Gain-Varying Guidance Algorithm using Differential Geometric Guidance Command

Li, Chaoyong; Jing, Wuxing; Wang, Hui; Qi, Zhiguo

doi:10.1109/taes.2010.5461652

Cited by 23 publications

(18 citation statements)

References 22 publications

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“…The original expression of 3D DGGL was described in the arc-length system which was quite complex. Li et al [6,9] transformed it into the time domain, without attenuation of the complexity. Li et al [15][16][17][18] proposed the simplified explicit expression of 3D DGGL in the time domain recently, viz.,…”

Section: Preliminarymentioning

confidence: 99%

“…It is easy to find out that Chiou and Kuo [3] designed a mθ with the formation of the augmented proportional navigation (APN). Li et al [6,9] used PN with varying navigation gain [25] to design a mθ . In this paper, we also adopt the concept of PN, viz.,…”

Section: Preliminarymentioning

confidence: 99%

“…Newtons iterative algorithm and fuzzy PID controller were used to obtain the angle of attack (AOA) and angle of sideslip (AOS) commands [7,8]. 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.…”

Section: Introductionmentioning

confidence: 99%

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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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Section: Preliminarymentioning

confidence: 99%

Section: Preliminarymentioning

confidence: 99%

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

Chen

2018

Astrodyn

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“…C.Y. Li, et al [3][4][5] translated the DGGC of the arc-length system into the time domain, and studied scenarios of DGGC interception of a tactical ballistic missile, as well as the initial capture condition of the case. K.B.…”

Section: Introductionmentioning

confidence: 99%

Intelligent guidance method based on differential geometric guidance command and fuzzy self-adaptive guidance law

Zhang

Long

2015

IFS

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Abstract. Differential geometric guidance command (DGGC) is widely acknowledged as a better method of endoatmospheric interception than three-dimensional (3D) pure proportional navigation (PPN). DGGC can be regarded as an intelligent method due to its sophisticated sense of Lyapunov. However, traditional DGGC cannot guarantee line of sight (LOS) finite time convergence (FTC) to zero against maneuvering targets, particularly in regard to a stable, robust trajectory, which effectively lowers the overall intelligence of the method. This study proposes employment of the fuzzy self-adaptive guidance law to estimate target acceleration and enhance guidance intelligence, which in turn enhances the intelligence of the traditional DGGC method, making it more adaptive and applicable to practical interception scenarios. Finally, the effectiveness of this newly-proposed guidance method is demonstrated by numerical simulation.

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“…Among the most well known classical laws for missile guidance is proportional navigation (PN) which itself has many variants 7,12,13,14 . In its basic form, PN requires measurements based on relative line-of-sight (LOS) between the missile and target and attempts to orient the missile velocity vector in order drive the LOS angular rate to zero.…”

Section: Introductionmentioning

confidence: 99%

A New Parameterized Guidance Law for Cooperative Air Defense

Snyder

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

Self Cite

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In this paper, a new cooperative guidance scheme is proposed capable of driving n number of missiles to impact time consensus in the presence of a time varying and or switching communication topology. Cooperative stability is preserved under this paradigm as well. In addition, the proposed scheme yields target intercept trajectories through a parameterization process which are optimal in the sense that trajectory separation from the missile/target relative line-of-sight is minimized.speed of th i missile x V = range velocity i ω = angular speed of th i missile ( ) k t S = time varying communication matrix z = parameterized trajectory 0 z = parameterized trajectory inital condition T z = parameterized trajectory terminal position u = control inputs b = parameterized trajectory coefficients C = steering control coefficients σ = inertial speed projection angle on line-of-sight λ = line-of-sight angle

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Gain-Varying Guidance Algorithm using Differential Geometric Guidance Command

Cited by 23 publications

References 22 publications

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

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

Intelligent guidance method based on differential geometric guidance command and fuzzy self-adaptive guidance law

A New Parameterized Guidance Law for Cooperative Air Defense

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