| A method of performing a multidisciplinary optimization of the aerodynamic and structural design of a simplified linear aerospike nozzle segment using Matlab has been developed. The method uses the Matlab function fmincon to determine the highest thrust-to-weight ratio based on given material properties and minimum desired thrust level. The Matlab code developed is allowed to vary the thruster angle and the amount of nozzle truncation in order to achieve its goal.; The developed code produces several kinds of output including the profile of the nozzle, the pressure distribution on the nozzle wall, the thruster angle, the amount of nozzle truncation, and the displacements of the nozzle wall. Results for the aerodynamics portion of the code were compared with results published previously by other authors. The structural portion of the code was compared against results from a Nastran model in a sample test case. |
