Impact-Time-Control Guidance Strategy with a Composite Structure Considering the Seeker’s Field-of-View Constraint

Lee, Seok-Won; Cho, Namhoon; Kim, Youdan

doi:10.2514/1.g005063

Cited by 32 publications

(43 citation statements)

References 40 publications

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“…For interception of moving target with constraint on terminal impact angle and look ahead angle, guidance law which generates guidance command proportional to the product of LOS rate and LOS angle, is proposed by Vairavan and Ratnoo (2017). Furthermore, there are proportional guidance laws with composite structure considering the seeker’s FOV constraint for intercepting non-maneuvering and fast-moving target (Lee and Kim, 2020; Lee et al, 2019), and guidance laws with impact time comtrol (Lee et al, 2020). Optimal control theory is also employed to solve problem of FOV limit.…”

Section: Introductionmentioning

confidence: 99%

“…However, in the above studies (Lee and Kim, 2020; Lee et al, 2013; Lee et al, 2019; Lee et al, 2020; Park et al, 2013; Ratnoo, 2016; Sang and Tahk, 2009; Shaferman, 2017; Vairavan and Ratnoo, 2017; Wang et al, 2016; Yang et al, 2016; Zhang et al, 2016), the limited FOV angle is simplified as the angle between the velocity direction of the missile and the LOS of missile and target by neglecting missile’s attitude dynamics and assuming the AOA of the missile is very small. For the missiles of the atmosphere, we know the AOA is usually the main factor driving the attitude motion and the trajectory motion of missile (Qi, 2004; Zhao et al, 2019).…”

Section: Introductionmentioning

confidence: 99%

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Integral barrier Lyapunov functions-based integrated guidance and control design for strap-down missile with field-of-view constraint

Zhao

Zhang

Guo

2021

Transactions of the Institute of Measurement and Control

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The problem of the integrated guidance and control (IGC) design for strap-down missile with the field-of-view (FOV) constraint is solved by using the integral barrier Lyapunov function (iBLF) and the sliding mode control theory. Firstly, the nonlinear and uncertainty state equation with non-strict feedback form for IGC design is derived by using the strap-down decoupling strategy. Secondly, a novel adaptive finite time disturbance observer is proposed to estimate the uncertainties based on an improved adaptive gain super twisting algorithm. Thirdly, the special time-varying sliding variable is designed and the iBLF is employed to handle the problem of FOV constraint. Theoretical derivation and simulation show that the IGC system is globally uniformly ultimately bounded and the FOV angle constraint is also guaranteed not only during the reaching phase but also during the sliding mode phase.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Integral barrier Lyapunov functions-based integrated guidance and control design for strap-down missile with field-of-view constraint

Zhao

Zhang

Guo

2021

Transactions of the Institute of Measurement and Control

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“…Under this guidance law, the seeker's look angle monotonically converges to 0 from the initial value. The authors of [18] divide the guidance process into two phases. In the first phase, the lead angle remains unchanged, and in the second phase, the missile is governed by the PNG law.…”

Section: Introductionmentioning

confidence: 99%

“…In [19,20], the guidance process is also divided into two stages, and in the first stage, the lead angle remains unchanged. Different from [18], in the second stage, a new guidance law is designed to replace the PNG law, and the time-to-go of this guidance law can also be solved analytically. Therefore, the impact time can also be controlled by selecting the appropriate switching point, and the FOV constraint is not violated.…”

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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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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“…However, the design and analysis in [1,10] incorporate an approximate estimate for the time-to-go of the pure proportional navigation guidance law (PPNG) which arbitrarily assumes small lead angle. To complement the theoretical and numerical issues arising from the inaccurate time-to-go, another guidance method was proposed in [12] by using the exact time-to-go of PPNG derived in [15], but this method requires switching between policies. In summary, a method based on the PPNG with its exact time-to-go for arrival time control under look angle constraint is still absent despite a lot of previous efforts.…”

mentioning

confidence: 99%

Look-Angle-Constrained Control of Arrival Time with Exact Knowledge of Time-to-Go

Cho

Lee

2021

Journal of Guidance, Control, and Dynamics

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The capability to control the time of arrival at a goal position as desired endows a single vehicle or a coalition of many of them with the strategic advantage to perform time-critical missions. Arrival time coordination can be used as an element to solve multi-agent, multi-depot routing and task planning problems in cooperative unmanned aerial robots.The tactic known as Salvo which either designates or synchronises the impact times across multiple missiles to enhance their collective survivability as well as attack effectiveness strongly depends on control of arrival time. In principle, control of arrival time is essentially adjustment of the arc length of the vehicle's flight path through manipulation of the curvature, provided that most vehicles flying in the atmosphere often prefer not to change their speeds excessively.On the other hand, the capability to take measurements of the target with onboard sensors provides a higher degree of autonomy to the vehicle and hence allows a more intelligent behaviour. Modern autonomous vehicles acquire information about the designated destination or the surrounding environment with imaging sensors, in particular. An onboard sensor that collects emission or reflection from the target is usually not likely to be omni-directional yet possesses only a finite field-of-regard. The requirement to ensure continuous acquisition of target-originated signals necessitates a measure to keep the information source inside the sensor's field-of-view which spans over a solid angle of limited range. That is, a box constraint is imposed on the look angle.Respecting the look angle box constraint significantly complicates the design of a manoeuvre policy when it is coupled with the necessity to control the arrival time. The demand to satisfy the desired flight time while obeying the look angle constraint drives an extensive amount of studies in the recent decade, particularly in the domain of missile guidance [1-14]. The approaches have been diversified by the choice of various control methodologies, controlled variables, and especially, the way of quantifying the time-to-go. The guidance methods proposed in [5][6][7]9] are based on parametric shaping of range with respect to a function of look angle, parametrisation of range as a polynomial of time, nonlinear tracking of desired lead angle, and nonlinear regulation of the range and lead angle tracking errors, respectively. The time-to-go information in these methods are provided as their respective exact forms. However, their structures are not similar to the well-known classical guidance laws. On the other hand, the methods proposed in

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Impact-Time-Control Guidance Strategy with a Composite Structure Considering the Seeker’s Field-of-View Constraint

Cited by 32 publications

References 40 publications

Integral barrier Lyapunov functions-based integrated guidance and control design for strap-down missile with field-of-view constraint

Integral barrier Lyapunov functions-based integrated guidance and control design for strap-down missile with field-of-view constraint

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

Look-Angle-Constrained Control of Arrival Time with Exact Knowledge of Time-to-Go

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