Solutions of true proportional navigation for maneuvering and nonmaneuvering targets

Yuan, Pin-Jar; Chern, Jeng-Shing

doi:10.2514/3.20828

Cited by 90 publications

(38 citation statements)

References 7 publications

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“…Proportional navigation and its variants have been widely used as homing guidance laws because they are highly efficient and easy for implementation [1][2][3]. The PN guidance law can achieve the required precision to intercept a non-maneuvering target or a weakly maneuvering target.…”

Section: Introductionmentioning

confidence: 99%

Guidance Law Design Based on Finite Time Convergence

Yang¹,

Chen²,

Liu³

et al. 2015

2015 International Conference on Computer Science and Mechanical Automation (CSMA)

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Traditional guidance laws are designed based on Lyapunov theorem. They will guide the line of sight (LOS) angular rate to converge to zero when time approaches infinity. In this paper, guidance laws with finite time convergence are proposed in terms of finite time stability theory of nonlinear control systems. It is proved that the LOS angular rate will converge to zero before the final guidance ends with the designed guidance laws. Simulation results show that the guidance laws are highly effective.

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Section: Introductionmentioning

confidence: 99%

Guidance Law Design Based on Finite Time Convergence

Yang¹,

Chen²,

Liu³

et al. 2015

2015 International Conference on Computer Science and Mechanical Automation (CSMA)

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“…Traditional proportional navigation guidance (PNG) law and its variants such as augmented Page 2 of 21 A c c e p t e d M a n u s c r i p t 2 proportional navigation guidance (APNG), biased proportional navigation guidance (BPNG), true proportional navigation guidance (TPN), generalized TPN have been widely used in the last few decades due to their efficiency and less information demand [1][2][3][4][5].…”

Section: Introductionmentioning

confidence: 99%

Sliding mode based impact angle guidance law considering actuator fault

Lin

2015

Optik

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“…In the traditional true proportional navigation (TPN), the commanded acceleration is applied in a direction normal to the LOS, and its magnitude is proportional to the LOS rate [3]. In the modified TPN, the commanded acceleration is applied in the normal direction of LOS and its magnitude is proportional to the product of LOS rate and closing speed between pursuer and evader [4]. Generalized proportional navigation (GPN) and ideal proportional navigation (IPN), in which the commanded acceleration is applied in a direction with a fixed bias angle to the normal direction of LOS and normal to the relative velocity between pursuer and evader, respectively, were presented recently [5,6].…”

Section: Introductionmentioning

confidence: 99%

<title>Pursuer guidance parameter identification and time-to-go estimation using angle-only measurements from an evader</title>

Lin¹,

Kirubarajan

Bar‐Shalom³

2003

SPIE Proceedings

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In this paper we present an algorithm for identifying the parameters of a proportional navigation guidance missile (pursuer) pursuing an airborne target (evader) using angle-only measurements from the latter. This is done for the purpose of classifying the missile so that appropriate countermeasures can be taken. In the literature, there have been numerous studies on how a pursuer tracks an evader and what the optimal guidance law should be. However, not much has been done on identifying/classifying the pursuer from the evader's point of view using angle-only measurements. This provides the motivation for our current work. Mathematical models are constructed for a pursuer with a changing velocity, i.e., a direction change and a speed change. Assuming the pursuer is launched from the ground with an acceleration, its motion can be described by a four-dimensional parameter vector consisting of its proportional navigation constant and three parameters related to thrusting (initial net specific thrust, the relative mass ejection rate and its maximum speed). Consequently, the problem can be solved as a parameter estimation problem, rather than state estimation. In this paper, we provide an estimator based on Maximum Likelihood (ML) to solve this identification problem. The parameter estimates obtained can be mapped into the time-to-go until intercept, thus the time-to-go estimate can also be obtained from the above estimator. Estimation results are presented for different scenarios together with the Cramer-Rao Lower Bound, which quantifies the best achievable estimation accuracy. The accuracy of the time-to-go estimate is also obtained. Simulation results demonstrate that the proposed estimator is efficient by meeting the CRLB.

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Solutions of true proportional navigation for maneuvering and nonmaneuvering targets

Cited by 90 publications

References 7 publications

Guidance Law Design Based on Finite Time Convergence

Guidance Law Design Based on Finite Time Convergence

Sliding mode based impact angle guidance law considering actuator fault

<title>Pursuer guidance parameter identification and time-to-go estimation using angle-only measurements from an evader</title>

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