Analytic Solutions of Generalized Impact-Angle-Control Guidance Law for First-Order Lag System

Lee, Yong-In; Kim, Seunghwan; Lee, Jin-Ik; Tahk, Min-Jea

doi:10.2514/1.57454

Cited by 53 publications

(38 citation statements)

References 8 publications

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“…Therefore, if one can represent a n using the given boundary conditions (18), it is straightforward to calculate L n . Substituting (19) for the boundary conditions (18) yields…”

Section: Solution To the Tasgl Design Problemmentioning

confidence: 99%

“…Unfortunately, the missile cannot be regarded as a lag-free system because it contains various subsystems such as actuators, sensors, and aerodynamics. In many cases, the missile dynamic lags results in the divergence of terminal missile acceleration even when the flight path angle is controlled [17,18]. It means that the flight path angle does not coincide with the impact angle of interest anymore when the missile dynamic lags are not ignorable.…”

Section: Introductionmentioning

confidence: 99%

“…18), z f = 0 means the zero miss-distance, (1) 0 f z = means that the flight path angle of a missile, γ m,f , should be controlled to zero. The additional terminal acceleration constraints intended for maintaining the angle-of-attack as zero.…”

mentioning

confidence: 99%

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Terminal acceleration stabilizing guidance law for impact angle constrained interception of a non-maneuvering target

Moon

Jung

2015

Int. J. Control Autom. Syst.

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A practical homing guidance scheme is newly proposed in order to meet the impact angle and terminal acceleration constraints, simultaneously. Provided that the homing guidance loop is modeled as a linear time-varying differential equation by approximating the missile dynamics as a firstorder system, its closed-form solution is expressed as a linear combination of hypergeometric functions. It implies that the instability of the homing guidance loop is mainly due to the missile dynamic lags and, furthermore, the non-diverging homing trajectory could be obtained by introducing the additional biased acceleration command as a rational function of time-to-go. These inspirational observations motivate us to formulate an impact angle control problem as designing an appropriate biased term which generates a non-diverging time-to-go polynomial homing trajectory for given terminal constraints. The resultant guidance command has a similar form used in conventional guidance laws but its feedback gains vary with time-to-go. This similarity means that, during the flight, the proposed guidance law adaptively embraces existing guidance laws derived by intentionally ignoring the effect of missile dynamic lags. Through the numerical simulations, the performance of the proposed guidance scheme is evaluated.

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“…Therefore, if one can represent a n using the given boundary conditions (18), it is straightforward to calculate L n . Substituting (19) for the boundary conditions (18) yields…”

Section: Solution To the Tasgl Design Problemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Terminal acceleration stabilizing guidance law for impact angle constrained interception of a non-maneuvering target

Moon

Jung

2015

Int. J. Control Autom. Syst.

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“…Let      be the estimation error, for the error dynamic system (11), if the NTSM surface is as (12), the control law is designed as (13) subject to the updating law (14), then  is ultimately uniformly bounded and the states of system (11) converge to zero in finite time.…”

Section: Guidance Law Designmentioning

confidence: 99%

“…(15) gives (12) and the control law is designed as (13), subject to the adaptive law (14), then the states of system (11) converge to zero in finite time.…”

Section: Guidance Law Designmentioning

confidence: 99%

Adaptive nonsingular sliding mode based guidance law with terminal angular constraint

He¹,

Lin²

2014

International Journal of Aeronautical and Space Sciences

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In this paper, a new adaptive nonsingular terminal sliding mode control theory based impact angle guidance law for intercepting maneuvering targets was documented. In the design procedure, a new adaptive law for target acceleration bound estimation was presented, which allowed the proposed guidance law to be used without the requirement of the information on the target maneuvering profiles. With the aid of Lyapunov stability criteria, the finite-time convergent characteristics of the line-of-sight angle and its derivative were proven in theory. Numerical simulations were also performed under various conditions to demonstrate the effectiveness of the proposed guidance law.

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Adaptive backstepping impact angle control with autopilot dynamics and acceleration saturation consideration

Wang

2017

Intl J Robust & Nonlinear

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Summary This paper presents a robust impact angle constraint guidance law for maneuvering target interception in the presence of autopilot dynamics and input saturation. The presented guidance law is designed on the basis of a combination of adaptive backstepping control technique and higher‐order sliding mode differentiator. Different from existing impact angle constraint guidance law using sliding mode control, the line‐of‐sight angular rate and impact angle tracking error are regulated by two different virtual control laws. Because the future course of action of the target, an independent entity, cannot be predicted beforehand, adaptive laws are introduced in guidance law derivation for disturbance rejection. Unlike dynamic surface control approach, higher‐order sliding mode differentiator is adopted here as an alternative way to obtain the derivatives of the virtual control laws, thus leading to the exact tracking performance of backstepping control. Detailed stability analysis shows that both the line‐of‐sight angular rate and impact angle error can be stabilized in a small region around zero asymptotically. Simulation results explicitly show that accurate interception is achieved with a wide range of impact angles. Copyright © 2017 John Wiley & Sons, Ltd.

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Analytic Solutions of Generalized Impact-Angle-Control Guidance Law for First-Order Lag System

Cited by 53 publications

References 8 publications

Terminal acceleration stabilizing guidance law for impact angle constrained interception of a non-maneuvering target

Terminal acceleration stabilizing guidance law for impact angle constrained interception of a non-maneuvering target

Adaptive nonsingular sliding mode based guidance law with terminal angular constraint

Adaptive backstepping impact angle control with autopilot dynamics and acceleration saturation consideration

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