A new look at classical versus modern homing missile guidance

Nesline, F.; Zarchan, Paul

doi:10.2514/6.1979-1727

Cited by 37 publications

(36 citation statements)

References 2 publications

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“…From the control law (8) handling two-dimensional dynamics (7), it is reasonable to extend the form similar to (8) for the 3-D dynamics (4). Thus, the completely new control law, a form similar to in (8), is constructed mixed with some tunable parameters as follows …”

Section: Robust Guidance Law Under Unpredictable Target Acceleration W=0mentioning

confidence: 99%

“…Babu et al [7] proposed the guidance law against highly maneuvering targets using the sliding surface of the zero LOS rate based on the Lyapunov method. Brierly and Longchamp [8] presented the sliding mode guidance law including rigid-body dynamics and actuator time delay. Moon et al [9] studied the sliding-mode missile guidance law via variable structure control.…”

Section: Design Of Three-dimensional Missile Guidance Law Via Slidingmentioning

confidence: 99%

“…Thus, the completely new control law, a form similar to in (8), is constructed mixed with some tunable parameters as follows …”

Section: Robust Guidance Law Under Unpredictable Target Acceleration W=0mentioning

confidence: 99%

See 2 more Smart Citations

Design of Three-Dimensional Missile Guidance Law via Sliding Mode with Saturation Constraint

Torabi¹,

Ahari²

2013

J Electr Electron Syst

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IntroductionThe missile guidance is a well-known nonlinear control engineering area of research. Since the basic principles were extensively covered The variable structure control law has been applied to many guidance Recently, Chen et al.[10] derived a new nonlinear fuzzy H ∞ guidance law with a saturation of actuators against maneuvering targets. They first approximated the nonlinear missile target pursuit dynamics with the Takagi -Sugeno linear fuzzy models. Then, based on this, they constructed a H ∞ control to handle the approximation error and external disturbances. However, it is a known fact that the approximation error between the fuzzy model and the true one is difficult to obtain exactly [11].In this paper, sliding mode guidance law based on the threedimensional (3-D) nonlinear engagement kinematics is proposed. The purpose of the proposed control design is to attenuate the influence of the target's maneuvers on the performance of the guidance law. That is to say that the proposed guidance is not only robust with respect to target maneuvering, but is also guaranteed state boundedness (Lyapunov stability). Statement of the ProblemFor a 3-D interception, relative motion between the missile and target is described by the spherical coordinates system (r , θ, Φ) with the origin fixed on the location of the missile.The 3-D missile -target engagement is shown in Figure 1, where a missile is attempting to intercept a moving target.The missile and target are assumed to be point masses in order to AbstractThe three-dimensional missile guidance law with saturating actuator is proposed for the pursuit of an unpredictably maneuvering target. The proposed guidance law achieves a satisfactorily robust performance without having to solve a complicated nonlinear Hamilton-Jacobi Partial Differential Inequality (HJPDI). In the proposed guidance scheme, the nonlinear part of the relative motion equations between the missile and target is first cancelled. Then, a tunable sliding mode law is designed to eliminate the effect of external disturbance. The proposed guidance law can achieve reduced interception time than others, yet it is considerably simpler. An example is proposed to confirm it.

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Section: Robust Guidance Law Under Unpredictable Target Acceleration W=0mentioning

confidence: 99%

Section: Design Of Three-dimensional Missile Guidance Law Via Slidingmentioning

confidence: 99%

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Design of Three-Dimensional Missile Guidance Law via Sliding Mode with Saturation Constraint

Torabi¹,

Ahari²

2013

J Electr Electron Syst

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“…In (Rusnak, 2004) a one sided linear quadratic optimization problem was solved and applied to missile terminal guidance. Previous to (Rusnak, 2004) it had been known that modern guidance laws were sensitive to errors in terminal time, (Nesline and Zarchan, 1981). A modern guidance law with reduced sensitivity to uncertainty in terminal time was suggested in (BenAsher and Yaesh, 1998).…”

Section: Introductionmentioning

confidence: 99%

Differential Games With Uncertain Terminal Time

Rusnak

Hexner

Weiss

2005

IFAC Proceedings Volumes

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Linear Quadratic Differential games have been used to model economic and other conflict situations. A salient feature of these analyses was that the interval of play was fixed (possibly inifinite), and known to both players. This paper introduces a linear quadratic differential game where only the probability density of the terminal time is known to the two players. The paper's results are used to derive a differential game based guidance law for uncertain time of intercept.

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“…Proportional navigation guidance (PNG) law and its variants have been widely used for tactical missiles in the past few decades due to their efficient and easy implementation [1][2][3]. For non-maneuverable or weakly maneuverable targets, the classical PNG law is proven to be optimal for minimization of both the miss distance and energy consumption [4].…”

Section: Introductionmentioning

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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A new look at classical versus modern homing missile guidance

Cited by 37 publications

References 2 publications

Design of Three-Dimensional Missile Guidance Law via Sliding Mode with Saturation Constraint

Design of Three-Dimensional Missile Guidance Law via Sliding Mode with Saturation Constraint

Differential Games With Uncertain Terminal Time

Adaptive nonsingular sliding mode based guidance law with terminal angular constraint

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