Geometric analysis of flight control command for tactical missile guidance

Kuo, Chen-Yuan; Soetanto, D.; Chiou, Ying-Chwan

doi:10.1109/87.911375

Cited by 62 publications

(41 citation statements)

References 11 publications

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“…In this section, based on the assumption that N > 1, which is different from previous studies, [11][12][13] a new necessary initial condition is developed to guarantee capture of the high-speed target and the DG guidance commands are well defined over the guidance envelope (i.e., the time period during the homing guidance phase). Moreover, an assumption of constant speed is made for both the missile and target to simplify this guidance problem.…”

Section: Initial Conditionsmentioning

confidence: 99%

“…Adler 10) introduced 3D PPN guidance law first in terms of the geodesic and normal curvatures of the missile's path on the surface generated by the LOS. Chiou and Kuo [11][12][13] proposed DG guidance commands for missile guidance problems using the Frenet formulas, 14) while Jing and Li 15,16) examined their applications. Ariff presented a novel DG guidance algorithm using the information of the involute of the target's trajectory.…”

Section: Introductionmentioning

confidence: 99%

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Analysis of 3D Geometric Guidance Problem

Jing

2008

Trans. Japan Soc. Aero. S Sci.

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Section: Initial Conditionsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Analysis of 3D Geometric Guidance Problem

Jing

2008

Trans. Japan Soc. Aero. S Sci.

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“…[4][5][6] With this restriction, the guidance command statement is not practical because the arc length cannot be measured by onboard sensors. In this section, the DG guidance system is presented in the time domain using classical DG theory.…”

Section: Differential Geometric Guidance and Control Systemmentioning

confidence: 99%

“…3) Notable work on DG guidance problems has been done by Chiou and Kuo. [4][5][6] In their papers, the Frenet formula…”

Section: Introductionmentioning

confidence: 99%

A Novel Approach to the 2D Differential Geometric Guidance Problem

Jing

Qi³

et al. 2007

Trans. Japan Soc. Aero. S Sci.

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This paper presents a detailed study of the two-dimensional (2D) differential geometric (DG) guidance problem, as well as its iterative solution and initial conditions. The DG guidance curvature command is transformed from an arc length system to the time domain using the classical DG theory. Subsequently, an algorithm for commanded angleof-attack is developed to formulate the DG guidance system, whose iterative solution is established based on Newton's iterative algorithm. Moreover, a flight control system is presented using the classical PID controller so as to form the DG guidance and control system. Finally, a new necessary initial condition is deduced to guarantee the capture of a high-speed target. Simulation results demonstrate that Newton's iterative algorithm works well and accurately in DG guidance problems and the proposed DG guidance law exhibits similar performance to the proportional navigation guidance (PNG) law in the case of intercepting a non-maneuvering target. However, the proposed method performs better than PNG in the case of intercepting a maneuvering target.

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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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Geometric analysis of flight control command for tactical missile guidance

Cited by 62 publications

References 11 publications

Analysis of 3D Geometric Guidance Problem

Analysis of 3D Geometric Guidance Problem

A Novel Approach to the 2D Differential Geometric Guidance Problem

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

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