Integrated CLOS and PN Guidance for Increased Effectiveness of Surface to Air Missiles

Tuz, Zahra Binte Fatima; Islam, Rizvi Syed Tauqeer ul; Ali, Shah Syed Irtiza

doi:10.13111/2066-8201.2017.9.2.11

Cited by 4 publications

(2 citation statements)

References 22 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Performance of CLOS guidance is not reasonably compared with other approaches unless in Yamasaki et al [9] and Bintefatima et al [24] where the true PN (TPN) is employed to perform comparative analyses. Here, to insure a fair comparison in presence of target maneuvers, we have incorporated an ATPN as the benchmark law which suggests the following pursuer acceleration [25]

{bold-italica}_{p} = N false({bold-italicω}_{P} \times {bold-italicV}_{c} false) + {bold-italica}_{t},

where

{bold-italicω}_{P}

{bold-italicV}_{c}

, and

{bold-italica}_{t}

are respectively LOS rate, closing velocity, and the target acceleration, all expressed in pointing frame (P) where its X P axis always points from the pursuer to target as shown in Figure 1.…”

Section: Problem Statementmentioning

confidence: 99%

Section: Atpn Guidance Lawmentioning

confidence: 99%

See 1 more Smart Citation

Novel command to line of sight guidance with practical limitations

Ahi

Haeri

2021

Asian Journal of Control

View full text Add to dashboard Cite

In this paper, a novel scheme of command to line-of-sight guidance law regarding the outstanding practical limitations is proposed. With the aid of formulating problem in pursuer's line of sight frame, the exact feed-forward acceleration commands are derived for a general target motion in three-dimensional engagement geometry. Then, a nonlinear control scheme constructed from feed-forward terms along with a nested saturated feedback strategy is suggested. Two momentous practical limitations are considered. The first is related to existence of pursuer's acceleration saturation which is ignored in all existing solutions. The required conditions to insure the global stability are derived regarding this inevitable constraint. The second is related to existence of guidance filter which is assumed to be ideal in existing literature. The importance of guidance filter is highlighted in the present work employing a cubature Kalman filter. The effectiveness of proposed scheme in comparison with the well-known augmented proportional navigation law, with the absence and presence of guidance filter, autopilot dynamics and target maneuvers is illustrated through benchmark scenarios.

show abstract

{bold-italica}_{p} = N false({bold-italicω}_{P} \times {bold-italicV}_{c} false) + {bold-italica}_{t},

where

{bold-italicω}_{P}

{bold-italicV}_{c}

, and

{bold-italica}_{t}

are respectively LOS rate, closing velocity, and the target acceleration, all expressed in pointing frame (P) where its X P axis always points from the pursuer to target as shown in Figure 1.…”

Section: Problem Statementmentioning

confidence: 99%