Geometric approach to capture analysis of PN guidance law

Li, Chaoyong; Jing, Wuxing

doi:10.1016/j.ast.2007.04.007

Cited by 21 publications

(11 citation statements)

References 24 publications

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“…When the flight altitude is 7500 m, the bomb enters the diving attack phase. As proportional guidance law is fit for practical use, we use it to guide the bomb to the target [9].…”

Section: Three-axis Turntablementioning

confidence: 99%

Design and Realization of a Hardware-in-the-Loop Simulation System for Aerial Guided Bombs

Wang

Qi³

2008

2008 2nd International Symposium on Systems and Control in Aerospace and Astronautics

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Hardware-in-the-Ioop (HIL) simulation is a costeffective technology for the design and evaluation of the aerial bomb's guidance and control system. In this paper, a feasible formula for aerial bomb's guidance and control system ground testing is presented. The structure and working process of the HIL simulation system are discussed in detail. The trajectory design method of the aerial guided bomb is proposed. The relative guidance and control law are also presented in this paper.

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“…When the flight altitude is 7500 m, the bomb enters the diving attack phase. As proportional guidance law is fit for practical use, we use it to guide the bomb to the target [9].…”

Section: Three-axis Turntablementioning

confidence: 99%

Design and Realization of a Hardware-in-the-Loop Simulation System for Aerial Guided Bombs

Wang

Qi³

2008

2008 2nd International Symposium on Systems and Control in Aerospace and Astronautics

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“…However, at the end of interception, the proportional guidance method is prone to overload saturation caused by the divergence of the line of sight rate, which leads to full deflection of the actuator. A number of researchers have improved this guidance method by adjusting the proportion coefficient and compensating for the acceleration of the target, which greatly improves guidance performance [6,7,8]. Considering that the trajectories of interceptors and targets are both curves when they are engaged in space, and that differential geometry theory is just the classical mathematical theory for studying curves and surfaces, research on interceptor trajectories by using differential geometry theory provides a new perspective for guidance law design [9][10][11][12].…”

Section: Introductionmentioning

confidence: 99%

Research on a Differential Geometric Guidance Law Based on Fractional-Order Theory

Tang

2020

IEEE Access

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In this paper, fractional-order calculus theory is used to investigate the geometric law for intercepting an agile target. In order to overcome the challenges presented by the divergence of line of sight rate (LOSR) of proportional navigation (PN), the fractional LOSR is used as a compensated term in the proposed fractional differential geometric guidance law (FDGGL). By adjusting the navigation gain of the FDGGL, the new proposed guidance law can be transformed into the traditional differential geometric guidance law (DGGL) and PN. The average overload and ballistic stability of the FDGGL are analyzed based on the fractional and control theory. Some analytical results about energy consumption and trajectory variation of the FDGGL were obtained. The simulation results shows that, compared with PN and DGGL, the FDGGL has better guidance performance when intercepting different maneuvering targets. INDEX TERMS missile guidance; differential geometric ; fractional; relative motion; command.

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“…It provides the missile acceleration command to the autopilot and guides the missile to fly to the target. As the most popular guidance law, the proportional navigation (PN) was proposed in the 1950s and is widely used because of its ease of implementation and high efficiency (Li and Jing, 2008), etc. In pure proportional navigation (PPN), the missile acceleration command is normal to the velocity of the missile in direction, and is proportional to the angular rate of the line-of-sight (LOS) between the missile and the target in magnitude (Becker, 1990; Guelman, 1971).…”

Section: Introductionmentioning

confidence: 99%

Two composite guidance laws based on the backstepping control and disturbance observers with autopilot lag

Man

Zhang²,

2019

Transactions of the Institute of Measurement and Control

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A composite three-dimensional (3D) missile guidance law is proposed for manoeuvering targets with the consideration of the first-order autopilot dynamics without any linearization. This guidance law consists of a backstepping controller and a feedforward compensation based on disturbance observers. In this control scheme, the unknown target acceleration is regarded as part of the lumped disturbance, estimated by a disturbance observer, and then feedforward compensated. The backstepping controller is introduced to deal with unmatched disturbances. Moreover, both the nonlinear disturbance observer (NDOB) and the generalized proportional integral observer (GPIO) are employed in the derivation. Simulation studies demonstrate the effectiveness of the proposed guidance law, and compare the guidance performance of the two composite guidance laws with different disturbance observers.

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Geometric approach to capture analysis of PN guidance law

Cited by 21 publications

References 24 publications

Design and Realization of a Hardware-in-the-Loop Simulation System for Aerial Guided Bombs

Design and Realization of a Hardware-in-the-Loop Simulation System for Aerial Guided Bombs

Research on a Differential Geometric Guidance Law Based on Fractional-Order Theory

Two composite guidance laws based on the backstepping control and disturbance observers with autopilot lag

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