Target Maneuver Adaptive Guidance Law for a Bounded Acceleration Missile

Atir, Ronen; Hexner, G.; Weiss, Haim; Shima, Tal

doi:10.2514/6.2009-6089

Cited by 3 publications

(4 citation statements)

References 18 publications

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“…In addition to the guidance law, various guidance filter designs have been reported. For example, the modified pseudomeasurement filter [25], unscented Kalman filter [26], two-step optimal filter [27], multimodel filter [28], and nonlinear filter [29] have been studied.…”

Section: Introductionmentioning

confidence: 99%

Biased PNG for target observability enhancement against nonmaneuvering targets

Lee¹,

Tahk

2015

IEEE Trans. Aerosp. Electron. Syst.

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This paper proposes a biased proportional navigation guidance (BPNG) law providing enhanced target observability for passive homing missile systems against a nonmaneuvering target. After examining the line-of-sight (LOS) rate equation, which is an important parameter of target observability and which reveals that the LOS rate is proportional to the rate of cross-range deviation, a bias term of BPNG is formulated using the rate of cross-range deviation to generate an additional LOS rate. The closed-form trajectory solution of the proposed guidance law is derived, and its capturability and characteristics are then investigated. Using numerical simulations, the performance of the proposed guidance law is determined in conjunction with a target state estimator.

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Section: Introductionmentioning

confidence: 99%

Biased PNG for target observability enhancement against nonmaneuvering targets

Lee¹,

Tahk

2015

IEEE Trans. Aerosp. Electron. Syst.

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“…(6), subject to Assumption 1, and the sliding surface Eq. (10). If the control law is selected as Eq.…”

Section: Basic Guidance Law Designmentioning

confidence: 99%

“…Shkolnikov et al 9) applied the second-order sliding mode observer to estimate the target maneuver and augmented it with PNG law to obtain a robust, augmented PNG (APNG) law. To intercept a target performing sudden step maneuvers, Atir et al 10) studied a multiple-model adaptive guidance law for missiles with bounded acceleration command. In Ref.…”

Section: Introductionmentioning

confidence: 99%

Continuous Robust Guidance Law for Intercepting Maneuvering Targets

Lin

2015

Trans. Japan Soc. Aero. S Sci.

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This paper documents a new guidance law for tactical missiles to intercept maneuvering targets. By incorporating linear and fractional power nonlinear terms, a faster convergent and chatter-free acceleration command is derived. With the aid of Lyapunov stability criteria, we prove that the line-of-sight angular rate can converge to a small region around the origin in finite time. Since the target maneuver cannot be obtained or measured in real applications, a nonlinear finite time convergence disturbance observer for target maneuver estimation is introduced and a composite guidance law with finite time convergence is presented to improve the overall performance. Theoretical analysis and numerical simulations demonstrate the effectiveness of the proposed method.

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“…Assuming a suitable dynamics model, several estimation algorithms have been designed and inserted in the guidance and homing loops as target state and maneuver estimating building blocks, such as Gauss-Markov processes, extended Kalman filter (EKF), multiple-model methods, and artificial intelligence observers [10][11][12][13][14][15][16][17][18][19][20]. To describe real-world scenarios, most of these observers continuously update a linearization around the current state estimate, use a large number of filters, or represent the target maneuver as a white noise process, which could be inappropriate in the case of abrupt target maneuvers or in the presence of measurement noises [21,22].…”

mentioning

confidence: 99%

Arbitrary-Order Sliding-Mode-Based Homing-Missile Guidance for Intercepting Highly Maneuverable Targets

Kada

2014

Journal of Guidance, Control, and Dynamics

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This paper investigates the development and implementation of a new homing-missile guidance system for intercepting highly maneuverable targets using arbitrary features of the homogeneous high-order sliding-mode controllers and observers. The concept of this guidance system involves artificially increasing the orders of controllers and observers to enhance accuracy and robustness of future interceptors. Two advanced guidance laws, that is, augmented proportional navigation law and direct collision or hit-to-kill law, are considered to construct acceleration-based and velocity-based attractive sliding manifolds, respectively; and high-order robust exact differentiators are used to compute high-order time derivatives of these manifolds. Real-time estimation of target maneuver from measurements using these differentiators is also considered. The resulting guidance laws are implemented in computer simulation using nonlinear interceptor dynamics and engagement kinematics. The results prove that the guidance system achieves high-level performance and successfully meets direct collision guidance requirements. In addition, this system shows good adaptability and strong robustness to target evasive maneuvers, parameter uncertainties, and measurement noises.

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Target Maneuver Adaptive Guidance Law for a Bounded Acceleration Missile

Cited by 3 publications

References 18 publications

Biased PNG for target observability enhancement against nonmaneuvering targets

Biased PNG for target observability enhancement against nonmaneuvering targets

Continuous Robust Guidance Law for Intercepting Maneuvering Targets

Arbitrary-Order Sliding-Mode-Based Homing-Missile Guidance for Intercepting Highly Maneuverable Targets

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