19].…”

Section: Introductionmentioning

confidence: 99%

Nonlinear Autopilot Design for Endo- and Exoatmospheric Interceptor With Thrust Vector Control

Hong

Lee

2020

IEEE Trans. Aerosp. Electron. Syst.

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This paper proposes an autopilot design for an interceptor with Thrust-Vector-Control (TVC) that operates in the endo-and exo-atmospheric regions. The main objective of the proposed autopilot design is to ensure control performance in both atmospheric regions, without changing the control mechanism. In this paper, the characteristics of the aerodynamic forces in both atmospheric regions are first investigated to examine the issue of the conventional control mechanism at various altitudes. And then, a control mechanism, which can be applied to both atmospheric regions, is determined based on the analysis results. An autopilot design is then followed by utilizing the control mechanism and the feedback linearization control (FBLC) method. Accordingly, the proposed autopilot does not rely on changing the control mechanism depending on flight condition unlike the conventional approach as well as it can adjust the control gains automatically according to the changes of flight operating conditions. In this paper, the robustness of the proposed autopilot is investigated through the tracking error analysis and the relative stability analysis in the presence of model uncertainties. The physical meaning of the proposed autopilot is also presented by comparing to the well-known three-loop control structure. Finally, numerical simulations are performed to show the performance of the proposed method.

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“…As expected, the function fmincon of the MATLAB Optimization Toolbox can solve such kind of smooth objective optimization problem well effectively with feasible initial design parameters. Moreover, it converges to the same minimum point even starting from different initial guesses [9]. In this line of thought, the optimal autopilot gain K is easily calculated by substituting the optimum parameters  , …”

Section: Constrained Optimizationmentioning

confidence: 99%

“…The autopilot design using constraint optimization methods is introduced in [7], [8]. These methods are considered for specified controller structure with totally numerical procedure.The main objective of this work is the formulation of an optimal control technique that achieves the optimum of the performance objective within direct constraints upon the robustness requirements and system limits in such a way that the design solution is automatically obtained without the requirement for weighting parameters [9]. In addition, this formulation allows a direct incorporation of the design requirements that cannot be handled easily using the quadratic performance index such as shaping of loop frequency responses.…”

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confidence: 99%

Constrained-Optimal Based Loop-Shaping State Feedback Approach for Missile Autopilot Design

Abdelatif¹,

Longjun²,

Bo³

2016

IJMO

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Abstract-Modern tactical missile systems are required to achieve high maneuverability and sufficient stability. As a result, the flight control design of a missile system is a creative process as it considers both performance requirements and performance limitations, which are inherently conflicting. Different modern control techniques handle such conflicting demands through the adjustment of cost weighting parameters between system internal states and control signals. The adjustment processes might need trials to tune the system performance to certain level at different operating conditions. This paper involves in the formulation of an optimal design approach that achieves the required level of robustness related to open-loop design requirements and system dynamic limits while minimizing the tracking error between the reference input and the system output. The proposed approach is based on a constrained optimization technique where the design parameters are automatically adjusted to the optimum tradeoff between the overall system performance and robustness. The effectiveness and feasibility of the proposed approach are demonstrated through a numerical example for the three-loop autopilot design.Index Terms-Optimal-robust state feedback, constraint optimization, frequency domain constraint, control effort constraint. I. INTRODUCTIONThe modern techniques such as H∞, μ-synthesis [1], optimal LQG [2] and dynamic inversion [3] are the most popular in the design of autopilot systems for several decades. While these techniques offering powerful design tools, they also suffer from certain shortcomings when put to practice. For example, these methods solve the tradeoff between design performance and robustness requirements indirectly by using weighting parameters on the internal states and the control signal of the system. Since the relation between these weightings and the resultant performance is not so clear, the selection and adjustment of these weightings and some other design parameters might be repeated at different operating conditions to meet the design requirements. Moreover, the autopilots obtained with these techniques are mostly of high order, which is may be difficult to implement.In general, the system achieves better in terms of time performance criteria as more as the tracking error minimized. However, the free minimization of tracking error may cause too high autopilot gain with an undesired frequency response. Consequently, the optimal control method should provide the Manuscript received April 10, 2016; revised June 10, 2016. The authors are with School of Automation, University of Science and Technology, Nanjing 210094, China (e-mail: mdyosf2010@yahoo.com, qlongjun@mail.njust.edu.cn, byming@mail.njust.edu.cn).optimum of the tracking performance combined with a direct incorporation of the frequency-domain criteria values and actuator limits to achieve a satisfactory robustness level. In the same sense, the minimum error between the desired and the actual open-loop crossover frequency is formed as an ...

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Optimization of three-loop missile autopilot gain under crossover frequency constraint

Cited by 10 publications

References 8 publications

Optimal Design for Three-loop Autopilot Using Multi-Constraint Optimization

Optimal Design for Three-loop Autopilot Using Multi-Constraint Optimization

Nonlinear Autopilot Design for Endo- and Exoatmospheric Interceptor With Thrust Vector Control

Constrained-Optimal Based Loop-Shaping State Feedback Approach for Missile Autopilot Design

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