Guidance and control system design for impact angle control of guided bombs

Kim, Yong-Ho; Kim, Jongju; Park, Minsu

doi:10.1109/iccas.2010.5670209

Cited by 7 publications

(3 citation statements)

References 8 publications

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“…The control input is assumed to be applied to the command of the fin deflection δ c with a time constant τ δ . An aerodynamic model similar to the guided bomb model presented in the study by Kim et al 20 was used to embody the lift L(⋅) and pitch moment M(⋅). For the comparative simulation, the scenarios shown in Figure 2(a) and (c) are used.…”

Section: Performance Demonstration Through Numerical Simulationmentioning

confidence: 99%

Gravity-compensated guidance for impact-angle interception of a moving target

Kim

Lee²,

Kim

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper proposes an impact-angle control guidance (IACG) law for anti-ship and anti-tank missiles in which the command converges to zero at the point of interception, even in a gravity field. The desired line-of-sight (LoS) angle that satisfies the terminal impact-angle and acceleration constraints is first defined. The guidance command is then derived as a solution that realizes the convergence of the actual LoS angle to the desired LoS angle during the terminal stage of homing in on a target. Gravity is considered when designing the guidance law such that the desired terminal constraints are accurately satisfied, even under realistic pitch-axis engagement. We also investigated whether the proposed law is optimal for minimizing the total expense of maneuvering while performing IACG in a gravity field. The results of the numerical simulations included in this study demonstrate that the proposed guidance law achieves accurate impact-angle interception with the command converging to zero at the end of homing.

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Section: Performance Demonstration Through Numerical Simulationmentioning

confidence: 99%

Gravity-compensated guidance for impact-angle interception of a moving target

Kim

Lee²,

Kim

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The guidance schemes for the aerial munitions are in general based on either the classical approach using proportional navigation guidance (PNG) or on modern control theory (MCT). The proportional navigation used in the classical approach employs feedback with a constant gain from the angular rate of the line of sight between the target and the aerial vehicle, in order to minimise the final miss distance ( 22 , 44 ) . PNG has been most widely used in various guided weapons since the 1940s as it requires a small amount of information that can be easily obtained from seeker mounted on the weapons or the ground radar, such as the closing velocity and the line-of-sight (LOS) rate of guided weapons ( 45 ) .…”

Section: Control Law Synthesismentioning

confidence: 99%

“…The performance of designed algorithm was then validated through numerical simulations. In another study, Kim et al ( 22 ) designed guidance and control system to impact a target with a desired impact angle for precision guided bombs such as JDAM. The guidance and control system architecture was composed of autopilot loop and impact angle control guidance loop.…”

Section: Introductionmentioning

confidence: 99%

Guidance and control of standoff air-to-surface carrier vehicle

Mir

Akhtar²,

Eisa

et al. 2019

Aeronaut. j.

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This paper presents an open framework, through which, conventional general purpose aerial munitions can be converted into smart munitions. The retrofit consists of a smart adaptation kit (SAK) having a dedicated Guidance and Control Module (GCM). The adaptation kit along with the GCM ensures that the SAK glide optimally towards the designated target. To reduce cost, the number of control surfaces of the SAK has been kept to a bare minimum, which resulted in an under actuated system. The methodology proposed utilises the theory of gain-scheduled control and leads to an efficient procedure for the design of the controllers, which accurately track reference trajectories defined in an inertial reference frame. The paper illustrates the application of this procedure to the design of stabilisation and tracking controller for the SAK. The design phase is summarised, and the performance of the resulting controllers is assessed in simulation using dynamic model of the vehicle. Simulation results show that apart from improved circular error probable (CEP) of hitting the target, munition ballistic range has also significantly increased with the proposed modification.

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