Biased PN based impact angle constrained guidance using a nonlinear engagement model

G, Akhil; Ghose, Debasish

doi:10.1109/acc.2012.6315574

Cited by 20 publications

(13 citation statements)

References 18 publications

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“…(15) Note that the form of b(t) introduced for terminal acceleration stabilization is a natural consequence of Remark 1 and 2. Inserting (15) into (5) and applying changes of variables in (8), the TASGL homing trajectory becomes the solution to the third-order differential equation.…”

Section: Problem Statementmentioning

confidence: 98%

“…Problem 1: For the homing guidance loop described by the differential (16), the design problem of TASGL is to find the coefficient L n for the biased acceleration command in (15). Moreover, it produces the nondivergent time-to-go polynomial trajectory (17) satisfying the following boundary conditions.…”

Section: Problem Statementmentioning

confidence: 99%

“…The biased term can be easily determined using the closed-form BPN solution derived under the assumption that the missile dynamic lags are negligible [14][15][16]. The BPN based method could be a viable solution for field engineers because it is easy to implement for its simple structure and, moreover, does not require acceleration feedbacks.…”

Section: Introductionmentioning

confidence: 99%

“…On the other hand, the BPN based method incorporates an intentional bias term with the PN guidance command to meet the impact angle requirement [11][12][13][14][15][16].…”

Section: Introductionmentioning

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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Section: Problem Statementmentioning

confidence: 98%

Section: Problem Statementmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

“…On the other hand, the BPN based method incorporates an intentional bias term with the PN guidance command to meet the impact angle requirement [11][12][13][14][15][16].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

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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“…In their works, they used small angle approximation, resulting in narrow launch envelops and very restricted capture region. To improve this method, Akhil and Ghose [15] designed a guidance law which was capable of achieving a wide range of impact angle constraint. They put forward a modified angle constraint biased PNG, where the required bias term is derived in a closed form consider-ing non-linear equations.…”

Section: Introductionmentioning

confidence: 99%

Finite time convergent wavelet neural network sliding mode control guidance law with impact angle constraint

Zhang

Han

et al. 2015

Int. J. Autom. Comput.

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This paper presents a novel guidance law to intercept non-maneuvering targets with impact angle and lateral acceleration command constraints. Firstly, we formulate the impact angle control to track the desired line-of-sight (LOS) angle, which is achieved by selecting the missile s lateral acceleration to enforce the sliding mode on a sliding surface at impact time. Secondly, we use the Lyapunov stability theory to prove the stability and finite time convergence of the proposed nonlinear sliding surface. Thirdly, we introduce the wavelet neural network (WNN) to adaptively update the additional control command and reduce the high-frequency chattering of sliding mode control (SMC). The proposed guidance law, denoted WNNSMC guidance law with impact angle constraint, combines the SMC methodology with WNN to improve the robustness and reduce the chattering of the system. Finally, numerical simulations are performed to demonstrate the validity and effectiveness of the WNNSMC guidance law.

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On-line optimization design of sliding mode guidance law with multiple constraints

Zhang

Wang

Tao

et al. 2013

Applied Mathematical Modelling

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Biased PN based impact angle constrained guidance using a nonlinear engagement model

Cited by 20 publications

References 18 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

Finite time convergent wavelet neural network sliding mode control guidance law with impact angle constraint

On-line optimization design of sliding mode guidance law with multiple constraints

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