Integrated backstepping design of missile guidance and control with robust disturbance observer

Hwang, Tae-Won; Tahk, Min-Jea

doi:10.1109/sice.2006.314847

Cited by 36 publications

(31 citation statements)

References 2 publications

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“…Then the proposed control law (9) is also continuous and chattering is avoided. Remark 3: Different from some literature [22,44], in which an accurate observer is needed to evaluate the uncertainties, and some literature [10,11,37], in which the bounds of uncertainties and disturbances are required to construct controllers, prior knowledge of uncertainties and disturbances is not necessary in Theorem 1. It is only required that the uncertainties and disturbances are bounded, but the bounds may be unknown.…”

Section: Novel Sliding-mode Control Lawsmentioning

confidence: 99%

“…It can eliminate the time lag existing inevitably in the conventional missile guidance and control design, which separates the guidance loop from the control loop; moreover, IGC can exploit fully the synergistic relationships between the separating subsystems. Up until now, various control methods for homing missiles have been incorporated with IGC, for example, backstepping [22], the θ-D method [23], subspace stabilization [24], linear optimal control theory [25], feedback linearization [26], game theory [27], the state-dependent Riccati equation [28], and slidingmode control [29][30][31][32]. To the best knowledge of the authors, few attempts are made on IGC design for missiles with terminal impact angle constraints.…”

Section: Introductionmentioning

confidence: 99%

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Partial Integrated Guidance and Control with Impact Angle Constraints

Wang

2015

Journal of Guidance, Control, and Dynamics

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Novel sliding-mode control laws are proposed in this paper to stabilize a class of uncertain nonlinear systems. Considering that the sign function, which is often used in the sliding-mode control can cause chattering of control input, the saturation function is used to take its place in proposed controllers. What is more, not only the proposed controllers are continuous but also convergence to the origin asymptotically and in finite time can both be guaranteed in theory. For asymptotic convergence, it is only required that uncertainties and disturbances are bounded and the bounds may be unknown by virtue of adaptive laws. The obtained results are then applied to partial integrated guidance and control design for a missile, completing desired terminal impact angle and hit-to-kill interception. Finally, simulations are conducted on the nonlinear longitudinal missile model and results demonstrate the effectiveness of the proposed method. Nomenclature A Tr , A Tλ= projections of target acceleration along and orthogonal to the line of sight, m∕s 2 c x , c z , c m = aerodynamic coefficients F x , F z = aerodynamic forces, N g = gravity acceleration, m∕s 2 I yy = moment of inertia around the pitch axis, kg∕m 2 k F , k M = constants determined by the missile geometry, m 2 and m 3 , respectively M = pitching moment, N · m M m = Mach number m = missile mass, kg n L = missile normal acceleration, m∕s 2 q = pitch rate, rad∕s r = the range along the line of sight, m V M = missile velocity, m∕s V r , V λ = components of relative velocity along and orthogonal to the line of sight, m∕s α = angle of attack, rad γ M = missile flight-path angle, rad δ e = elevator deflection, rad θ = pitch angle, rad λ = line-of-sight angle, rad ρ = atmospheric density, kg∕m 3

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Section: Novel Sliding-mode Control Lawsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Partial Integrated Guidance and Control with Impact Angle Constraints

Wang

2015

Journal of Guidance, Control, and Dynamics

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“…Therefore, it has been applied to the design of missile's guidance and control systems. [32][33][34][35][36] An adaptive, integrated guidance, and control approach for ballistic missile interceptors is presented in Sharma and Richards 32 using backstepping control techniques. An integrated design of guidance and control using backstepping control with disturbance observer are studied in Hwang and Tahk 33 and the stability of integrated backstepping guidance and control logic is proven by Lyapunov sense.…”

Section: Introductionmentioning

confidence: 99%

“…36 Most above designs and analyses are made for the planar guidance. 32,33,35,36 Although in Jung and Kim 34 the guidance laws with impact angle or impact time are proposed for the three-dimensional guidance, there is not a rigorous analysis for the convergence of LOS rates in the paper. In this paper, based on the backstepping method and our nonlinear Lyapunov function, we rigorously design three-dimensional guidance laws accounting for the autopilot lag.…”

Section: Introductionmentioning

confidence: 99%

A generalized design method for three-dimensional guidance laws

Zhou

Teo

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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The true proportional navigation guidance law, the augmented proportional navigation guidance law, or the adaptive sliding-mode guidance law, is designed based on the planar target-to-missile relative motion dynamics. By a proper construction of a nonlinear Lyapunov function for the line-of-sight angular rates in the three-dimensional guidance dynamics, it is shown that the three guidance laws mentioned above are able to ensure the asymptotic convergence of the angular rates as they are directly applied to the three-dimensional guidance environment. Furthermore, considering the missile autopilot dynamics as a first-order lag, we design three-dimensional nonlinear guidance laws by using the backstepping technique for three cases: (1) the target does not maneuver; (2) the information of target acceleration can be acquired; and (3) the target acceleration is not available but its bound is known a priori. In the first step of the backstepping design of the control law, there is no need to cancel the nonlinear coupling terms in the three-dimensional guidance dynamics in such way that the final expressions of the proposed guidance laws are significantly simplified. Thus, the proposed nonlinear Lyapunov function for the line-of-sight angular rates is a generalized function for designing three-dimensional guidance laws. Simulation results of a missile interception mission show that the proposed guidance laws are highly effective.

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“…In 1998, Corey Schumacher presented a nonlinear six-degree-of-freedom simulation of a maneuver performed with the dynamic inversion controller [2]. In 2006, Hwang designed a guidance and control incorporation algorithm of pitch channel by using backstepping design method [3].…”

Section: Introductionmentioning

confidence: 99%