Optimal Terminal Guidance with Constraints at Final Time

York, Randy J.; Pastrick, Harold L.

doi:10.2514/3.57212

Cited by 61 publications

(14 citation statements)

References 6 publications

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“…Zn addition to Al-A6, suppose the An initial geometry of pursuer and target d(psine,(O) -~in6,(0)>~ + q(ada(0>>2 < P (8) l e,(o>l < n/2 (9) for some constants p E ( 0 , lp) and q > 0. that AS. The navigation constant N is chosen such…”

Section: A7 Satisfiesmentioning

confidence: 99%

“…The target velocity and the target attitude angle are estimated by the tracking system of the pursuer. Therefore, for the implementation of (7), an active seeker and a built-in INS are required which are also necessary for the other ones addressed in [6,9,111. The cost for implementing the proposed guidance law is similar to the previous ones.…”

Section: A7 Satisfiesmentioning

confidence: 99%

“…Kim and Grider derived optimal and suboptiimal guidance laws for flight trajectories with constraint on impact attitude angle [6], which seems to be a pioneering research on this area. York and Pastrick improved Kim and Grider's by matching the guidance law to a first-order autopilot [9]. Bryson and Ho solved an optimal control problem for rendezvous [lo].…”

Section: It Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Biased PNG law for impact with angular constraint

Kim

Lee

Han

1998

IEEE Trans. Aerosp. Electron. Syst.

412

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A new homing guidance law is proposed to impact a target with a desired attitude angle. It is a variation of the conventional proportional navigation guidance (PNG) law which includes a supplementary time-varying bias. The proposed guidance law does not require a time-to-go estimation and has a simpler form. Analytic conditions for fulfilling the guidance goal are also provided. Simulation results demonstrate that the proposed guidance law has wider launch envelopes than the previous one and shows a good performance even against a maneuvering target.Relative range and range rate to target LOS angle and its rate Body attitude angle of pursuer and target Lateral and commanded accel'eration of pursuer Total velocity of pursuer and itarget Seeker gimbal angle Desired body attitude angle at the time of impact Desired LOS angle at the time of impact.

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Section: A7 Satisfiesmentioning

confidence: 99%

Section: A7 Satisfiesmentioning

confidence: 99%

Section: It Introductionmentioning

confidence: 99%

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Biased PNG law for impact with angular constraint

Kim

Lee

Han

1998

IEEE Trans. Aerosp. Electron. Syst.

412

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“…The range over range rate estimate is accurate only when the closing velocity is constant and the initial heading error is small. Improved methods for time-to-go estimation by solving a linear quadratic control problem is discussed in York and Pastrick [5]. In Tahk et al [6], a recursive time-to-go method is discussed in which the timeto-go estimates are updated recursively.…”

mentioning

confidence: 98%

Accurate Time-to-Go Estimation for Proportional Navigation Guidance

Dhananjay

Ghose

2014

Journal of Guidance, Control, and Dynamics

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“…They were further improved by York and Pastrick [6] through matching the guidance law to a firstorder autopilot. Furthermore, Song et al [7] studied an optimal guidance law (OGL) for varying velocity missiles against a maneuvering target, where the guidance law is combined with a target-tracking filter to predict the in- tercept point.…”

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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Optimal Terminal Guidance with Constraints at Final Time

Cited by 61 publications

References 6 publications

Biased PNG law for impact with angular constraint

Biased PNG law for impact with angular constraint

Accurate Time-to-Go Estimation for Proportional Navigation Guidance

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

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