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Experimental research and numerical simulations of thrust vector control nozzle flow

Published online by Cambridge University Press:  25 May 2016

S. Zivkovic ,
M. Milinovic ,
N. Gligorijevic  and
M. Pavic
S. Zivkovic*
Affiliation:
Military Technical Institute, Rocket Armament Sector, Department for Rocket Propulsion, Belgrade, Serbia
M. Milinovic*
Affiliation:
University of Belgrade, Faculty of Mechanical Engineering, Department for Weapons Systems, Belgrade, Serbia
N. Gligorijevic*
Affiliation:
Military Technical Institute, Rocket Armament Sector, Department for Rocket Propulsion, Belgrade, Serbia Military Academy, Department for Chemical Engineering, Belgrade, Serbia
M. Pavic*
Affiliation:
Military Technical Institute, Rocket Armament Sector, Department for Guidance and Control, Belgrade, Serbia
*
sasavite@yahoo.com
mmilinovic@mas.bg.ac.rs
nikola.gligorijevic@gmail.com
cnn@beotel.rs
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Abstract

Rocket motor nozzle flow geometry is considered through its influence on the thrust vector control (TVC) performances. Extensive research is conducted using theoretical and software simulations and compared with experimental results. Cold and hot flow test equipments are used. The main objective of the research is to establish the methodology of flow geometry optimisation on the TVC hardware system. Several geometry parameters are examined in detail and their effects on the system performances are presented. The discovered effects are used as guidelines in the TVC system design process. A numerical method is presented for the determination of dynamic response time upper limit for the TVC system based on the gas flow dynamics performances.

Keywords

Rocket motorthrust vectoringjet tabsnozzle geometryseparated flowrecirculation zoneside forcethrust loss

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 120 , Issue 1229 , July 2016 , pp. 1153 - 1174
Copyright
Copyright © Royal Aeronautical Society 2016 

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