Two-Phase Optimal Guidance Law considering Impact Angle Constraint with Bearings-Only Measurements

Wang, Tianning; Tang, Shijie; Guo, Jie; Zhang, Haoqiang

doi:10.1155/2017/1380531

Cited by 11 publications

(3 citation statements)

References 22 publications

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“…With the aim of successfully intercepting maneuvering targets, many advanced modern robust guidance law algorithms have been employed, such as the nonlinear H ∞ guidance law [7], the adaptive guidance law [8], the differential game guidance law [9], the L 2 gain guidance law [10], and the optimal guidance law [11]. Compared with the abovementioned robust guidance laws, the sliding mode guidance law [12,13] appears as the most widespread one on account of its simple design process and good robustness to external disturbances [14].…”

Section: Introductionmentioning

confidence: 99%

A Novel Guidance Law for Intercepting a Highly Maneuvering Target

Zhang

2021

International Journal of Aerospace Engineering

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Given the resolution of the guidance for intercepting highly maneuvering targets, a novel finite-time convergent guidance law is proposed, which takes the following conditions into consideration, including the impact angle constraint, the guidance command input saturation constraint, and the autopilot second-order dynamic characteristics. Firstly, based on the nonsingular terminal sliding mode control theory, a finite-time convergent nonsingular terminal sliding mode surface is designed. On the back of the backstepping control method, the virtual control law appears. A nonlinear first-order filter is constructed so as to address the “differential expansion” problem in traditional backstepping control. By designing an adaptive auxiliary system, the guidance command input saturation problem is dealt with. The RBF neural network disturbance observer is used for estimating the unknown boundary external disturbances of the guidance system caused by the target acceleration. The parameters of the RBF neural network are adjusted online in real time, for the purpose of improving the estimation accuracy of the RBF neural network disturbance observer and accelerating its convergence characteristics. At the same time, an adaptive law is designed to compensate the estimation error of the RBF neural network disturbance observer. Then, the Lyapunov stability theory is used to prove the finite-time stability of the guidance law. Finally, numerical simulations verify the effectiveness and superiority of the proposed guidance law.

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Section: Introductionmentioning

confidence: 99%

A Novel Guidance Law for Intercepting a Highly Maneuvering Target

Zhang

2021

International Journal of Aerospace Engineering

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“…Whereas, severe measurement errors introduced by the strapdown seeker make it difficult to achieve an accurate estimation. Moreover, with few exceptions of [2], [32], [33], preexisting laws pay little attention to maintaining sufficient observability during the homing phase, with result that the filter/estimator cannot work properly [2].…”

Section: Introductionmentioning

confidence: 99%

Integrated Strapdown Missile Guidance and Control With Field-of-View Constraint and Actuator Saturation

et al. 2020

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This paper presents an integrated guidance and control (IGC) law for the strapdown homing missile with consideration of the field-of-view (FOV) constraint and actuator saturation. Given that the commonly-required guidance information, such as the inertial line-of-sight (LOS) angle and/or its angular rate, cannot be measured by the strapdown seeker, a detailed IGC model considering the gravity and timevarying missile velocity is first derived based on the only measurable information, the body-LOS (BLOS) angle. Then a novel IGC controller is designed for this model by means of the integral-type Barrier Lyapunov Function (iBLF) based dynamic surface control technique. This IGC controller following the pure tracking principle is capable of forcing the BLOS angle to track the negative angle of attack while satisfying the FOV constraint and actuator saturation in an integrated manner, thereby guaranteeing a precise attack on a stationary ground target. The stability of closed-loop system and the boundedness of constrained BLOS angle are both proved strictly, and the performance of proposed IGC controller is thoroughly testified by method comparisons and Monte-Carlo analysis. INDEX TERMS Actuator saturation, body-LOS (BLOS) angle, dynamic surface control, FOV constraint, integral-type Barrier Lyapunov Function (iBLF), integrated guidance and control (IGC).

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“…In these papers, the acceleration of the target was a known bounded external disturbance to the missile. A two-phase optimal guidance law was derived to improve the estimation accuracy and terminal performances for impact angle constraint engagement [6]. Yang et al [7] presented a time-varying biased proportional guidance law in which two time-varying bias terms were applied to divide the trajectory into the initial phase and terminal phase.…”

Section: Introductionmentioning

confidence: 99%

Evasion-Pursuit Strategy against Defended Aircraft Based on Differential Game Theory

Sun¹,

Shen²,

Gu³

et al. 2019

International Journal of Aerospace Engineering

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The active defense scenario in which the attacker evades from the defender and pursues the target is investigated. In this scenario, the target evades from the attacker, and the defender intercepts the attacker by using the optimal strategies. The evasion and the pursuit boundaries are investigated for the attacker when the three players use the one-to-one optimal guidance laws, which are derived based on differential game theory. It is difficult for the attacker to accomplish the task by using the one-to-one optimal guidance law; thus, a new guidance law is derived. Unlike other papers, in this paper, the accelerations of the target and the defender are unknown to the attacker. The new strategy is derived by linearizing the model along the initial line of sight, and it is obtained based on the open-loop solution form as the closed-loop problem is hard to solve. The results of the guidance performance for the derived guidance law are presented by numerical simulations, and it shows that the attacker can evade the defender and intercept the target successfully by using the proposed strategy.

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Two-Phase Optimal Guidance Law considering Impact Angle Constraint with Bearings-Only Measurements

Cited by 11 publications

References 22 publications

A Novel Guidance Law for Intercepting a Highly Maneuvering Target

A Novel Guidance Law for Intercepting a Highly Maneuvering Target

Integrated Strapdown Missile Guidance and Control With Field-of-View Constraint and Actuator Saturation

Evasion-Pursuit Strategy against Defended Aircraft Based on Differential Game Theory

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