Research on Induced Rolling Moment of Ship-to-air Missile derived from "Meteor" Missile in Series with Rocket Engine

被引：0

作者：

Huang En ^{[1
]}

Li Shunli ^{[1
]}

Zhou Ding ^{[1
]}

机构：

[1] Harbin Inst Technol, Sch Astronaut, Harbin 150006, Peoples R China

来源：

2013 THIRD INTERNATIONAL CONFERENCE ON INSTRUMENTATION & MEASUREMENT, COMPUTER, COMMUNICATION AND CONTROL (IMCCC) | 2013年

关键词：

Meteor Missile; fixed tails; induced flow field; induced rolling moment; induced rolling moment coefficient;

D O I：

10.1109/IMCCC.2013.125

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

In order to realize the RSC(roll stability control, RSC) of ship-to-air missile derived from Meteor Missile in series with rocket engine, do research on the induced rolling moment caused by connecting tandem after body with fixed tails to Meteor. The induced rolling moment's formation mechanism of fixed tails in derived missile's RSC has been analyzed. This paper obtains the induced rolling moment function taking attack angle and rudder angle as arguments through qualitative and quantitative analysis, then it performs mathematical simulation verification.

引用

页码：553 / 559

页数：7

共 3 条

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[3] Rolling Moment of Slender Body at High Incidence for Air-to-Air Missile/Rocket Applications
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