Adaptive dynamic surface control for integrated missile guidance and autopilot

Hou, Ming; Duan, Guang‐Ren

doi:10.1007/s11633-010-0563-z

Cited by 51 publications

(28 citation statements)

References 16 publications

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“…Adaptive techniques based on Lyapunov methods have been applied to guarantee the stability [11]. However, these techniques adjust the gains accordingly to the input signal excitability.…”

Section: Aσmentioning

confidence: 99%

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Block Dynamic Surface Control Applied to a Sea-Skimming Missile

Coelho

Hemerly

2017

Journal of Guidance, Control, and Dynamics

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Nomenclature C Aσ= aerodynamic axial force coefficient derivative with respect to equivalent fins angle, rad −1 C lδ a = aerodynamic rolling moment coefficient derivative with respect to aileron angle, rad −1 C mδ e = aerodynamic pitch moment coefficient derivative with respect to elevator angle, rad −1 C Nδ e = aerodynamic normal force coefficient derivative with respect to elevator angle, rad −1 C nδ r = aerodynamic yaw moment coefficient derivative with respect to rudder angle, rad −1 c ref = chord of reference, m C Yδ r = aerodynamic lateral force coefficient derivative with respect to ruder angle, rad −1 F x ; F y ; F z = forces in body-axis direction, N h ref = reference height commanded, m I 0 = inertia tensor, kg ⋅ m 2 I 3×3 = 3 × 3 identity matrix M x ; M y ; M z = torque represented in body axis, N∕m m = mass, kg q = dynamic pressure, N∕m 2 S ref = reference surface, m 2 t = time, s V 0 = average velocity, m∕s v x ; v y ; v z = velocity in body-axis direction, m∕s x, y, z = Cartesian coordinates of position, m α, β = angles of attack and sideslip, rad α 0 = predicted angle of attack when in steady-state flight, rad δ a ; δ e ; δ r = aileron, elevator, and rudder equivalent angles, rad δ a 0 ; δ e 0 ; δ r 0 = predicted steady-state flight angles of aileron, elevator, and rudder, rad ϕ, θ, ψ = roll, pitch, and yaw angles, rad ω x ; ω y ; ω z = angular rate represented in body axis, rad/s

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“…Adaptive techniques based on Lyapunov methods have been applied to guarantee the stability [11]. However, these techniques adjust the gains accordingly to the input signal excitability.…”

Section: Aσmentioning

confidence: 99%

“…To deal with these difficulties, advanced approaches have been investigated, like sliding-mode control (SMC) and multiple or dynamic surface control (DSC) [11,13,14]. These methods permit us to deal with some kind of bounded uncertainties, like parameters errors or nonlinearities.…”

Section: Aσmentioning

confidence: 99%

Block Dynamic Surface Control Applied to a Sea-Skimming Missile

Coelho

Hemerly

2017

Journal of Guidance, Control, and Dynamics

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“…In the PIGC method, both the outer and inner loops were designed to preserve the philosophical benefits of both IGC and conventional separated design. In [16], an adaptive dynamic surface control algorithm was applied to the IGC of the pitch, yaw, and roll channels based on the independent design. Using the small-gain theorem, an IGC design approach was proposed to guarantee the stability of missile with respect to target maneuvers and missile model uncertainties [17].…”

Section: Introductionmentioning

confidence: 99%

Fast Robust Integrated Guidance and Control Design of Interceptors

Song

Zhang

2016

IEEE Trans. Contr. Syst. Technol.

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In this brief, a fast robust integrated guidance and control design approach, considering the 3-D interception of interceptors for hypersonic vehicles, is proposed. The proposed method is designed using the modified fast terminal sliding mode control and dynamic surface control with signal compensation. The fractional integral fast terminal sliding functions are presented independently, and all the sliding phases run parallel to increase the system response speed. Utilizing the dynamic surface control method, the robust compensation signals are constructed to eliminate the influence of uncertainty equivalents thoroughly. Therefore, the proposed approach guarantees the fast convergence of line-of-sight angular rates and the system robustness for uncertainties. The simulation results demonstrate the robustness of the proposed controller, and a variety of comparison studies are also carried out to demonstrate the advantage of the new approach.Index Terms-Dynamic surface control, fast terminal sliding mode (FTSM) control, integrated guidance and control (IGC), interceptor.

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“…In [14], a game theoretic approach was employed for the design of an integrated linear autopilot-guidance controller that minimizes the interception miss and control energy of the interceptor, under the worst case of target maneuver and worst case of measurement disturbances. In recent years, such nonlinear control theory as sliding mode control (SMC) [7,11,18], backstepping control [6] and dynamic surface control (DSC) [4,5] was employed to design the robust integrated guidance-control controller. In this paper, to consider the guidance requirement and missile's dynamic characteristics simultaneously, the concept of IGC is adopted.…”

Section: Introductionmentioning

confidence: 99%