A parameter design strategy for seeker’s field-of-view constraint in impact angle guidance

Qin, Wen; Xia, Qing; Weixia, Su

doi:10.1177/0954410015576237

Cited by 13 publications

(5 citation statements)

References 13 publications

(13 reference statements)

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“…Expanding (24), we can obtain a quadratic equation with respect to N I as shown in (25), where the proportionality coefficient should be regarded as a known parameter. To solve the value of unknown parameter N I of (25), a simple algebraic method is applied in (26).…”

Section: Implementation Of the Two-phased Guidance Lawmentioning

confidence: 99%

“…The integral value was calculated from initial engagement conditions and desired impact angle. Based on the same strategy of [19], a few of two-phased BPN (TPBPN) guidance laws were proposed in [20][21][22][23][24][25] for attacking a stationary target. A TPBPN was proposed in [20] based on the bias-shaping method, which can satisfy both the terminal-angle constraint and the FOV limitation to maintain the seeker's lock-on condition.…”

Section: Introductionmentioning

confidence: 99%

“…Based on a two-stage PN guidance law, Ratnoo [24] derived a closed-form solution for the choice of navigation gains to satisfy the look angle and impact angle limit. Wen et al [25] proposed a new guidance parameter design strategy based on the classical time-to-go weighted impact angle optimal guidance law. A robust guidance law which was based on the switching logic was designed in [26] by an additional term and combined the sliding mode control.…”

Section: Introductionmentioning

confidence: 99%

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A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit

Zhang

Tang

Guo

et al. 2018

International Journal of Aerospace Engineering

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A two-phased guidance problem with terminal impact angle constraints and seeker’s field-of-view limit is addressed in this paper for a missile against a nonmaneuvering incoming target. From the conventional PN guidance without any constraints, it is found that satisfying the impact angle constraint causes a more curved missile trajectory requiring a large look angle. To avoid the look angle exceeding the seeker’s physical limit, a two-phased look angle control guidance scheme with the terminal constraint is introduced. The PN-typed guidance law is designed for each guidance phase with a specific switching condition of line-of-sight. The proposed guidance law is comprised of two types of acceleration commands: the one in the initial phase which aims at controlling the missile’s look angle to reach the limit and the other for final phase which is produced by switching the navigation gain. The monotonicity of the line-of-sight angle and look angle is analyzed and proved to support the proposed method. To evaluate the specific navigation gains for both initial and final phases, the scaling coefficient between them is discussed by solving a quadratic equation with respect to the initial navigation gain. To avoid a great abrupt acceleration change at the switching instant, a minimum coefficient is chosen. Extensive simulations are performed to validate the efficiency of the proposed approach.

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Section: Implementation Of the Two-phased Guidance Lawmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit

Zhang

Tang

Guo

et al. 2018

International Journal of Aerospace Engineering

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“…Xin et al regarded this problem as a nonlinear optimal control problem and proposed a closed-loop guidance law by using the θ − D control theory [10]. Wen et al [11] presented an IACG law weighted by time-to-go polynomial to address the FOV constraint, which is ensured by continuous optimization. In [12], a range-to-go weighted optimal IACG law considering the FOV constraint was proposed.…”

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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“…In recent years, studies on seeker's field-of-view (FOV) constraints [17][18][19][20] as well as impact angle constraints have been carried out. Imposing an impact angle constraint may result in the trajectory shaping of a missile to be highly curved, which may cause a critical problem such as a target loss in practice when applying the impact angle guidance law to a missile equipped with seekers.…”

Section: Introductionmentioning

confidence: 99%

Direct impact angle control guidance for passive homing missiles

Cho

Kim

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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A guidance problem for impact angle control applicable to a missile equipped with a passive seeker is investigated. The proposed guidance law based on the sliding mode control consists of the proportional navigation guidance term with a varying navigation constant and the additional biased term which is a function of the novel sliding surface. The guidance law directly uses the impact angle error but does not require any range information to be estimated by the additional filter loop of the passive seeker. The asymmetric limit of the passive seeker’s field-of-view is also taken into account, which is not violated by introducing a continuous switching function. The finite time convergence properties are analyzed, and nonlinear simulations are performed to investigate the effectiveness of the proposed guidance law.

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A parameter design strategy for seeker’s field-of-view constraint in impact angle guidance

Cited by 13 publications

References 13 publications

A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit

A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit

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

Direct impact angle control guidance for passive homing missiles

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