Missile autopilot design and analysis based on backstepping

Fan, Junfang; Su, Zhong; Zhen-xuan, Cheng

doi:10.1109/isscaa.2010.5634040

Cited by 2 publications

(1 citation statement)

References 4 publications

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“…(10) allows the application of a backstepping approach. However, the traditional backstepping approach cannot be applied because it needs the model simplifications mentioned in the preceding section [11,23]. Thus, we propose to use block dynamic surface control, thereby keeping the advantage of having the uncertainty with a smaller amplitude; hence, less control action is demanded and a more robust control system is obtained.…”

Section: Control Strategymentioning

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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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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Section: Control Strategymentioning

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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Design of missile autopilot using backstepping controller

Pal

Kumar

2014

International Conference on Electronics, Communication and Instrumentation (ICECI)

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Autopilot's main objective is to track the desired response optimally, by considering the constraints of model. It should have faster response with overshoot within the specified limit, as well as it should have minimum steady state error for the better performance of guidance. As missile dynamics is highly nonlinear in nature, thus nonlinear controller is preferred. Nonlinear controller like dynamic inversion (DI) is used extensively due to its simplicity. However, this controller is slow, because of the use of integrator for the removal of steady state error. In this paper backstepping controller is used with different choice of lyapunov function to track the pitch dynamics of missile. Using backstepping controller with proper choice of lyapunov function makes the autopilot faster.

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Missile autopilot design and analysis based on backstepping

Cited by 2 publications

References 4 publications

Block Dynamic Surface Control Applied to a Sea-Skimming Missile

Block Dynamic Surface Control Applied to a Sea-Skimming Missile

Design of missile autopilot using backstepping controller

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