REPUBLIC OF SERBIA

MINISTRY OF DEFENCE

www.mod.gov.rs

MINISTRY OF DEFENCE

Material Resources Sector

Defensive Technologies Department

Military Technical Institute

www.vti.mod.gov.rs

Solid propellant roCket motor nozzle
heat transfer model verification

Saša Živković

Military Technical Institute, Belgrade, sasavite@yahoo.com

radOslav sirovatka

Military Technical Institute, Belgrade, radesirovatka@sezampro.rs

Nikola gligorijević

Military Technical Institute, Belgrade, nikola.gligorijevic@gmail.com

SREDOJE SUBOTIĆ

Military Technical Institute, Belgrade, sredoje.subotic@gmail.com

STEVAN KOZOMARA

Military Technical Institute, Belgrade, kozomara@open.telekom

MOMČILO NIKOLIĆ

Military Technical Institute, Belgrade, mocamirin@gmail.com

Abstract: Heat transfer is one of the most important and complex rocket motor design task. Physical process of heat transfer is unsteady and complex itself and solid propellant rocket motor constructive and technological specificity additionally complicate design. Active thermal protective materials with ablative reaction mechanism are frequently in use, and the motor parts are geometrically complex and made from diverse materials. All this factors are leading to calculation with numerical methods, and one of them is described in this paper. A simple measurement is conducted to improve calculation reliability and for results verification.

Key words: heat transfer, rocket motor, cfd, experiment.