Non-singular terminal sliding mode guidance and control with terminal angle constraints for non-maneuvering targets

Kumar, Shashi Ranjan; Rao, Sachit; Ghose, Debasish

doi:10.1109/vss.2012.6163517

Cited by 35 publications

(30 citation statements)

References 14 publications

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“…Remark 9: If K 1 > 1∕4, K 2 > 0, 0 < ϱ 1 < 1, andΔ max t 0 > 0 with t 0 the initial time, then s 1 goes to zero asymptotically under the control (21). Moreover, in this case, the bound of uncertainty Δ max , namely, V max λ , V max r , A max Tr , A max Tλ , and _ A max Tλ mentioned in Assumptions 1 and 2 may be unknown.…”

Section: A Outer Loopmentioning

confidence: 99%

“…Based on the finite time stability theory and the variable structure control theory, a finite time convergent sliding-mode guidance law with terminal impact angle constraint was presented in [20]. Kumar et al [21] proposed guidance laws to intercept stationary and constant velocity targets at a desired impact angle, based on nonsingular terminal sliding-mode control theory. However, only guidance laws, namely, interceptor accelerations, were designed in [20,21]; autopilot design was not involved.…”

Section: Introductionmentioning

confidence: 99%

“…Kumar et al [21] proposed guidance laws to intercept stationary and constant velocity targets at a desired impact angle, based on nonsingular terminal sliding-mode control theory. However, only guidance laws, namely, interceptor accelerations, were designed in [20,21]; autopilot design was not involved.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

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: A Outer Loopmentioning

confidence: 99%

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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“…In Ref. [21], the authors designed a new sliding mode based impact angle guidance law for non-maneuvering targets based on the nonsingular terminal sliding mode (NTSM) control. However, none of them considers the actuator fault, which is a practical problem when implementing.…”

Section: Introductionmentioning

confidence: 99%

Sliding mode based impact angle guidance law considering actuator fault

Lin

2015

Optik

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“…Using backstepping control theory, Kim et al (2007) proposed an impact angle guidance law, which only needs the information of line-of-sight (LOS) angular rate, estimated time-to-go and desired impact angle. Kumar et al (2012a) studied a novel non-singular sliding mode control (SMC)-based impact angle guidance law for non-manoeuvring targets. An all-aspect guidance and control scheme with impact angle constraint is presented by Kumar et al (2012b).…”

Section: Introductionmentioning

confidence: 99%

A robust impact angle constraint guidance law with seeker’s field-of-view limit

Lin

2014

Transactions of the Institute of Measurement and Control

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In this paper, a new robust guidance law is designed to satisfy both impact angle constraint and the seeker's field-of-view limit for missiles with strapdown seekers. Since the impact angle guidance law needs a highly curved trajectory and most strapdown seekers have a very narrow field-of-view, maintaining the seeker's lock-on is the key issue for these missiles. To address this problem, a switching logic is adopted, which adds an additional term in the original guidance law when the look angle exceeds the pre-designed boundary value to maintain the seeker's lock-on. An impact angle guidance law is designed based on terminal sliding mode control theory and the finite time convergence characteristic of the line-of-sight angle, as well as its derivative is proved through the Lyapunov method. Numerical simulations are performed to validate the effectiveness of the proposed guidance law. Some intuitive tunings of the design parameters are also offered in the simulation results to achieve large impact angles.

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Non-singular terminal sliding mode guidance and control with terminal angle constraints for non-maneuvering targets

Cited by 35 publications

References 14 publications

Partial Integrated Guidance and Control with Impact Angle Constraints

Partial Integrated Guidance and Control with Impact Angle Constraints

Sliding mode based impact angle guidance law considering actuator fault

A robust impact angle constraint guidance law with seeker’s field-of-view limit

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