Design and Analysis of Solid Rocket Motor Nozzle,
EUROPEAN SPACE AGENCY PARIS (FRANCE)
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The objective of this paper is to present the different methods used to design and analyse solid rocket motor nozzles. In a preliminary phase, the typical requirements and parameters required to design a nozzle are discussed. Afterwards the general process of th design is detailed nozzle configuration, aerodynamic contour design, selection and sizing of liners and insulators, etc. In a second step, the different systems used to control the motor thrust or to improve the performance, such as extendible exit cone, are presented. To conclude the presentation, the different steps of the nozzle analysis are presented. For each step aerodynamic, thermal and structural the different computer programs used are presented principle, possibilities, limitations.
- Solid Propellant Rocket Engines