S.P. Barinov – Corresponding Member of Russian Academy of Engineering, Dr.Sc.(Eng.), Senior Research Scientist,
First Deputy General Director of Research and Development,
JSC «Kaluga Scientific Research Radio Engineering Institute»
E-mail: barinov@knirti.obninsk.com
S.M. Lazarenkov – Ph.D.(Eng.), Senior Research Scientist, Leading Research Scientist,
MESC «Zhukovsky–Gagarin Air Force Academy» (Voronezh)
E-mail: semila55@yandex.ru
Yu.I. Maevsky – Dr.Sc.(Eng.), General Designer of REW System, Deputy General Director on Research and Development,
JSC «KRET»
A.A. Morozov – General Director of JSC «Kaluga Scientific Research Radio Engineering Institute»
A design method of the predictive model of a missile guidance loop based on measurements of its phase coordinates after injection of an intended interference in the guidance loop input is considered. The missile behavior prediction merit is evaluated with the use of a «correlation index of actual values and model-predicted estimates of the guidance loop output». It is shown that the identification time for the typical missile guidance loop is not increase 0,8…1,2 s, and prediction time with probability of 0.95 is more 80% of the time of the conflict and sufficient for optimal jamming response.
An analysis of the design process of a missile guidance loop prediction model (PM) is undertaken based on its identification results as one of the major procedures for parametric synthesizing of jamming techniques against missile radar guidance systems in the course of electronic warfare engagement. The problem of missile guidance loop identification was considered in terms of the problem of determination of characteristics and parameters of the identification model (IM) of a partially specified structure by measured inputs and outputs over a limited time. A design (synthesis) procedure is suggested for the prediction model of a missile guidance loop based on its parametric identification with the use of the recurrent least square method (RLSM). The identification is carried out by measuring phase coordinates of a threat missile after stimulating the input of the missile guidance loop with interference caused by a protected aircraft maneuver or special jamming techniques. Mathematical simulation shows that the use of RLSM makes it possible to almost certainly predict the original loop behavior for the time period of typical missile guidance loops is 80% of total electronic engagement time. For RLSM case, the identification time does not exceed 0.5…1.2 s. We make a conclusion that the use of predictive models of missile guidance loops based on their parametric identification with RLSM gives high merit of prediction of missile behavior for the duration of its terminal guidance and makes it possible to select optimal jamming response in the course of electronic warfare engagement.
- Barinov S.P., Lazarenkov S.M., Maevskii Yu.I., Shcherbakov A.N. Sistemotekhnicheskii analiz putei povysheniya effektivnosti kompleksov individualno-vzaimnoi zashchity letatelnykh apparatov ot perspektivnykh sistem navedeniya upravlyaemykh raket. Vestnik NTS VPK. 2019. Vyp. 1. S. 46−50. (in Russian)
- Kozlov S.V., Karpukhin V.I., Lazarenkov S.M. Modeli konflikta aviatsionnykh sistem radioelektronnoi borby i protivovozdushnoi oborony. Voronezh: VUNTs VVS «VVA». 2013. 467 s. (in Russian)
- Semenov A.D., Artamonov D.V., Bryukhachev A.V. Identifikatsiya ob’ektov upravleniya: Ucheb. posobie. Penza: Izd-vo Penzenskogo gosudarstvennogo universiteta. 2003. (in Russian)