A model of a linear aerospike rocket nozzle that consists of coupled aerodynamic and structural analyses has been developed. A nonlinear computational fluid dynamics code is used to calculate the aerodynamic thrust, and a three-dimensional finite-element model is used to determine the structural response and weight. The model will be used to demonstrate multidisciplinary design optimization (MDO) capabilities for relevant engine concepts, assess performance of various MDO approaches, and provide a guide for future application development. In this study, the MDO problem is formulated using the multidisciplinary feasible (MDF) strategy. The results for the MDF formulation are presented with comparisons against separate aerodynamic and structural optimized designs. Significant improvements are demonstrated by using a multidisciplinary approach in comparison with the single-discipline design strategy.
Multidisciplinary Approach to Aerospike Nozzle Design
1997
18 pages
Report
Keine Angabe
Englisch
Multidisciplinary Approach to Aerospike Nozzle Design
NTRS | 1997
|Multidisciplinary Approach to Linear Aerospike Nozzle Optimization
British Library Conference Proceedings | 1997
|