Capturability of a Geometric Guidance Law in Relative Velocity Space

Dhananjay, N.; Ghose, Debasish; Bhat, M. Seetharama

doi:10.1109/tcst.2008.924561

Cited by 19 publications

(7 citation statements)

References 13 publications

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“…The planar DGGL is with the same direction of the commanded acceleration of two-dimensional (2D) PPN. 19,20,29,30,32 Li et al 31 proposed a 3D gainvarying guidance algorithm (GGA) using the concept of planar DGGL, whose direction of commanded acceleration was actually the same as that of 3D PPN, while the relationship of equation (13) was satisfied for a nonmaneuvering target. In fact, Li et al's 3D geometric guidance algorithm (equation 25in Li et al 31 ) can be interpreted as…”

Section: Relative Kinematicsmentioning

confidence: 99%

“…Li et al 31 later advanced a 3D gain-varying guidance algorithm (GGA) by using the concept of planar DGGL and the principle of 3D PPN, and the post-launch capture condition of this guidance algorithm was analyzed. Dhananjay et al 32 investigated the capturability of the planar DGGL and pointed out that the planar DGGL was similar to augmented PPN with a timevarying navigation gain and the target maneuvering term. In short, it can be intuitively concluded that, when the target maneuvering term is cleared from the guidance command for the consideration of realization, Chiou and Kuo's planar DGGL becomes planar PPN with a time-varying navigation gain, while the 3D DGGL can be taken as a different 3D geometric guidance law with the PN concept.…”

Section: Introductionmentioning

confidence: 99%

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Performance analysis of differential geometric guidance law against high-speed target with arbitrarily maneuvering acceleration

Chen

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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The interception of high-speed target with an arbitrary maneuvering acceleration causes serious troubles to the guidance and control system design of airborne missile. A novel guidance law based on the classical differential geometry curve theory was proposed not long ago. Although it is believed and numerically demonstrated that this differential geometric guidance law (DGGL) is superior to the classical pure proportional navigation (PPN) in intercepting high-speed targets, its performance has not been thoroughly analyzed. In this paper, using the Lyapunov-like approach, the performance of DGGL against the high-speed target with an arbitrary but upper-bounded maneuvering acceleration is well studied. The upper bounds of the LOS rate and commanded acceleration of DGGL are obtained, and conditions that guarantee the capture of this type of maneuvering target are also presented. The nonlinear relative dynamics between the missile and target is taken into full account. Finally, the proposed theoretical findings are demonstrated by numerical simulation examples.

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Section: Relative Kinematicsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Performance analysis of differential geometric guidance law against high-speed target with arbitrarily maneuvering acceleration

Chen

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Conventional proportional navigation systems have been improved with time-variable filtering, and the design process has been enhanced with automatic computer approaches. Several studied have been taken in the past to investigate, evaluate, and improve the proportional navigation problem [1,[8][9][10][11][12]. With online Kalman estimation for filtering noisy radar data and optimal control gains, the guidance systems have been developed in performances.…”

Section: Introductionmentioning

confidence: 99%

An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance

Nguyen¹,

Nguyen²

2020

AJAE

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The guidance laws are commonly designed to yield as small a miss distance as possible, harmonious with the missile's acceleration capability. In recent decades, the concept of optimized guidance law is well understood in applications where information concerning the target range and line-of-sight angle is available. Researchers' efforts have been continually made to apply modern control theory to conventional and adaptive autopilot designs, even though the classical theory is still applicable to autopilots. It can be noted that it is desirable to perform a detailed computer-aided feasibility study within the context of a realistic missile-target engagement model. Development and evaluation of guidance and control laws for simplified missile-target engagement scenarios are extended and adapted to the air-to-air missile situation and implemented in a complete three-dimensional engagement model. Thus, this study proposed a computational method for constructing an optimal midcourse guidance law, which is based on the optimal control theory and initial boundary conditions. This proposed guidance law is derived from an optimal control theory with the boundary conditions such as allowed relative distance between missile and target at the final time, low line-of-sight rate. A numerical simulation verifies the performance of this guidance law with the impact of harmonic wind. The simulation results demonstrate that the quality of effectiveness as well as the applicability of this proposed algorithm.

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“…Li et al [9] later advanced a 3D gain-varying guidance algorithm by combining the concepts of 3D DGGL and 3D PPN. Dhananjay et al [10] investigated the capturability of the planar DGGL. Ye et al [11] proposed a nonlinear DGGL based on nonlinear control theory to handle the influence caused by the target maneuvering acceleration.…”

Section: Introductionmentioning

confidence: 99%

“…The planar DGGL is similar to PPN with a varying [10]. For 3D DGGL, both the expression in the arc-length system proposed by Chiou et al [3] and the expression in the time domain given by Li et al [6] were not intuitive and convenient enough for performance analysis and application to practical interception scenarios.…”

Section: Introductionmentioning

confidence: 99%

Performance analysis of three-dimensional differential geometric guidance law against low-speed maneuvering targets

Chen

2018

Astrodyn

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The performance of the three-dimensional differential geometric guidance law with proportional navigation formation against a target maneuvering arbitrarily with time-varying normal acceleration is thoroughly analyzed using the Lyapunov-like approach. The validation of this guidance law is firstly proved, and then the performance issues such as capturability, heading error control efficiency, line of sight rate convergence, and commanded acceleration requirement are analyzed, under the condition that the missile is initially flying toward the target with a speed advantage. It is proved that an intercept can occur and the line of sight rate and missile commanded acceleration can be limited in certain ranges, if the initial heading error is small and the navigation gain is sufficiently large. The nonlinear relative dynamics between the missile and the target is taken into full account, and the analysis process is simple and intuitive, due to the use of a convenient line of sight rotating coordinate system. Finally, the new theoretical findings are validated by numerical simulations.

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Capturability of a Geometric Guidance Law in Relative Velocity Space

Cited by 19 publications

References 13 publications

Performance analysis of differential geometric guidance law against high-speed target with arbitrarily maneuvering acceleration

Performance analysis of differential geometric guidance law against high-speed target with arbitrarily maneuvering acceleration

An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance

Performance analysis of three-dimensional differential geometric guidance law against low-speed maneuvering targets

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