Deviated Pure-Pursuit-Based Optimal Guidance Law for Imposing Intercept Time and Angle

Livermore, Riley A.; Shima, Tal

doi:10.2514/1.g003179

Cited by 32 publications

(12 citation statements)

References 24 publications

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“…D URING the past two decades, adaptive control for nonlinear systems has attracted considerable attention and many important control schemes have been proposed and applied to the missile guidance systems [1][2][3][4][5][6]. These methods aim to increase the destructive power, or reduce the sensitivity to the target's maneuverability, or enhance the survivability of the missile.…”

Section: Introductionmentioning

confidence: 99%

Fuzzy Observer-Based Dynamic Surface Control for Input-Saturated Nonlinear Systems and its Application to Missile Guidance

Zhang

2020

IEEE Access

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In this paper, a fuzzy observer-based tracking control scheme is proposed for a class of strict-feedback uncertain nonlinear system with input saturation. To facilitate the fuzzy logic system (FLS) design, the original uncertain nonlinear system is transformed into an output feedback system firstly. Then, an adaptive state observer is constructed. In order to efficiently tackle the input saturation, an auxiliary system (AS) is introduced. Using the estimated states and AS, the dynamic surface control (DSC) strategy is developed based on backstepping method. Under the DSC scheme, the tracking control problem is reduced to optimal regulation problem of an affine system. Subsequently, an adaptive dynamic programming (ADP) based optimal control scheme is proposed. The stability of the overall system is guaranteed by Lyapunov theory. Finally, guidance simulation is made to confirm the effectiveness of the developed control method.

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Section: Introductionmentioning

confidence: 99%

Fuzzy Observer-Based Dynamic Surface Control for Input-Saturated Nonlinear Systems and its Application to Missile Guidance

Zhang

2020

IEEE Access

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“…A specified TVSM with two coefficients is built and the impact constraints are satisfied by adjusting these coefficients. In [11], an ITACG law was developed based on optimal control theory and deviated pure pursuit. Chen and Wang [12] developed an ITACG law by adding a feedback controller to an impact angle control guidance (IACG) law based on optimal control.…”

Section: Introductionmentioning

confidence: 99%

“…Some researchers have used linear approximations [6,8,12,17] to estimate the impact time under a small heading angle assumption, which might result in performance degradation under large impact angles [12]. Second, the existing ITACG laws [5][6][7][8][9][11][12][13][14][15] cannot provide an impact time range under given initial conditions, which results in difficulties in ensuring the success of the simultaneous arrival of multiple UAVs. Finally, all the above ITACG laws [5][6][7][8][9][10][11][12][13][14][15] assume that the UAV speed is constant, while in practice, the UAV speed changes over time.…”

Section: Introductionmentioning

confidence: 99%

“…Second, the existing ITACG laws [5][6][7][8][9][11][12][13][14][15] cannot provide an impact time range under given initial conditions, which results in difficulties in ensuring the success of the simultaneous arrival of multiple UAVs. Finally, all the above ITACG laws [5][6][7][8][9][10][11][12][13][14][15] assume that the UAV speed is constant, while in practice, the UAV speed changes over time. Hence, the guidance performance may degrade greatly under variable speed.…”

Section: Introductionmentioning

confidence: 99%

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A Geometry-Based Guidance Law to Control Impact Time and Angle under Variable Speeds

2020

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To provide a feasible solution for a variable speed unmanned aerial vehicle (UAV) to home on a target with impact time and angle constraints, this paper presents a novel geometry-based guidance law composed of trajectory reshaping and tracking. A trajectory generation process using Bezier curves is introduced to satisfy the impact time and angle constraints under time-varying speed. The impact angle is satisfied by driving the UAV along a specified ending line. The impact time is satisfied by controlling the trajectory length, which is realized through adjusting one Bezier curve end point along the ending line. The adjustable range of this end point, along with the maximum trajectory curvature, is analyzed to ensure that the trajectory is flyable. Guidance command is generated using inverse dynamics. Numerical simulations under various scenarios are demonstrated to illustrate the performance and validate the effectiveness of the proposed method.

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“…Homing guidance systems that can implement fire-andforget attacks have been rapidly developed and widely applied [1,2]. In recent years, studies on homing guidance have dealt with constraints in the angle of impact [3], mostly through the employment of optimal control theory [4][5][6][7][8][9][10][11][12][13]. Moreover, constraints on the maximum acceleration command are also commonly considered [14,15].…”

Section: Introductionmentioning

confidence: 99%

Cooperative Guidance of Seeker-Less Missiles for Precise Hit

Zhao

Xiong

2019

International Journal of Aerospace Engineering

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A novel cooperative guidance scenario is proposed that implements fire-and-forget attacks for seeker-less missiles with a cheap finder for stationary targets and without requiring real-time communication among missiles or precise position information. Within the proposed cooperative scenario, the classic leader-follower framework is utilized, and a two-stage cooperative guidance law is derived for the seeker-less missile. Linear-quadratic optimal control and biased proportional navigation guidance (PNG) are employed to develop this two-stage cooperative guidance law to minimize the control cost in the first stage and to reduce the maximum acceleration command in the second stage when the acceleration command is continuous. Simulations and comparisons are conducted that demonstrate the effectiveness and advantages of the proposed guidance law.

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Deviated Pure-Pursuit-Based Optimal Guidance Law for Imposing Intercept Time and Angle

Cited by 32 publications

References 24 publications

Fuzzy Observer-Based Dynamic Surface Control for Input-Saturated Nonlinear Systems and its Application to Missile Guidance

Fuzzy Observer-Based Dynamic Surface Control for Input-Saturated Nonlinear Systems and its Application to Missile Guidance

A Geometry-Based Guidance Law to Control Impact Time and Angle under Variable Speeds

Cooperative Guidance of Seeker-Less Missiles for Precise Hit

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