Modified Pure Proportional Navigation Guidance Law for Impact Time Control

Cho, Namhoon; Kim, Youdan

doi:10.2514/1.g001618

Cited by 157 publications

(50 citation statements)

References 30 publications

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“…The classical PNG generates the commanded acceleration of the interceptor in proportion to the turning rate of LOS. In a 3D scenario, PNG is defined in a vector format as [26] a PNG = NΩ L × V (7) where N > 0 denotes the navigation gain. The notations Ω L and V represent the LOS angular rate and missile velocity vectors, respectively.…”

Section: A Impact Time Prediction In Three-dimensional Engagementmentioning

confidence: 99%

Three-Dimensional Optimal Impact Time Guidance for Antiship Missiles

Lin

2019

Journal of Guidance, Control, and Dynamics

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Section: A Impact Time Prediction In Three-dimensional Engagementmentioning

confidence: 99%

Three-Dimensional Optimal Impact Time Guidance for Antiship Missiles

Lin

2019

Journal of Guidance, Control, and Dynamics

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“…To this purpose, we introduce the accurate timeto-go estimation formula in the framework of PNG expressed by the incomplete beta function. This accurate time-to-go formula, as presented in [5], is called the exact solution to the time-to-go of PNG.…”

Section: Effect Of Time-to-go Estimation On the Proposed Itcgmentioning

confidence: 99%

“…Moreover [1], a number of ITCG laws presented in the current research literature [2][3][4][5][6][7][8][9][10][11][12][13][14][15][16][17] are also dependent on the time-to-go estimation, although they may be designed based on different theories or techniques. For instance, the studies presented in [1][2][3][4][5][6][7][8][9][10] were performed in terms of the principle of PNG, among which several widely used formulas for estimating the time-to-go are also derived in the framework of PNG. A sliding-mode-based ITCG law was derived in [11] with a simple time-to-go estimate that uses the range divided by the closing speed.…”

Section: Introductionmentioning

confidence: 99%

Nonsingular PNG-Based Impact Time Control Guidance with Lower Dependence on Time-to-Go Estimate

Chang

Chen

2019

International Journal of Aerospace Engineering

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In a bid to take advantage of natural characteristics of the proportional navigation guidance (PNG) in practical engineering, the PNG-based impact time control guidance (ITCG) continues to be a popular alternative for achieving the desired impact time of a missile. For most such ITCG, the performance is dependent on the accuracy of the time-to-go estimation. Along the lines of the development of PNG-based ITCG in earlier studies, a nonsingular ITCG is proposed on the basis of nonlinear formulations. It is demonstrated that, by theoretical analysis and numerical simulation, this proposed ITCG is shown to be advantageous in certain circumstances. By deriving a novel additional acceleration command, the proposed law is of lower dependence on time-to-go estimate and is capable of eliminating some singularities, leading to wider adjustable range of the desired impact time and better adaptability to more conditions. This research is expected to be supplementary to those presented in the current research literature.

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“…In recent years, the problem of multiple low-speed attackers simultaneously attacking a high-speed moving target has become a research hot spot in [1], [2], [3], [4], [5]. With the research of multi-agent consistency control methods in [6], [7], [8], [9], [10], the guidance law design of multi-attackers simultaneously attacking a moving target emerges in endlessly, but it is too theoretical to consider practical problems, such as internal collision of attackers before attacking a target in [11], and multi-attackers can satisfy the optimal cost function, but the trajectory is too curved to apply to the actual situation. Even though the design of the attackers' guidance laws can make the relative motion states of the attacker-target consistent, it can not guarantee accurate attack.…”

Section: Introductionmentioning

confidence: 99%

Design of distributed guidance laws for multiple unmanned aerial vehicles cooperative attack of a moving target based on reducing surrounding area

Wei

Yang

Fan

2020

Transactions of the Institute of Measurement and Control

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In this paper, two cooperative guidance laws based on two-point boundary value are designed to deal with the problem of cooperative encirclement and simultaneous attack under condition of both known target acceleration and unknown target acceleration. The only requirement for the multi-attacker communication network is that it contains a directed spanning tree. The guidance laws can function properly as long as at least one attacker can observed the target. The acceleration components along the attacker-target line of sight in the novel guidance laws can reduce the relative remaining distance between each of the attackers and the target at the same speed, thus completing simultaneous attack and avoiding the calculation of the remaining time. The components of the guidance laws perpendicular to the attacker-target line of sight can make the normal overload of relative motion zero, so that the trajectory will be smooth and the collision problem within the attacker can be avoided. Simulation results verified the practicability of the novel guidance laws.

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Modified Pure Proportional Navigation Guidance Law for Impact Time Control

Cited by 157 publications

References 30 publications

Three-Dimensional Optimal Impact Time Guidance for Antiship Missiles

Three-Dimensional Optimal Impact Time Guidance for Antiship Missiles

Nonsingular PNG-Based Impact Time Control Guidance with Lower Dependence on Time-to-Go Estimate

Design of distributed guidance laws for multiple unmanned aerial vehicles cooperative attack of a moving target based on reducing surrounding area

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