Review and Prospect of Missile Plasma Synthetic Jet Control Technology

doi:10.12382/bgxb.2023.0894

Abstract

Abstract:

In the context of the continuous development of anti-missile technology, higher requirements must be imposed on missile maneuverability and fast response to improve the missile hit rate. In recent years, due to the advantages of short response time, no mechanical parts and wide working frequency band, the active flow control technology based on plasma synthetic jet actuator has become a research hotspot in the weapons science and technology and the aerospace field. Great application prospects have been demonstrated in the flow control fields of missiles, such as fast response aerodynamic control, transverse mainstream interference control, shock wave control, shock wave/boundary layer interference control, etc., which provides technical support for reducing the missile resistance and improving the maneuverability and fast response of missile. The principle, development and key problems of the missile plasma synthetic jet flow control technology are described and summarized based on the related literatures issued at home and abroad in the past 20 years and the research experience, hoping to provide help to the relevant researchers.

Key words: missile, plasma synthesis jet, active flow control, aerodynamic control, shock wave control

CLC Number:

TJ762.2

ZHANG Xiaobing, LI Jinfeng. Review and Prospect of Missile Plasma Synthetic Jet Control Technology[J]. Acta Armamentarii, 2024, 45(10): 3356-3370.

Figures/Tables 9

Fig.1 Four types of missiles

Fig.2 Two kinds of plasma synthetic jet actuator and their three-stage working diagrams

Fig.3 Effect of lateral jet on the roll characteristics of canard layout missiles[52]

Fig.4 Comparison of experimental and numerically simulated results of thrust vector nozzle[53]

Fig.5 Schlieren results of the interference effect of plasma synthetic jet on supersonic transverse incoming flow[86]

Fig.6 Controlling the shock wave generated by a finite-height cylinder by the plasma synthetic jet[14]

Fig.7 Structure of shock wave/boundary layer interference flow field and the simulated result[33,60]

Fig.8 Variation of the average velocity of synthetic jet with time at the exit of multiple actuators

Fig.9 Comparison of normal actuator and ablative actuator[46]

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