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

Author

Huang En ; Li Shunli ; Zhou Ding

Author_Institution

Sch. of Astronaut., Harbin Inst. of Technol., Harbin, China

fYear

2013

fDate

21-23 Sept. 2013

Firstpage

553

Lastpage

556

Abstract

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.

Keywords

missile control; rocket engines; stability; attack angle; fixed tails; induced rolling moment formation mechanism; mathematical simulation verification; meteor missile; missile RSC; qualitative analysis; quantitative analysis; rocket engine; roll stability control; rudder angle; ship-to-air missile; Equations; Frequency modulation; Joining processes; Mathematical model; Missiles; Power system stability; Trajectory; Meteor Missile; fixed tails; induced flow field; induced rolling moment; induced rolling moment coefficient;

fLanguage

English

Publisher

ieee

Conference_Titel

Instrumentation, Measurement, Computer, Communication and Control (IMCCC), 2013 Third International Conference on

Conference_Location

Shenyang

Type

conf

DOI

10.1109/IMCCC.2013.125

Filename

6840515