Generalized Model Predictive Static Programming and Angle-Constrained Guidance of Air-to-Ground Missiles

Maity, Arnab; Oza, Harshal B.; Padhi, Radhakant

doi:10.2514/1.g000038

Cited by 89 publications

(26 citation statements)

References 29 publications

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“…Consider the closed-loop networked system (15) and (16) with Eq. (19), satisfying Assumptions 1-2 and |ϕ i (0)| < π/2(i ∈ Ω).…”

Section: Theoremmentioning

confidence: 99%

“…The issue of impact angle control guidance (IACG) has been addressed in an amount of works, from the biased proportional navigation guidance based IACG laws [8,9,13,21,31] to the optimal control theory based IACG laws [12,22,23], from the model predictive static programming technique based IACG laws [1,16] to the sliding mode control theory based IACG laws [4,10,11,14,20,28,32], too numerous to mention one by one.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Distributed cooperative guidance of multiple anti-ship missiles with arbitrary impact angle constraint

Wang

Zhang

2015

Aerospace Science and Technology

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“…Consider the closed-loop networked system (15) and (16) with Eq. (19), satisfying Assumptions 1-2 and |ϕ i (0)| < π/2(i ∈ Ω).…”

Section: Theoremmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Distributed cooperative guidance of multiple anti-ship missiles with arbitrary impact angle constraint

Wang

Zhang

2015

Aerospace Science and Technology

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“…In Literature (6) , a linear time-varying guidance law was addressed using the inverse problem in optimal control theory to obtain the expected impact angle and minimal miss distance. With the progress of model predictive static programming and generalised model predictive static programming approaches in recent years, Literature (7) and (8) proposed new suboptimal guidance commands to accomplish specific impact angles.…”

Section: Introductionmentioning

confidence: 99%

Novel second-order sliding mode guidance law with an impact angle constraint that considers autopilot lag for intercepting manoeuvering targets

Zhang

Xia

2020

Aeronaut. j.

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A novel second-order sliding-mode-based impact angle and autopilot lag guidance law for engaging manoeuvering targets with unknown acceleration is presented in this study. A backstepping technique is applied to the design of the sliding surface. The proposed guidance law is based on a new sliding surface. It exhibits the advantage of ensuring that the sliding surface and its derivative will converge to zero in finite time while guaranteeing that the sliding surface will not cross zero until the ultimate time. The method effectively eliminates the undesired chattering of the sliding surface. To compensate for the uncertainty caused by target manoeuvering, a new observer is developed to estimate target manoeuvering. The convergence of the system is proven through a Lyapunov function and finite time convergence theory. Lastly, mathematical simulations results show that the proposed guidance law can achieve precise interception with a wide range of impact angles, thereby verifying the effectiveness of the guidance law.

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“…MPSP is suitable for two-point boundary value problems with terminal constraints. Applications of the technology on different issues can be seen in recent articles [22][23][24]. The following are the main contributions of this paper:…”

Section: Introductionmentioning

confidence: 99%

Three-Dimensional Impact Time and Angle Control Guidance Based on MPSP

Zhang

Chen

2019

International Journal of Aerospace Engineering

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A new nonlinear guidance law for air-to-ground missile cooperation attacks is proposed in this paper. This guidance law enables missiles with different initial conditions to attack targets simultaneously, and it can also precisely satisfy the terminal impact angle conditions in both flight-path angle and heading angle. The guidance law is devised using the model predictive static programming (MPSP) method, and the control saturation constraint is incorporated in the MPSP algorithm. The first-order-lag acceleration of the missile is taken as the state variable to realize the convergence of the terminal acceleration to zero. Moreover, a collision avoidance strategy for three-dimensional missile cooperative flight is proposed. The simulation results show that the guidance law can make the missiles hit the target accurately at the same time with the ideal impact angles and can realize the control saturation constraints of the missiles. This can increase the attack effects and is significant for collaborative attacks.

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Generalized Model Predictive Static Programming and Angle-Constrained Guidance of Air-to-Ground Missiles

Cited by 89 publications

References 29 publications

Distributed cooperative guidance of multiple anti-ship missiles with arbitrary impact angle constraint

Distributed cooperative guidance of multiple anti-ship missiles with arbitrary impact angle constraint

Novel second-order sliding mode guidance law with an impact angle constraint that considers autopilot lag for intercepting manoeuvering targets

Three-Dimensional Impact Time and Angle Control Guidance Based on MPSP

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