Impact time control guidance considering seeker's field-of-view limits

Kim, Hyeong-Geun

doi:10.1109/cdc.2016.7798900

Cited by 16 publications

(7 citation statements)

References 13 publications

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“…Therefore, this method is also subject to the problem of guidance command jumps. In [23], the kinematic conditions for impact time control are defined, and then the backstepping control method is used to satisfy the defined conditions. In the backstepping control structure, the designed virtual control can realize the FOV constraint.…”

Section: Introductionmentioning

confidence: 99%

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Field-of-View Constrained Impact Time Control Guidance via Time-Varying Sliding Mode Control

Ma¹,

Wang²,

Wang³

2021

Aerospace

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The problem of impact time control guidance with field-of-view constraint is addressed based on time-varying sliding mode control. The kinematic conditions that satisfy the impact time control with field-of-view constraint are defined, and then a novel time-varying sliding surface is constructed to achieve the defined conditions. The sliding surface contains two unknown coefficients: one is tuned to achieve the global sliding surface to satisfy the impact time constraint and zero miss distance, and the other is tuned to guarantee the field-of-view constraint. The guidance law is designed to ensure the realization of the global sliding mode. On this basis, the guidance law is modified to a closed-loop structure, and the maximum detection capability of the seeker is utilized to a greater extent. Under the proposed guidance law, neither the small angle assumption nor time-to-go estimation is needed. The guidance command is continuous and converges to 0 at the desired impact time. Simulation results demonstrate the effectiveness and superiority of the proposed guidance law.

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Section: Introductionmentioning

confidence: 99%

“…Third, compared with [21,22], under the proposed guidance law, the guidance command is continuous without jumps, which is more conducive to practical applications. Fourth, compared with [23,24], the required maximum acceleration command is significantly reduced under the proposed guidance law.…”

Section: Introductionmentioning

confidence: 99%

Field-of-View Constrained Impact Time Control Guidance via Time-Varying Sliding Mode Control

Ma¹,

Wang²,

Wang³

2021

Aerospace

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“…Similarly, Park et al proposed a three-stage biased PNG (BPNG) law with a time-varying bias by using the switching logic to change guidance stages to address the FOV constraint [14]. The third one is based on other advanced control theories [15]- [17]. Wang et al proposed a SMC based guidance law considering the FOV constraint by using an integral barrier Lyapunov function to make the constrained state reach the sliding mode in finite time [15].…”

Section: Introductionmentioning

confidence: 99%

“…Qian et al [16] modeled this problem as an infinite-horizon nonlinear regulator problem with state constrained and solved it by using a Riccati equation related to the baseline state. The back-step control was adopted to solve the FOV constraint in [17].…”

Section: Introductionmentioning

confidence: 99%

Impact Angle Control Guidance Law With Seeker’s Field-of-View Constraint Based on Logarithm Barrier Lyapunov Function

2020

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In recent years, the strapdown system has become the significant trend of the development of precision guided weapons. In order to effectively hit the lightly armored targets, researchers have done a series of studies on the impact angle control. However, most of them ignored the field-of-view constraint of the strapdown seeker. The existing impact angle control guidance laws with the field-of-view constraint have obvious drawbacks to some extent. For example, most of them are only applicable against nonmaneuvering targets and some of them suffer sudden hopping of guidance command due to the use of switching logic. Taking the strapdown seeker missile as the research object, this paper studies the field-of-view constrained impact angle control guidance problem against stationary targets, constant speed targets and maneuvering targets. According to the sliding mode control theory, two kinds of sliding surfaces are designed to make the missile achieve high precision attack under a desired impact angle within the field-of-view constraint. A quadratic barrier Lyapunov function and a logarithm barrier Lyapunov function are used to guarantee that the sliding surfaces designed for the impact angle constraint and the field-of-view constraint can converge to zero in finite time respectively. Then, a nonlinear extended state observer is proposed to estimate the unmeasurable disturbance of the system and alleviate the undesirable chattering by compensating it with the estimation of the disturbance. Finally, the feasibility of the proposed law is verified by numerical simulations.INDEX TERMS Field-of-view constraint, impact angle control, logarithm barrier Lyapunov function, nonlinear extended state observer, sliding mode control.

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“…As an extension of this work, addressing the FOV constraint by the varying coefficient of weighted optimal control is discussed in [15], wherein changeable weighting coefficients provide an additional degree of freedom to shape missile trajectory while maintaining the lock-on condition. In addition, it is reported in recent literature that some advanced control methodologies are also employed to handle the issue of FOV constraint, such as sliding mode control [16], backstepping control [17], and nonlinear mapping [18].…”

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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Impact time control guidance considering seeker's field-of-view limits

Cited by 16 publications

References 13 publications

Field-of-View Constrained Impact Time Control Guidance via Time-Varying Sliding Mode Control

Field-of-View Constrained Impact Time Control Guidance via Time-Varying Sliding Mode Control

Impact Angle Control Guidance Law With Seeker’s Field-of-View Constraint Based on Logarithm Barrier Lyapunov Function

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

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