Multidisciplinary Approach to Aerospike Nozzle Design

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.

[1]  Dean R. Chapman,et al.  Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition , 1958 .

[2]  T. J. Mueller,et al.  Base Flow Characteristics of a Linear Aerospike Nozzle Segment , 1973 .

[3]  G. Hagemann,et al.  Nozzle flowfield analysis with particular regard to 3D-plug cluster configurations , 1996 .

[4]  Hans Immich,et al.  FESTIP technology developments in liquid rocket propulsion for reusable launch vehicles , 1996 .

[5]  John E. Dennis,et al.  Problem Formulation for Multidisciplinary Optimization , 1994, SIAM J. Optim..

[6]  John J. Korte,et al.  An Explicit Upwind Algorithm for Solving the Parabolized Navier-Stokes Equations , 1989 .

[7]  Robert Baumgartner,et al.  Lifting body - An innovative RLV concept , 1995 .

[8]  G. Angelino,et al.  Approximate method for plug nozzle design , 1964 .

[9]  G. Rao,et al.  Spike Nozzle Contour for Optimum Thrust , 1961 .

[10]  H. Doyle Thompson,et al.  Design of Maximum Thrust Plug Nozzles for Fixed Inlet Geometry , 1971 .

[11]  R. V. Burry,et al.  Liquid propellant rocket engines - Their status and future. , 1967 .

[12]  Garret N. Vanderplaats,et al.  CONMIN: A FORTRAN program for constrained function minimization: User's manual , 1973 .

[13]  Robert D. Braun,et al.  Collaborative optimization: an architecture for large-scale distributed design , 1996 .

[14]  G. Rao,et al.  Recent Developments in Rocket Nozzle Configurations , 1961 .

[15]  G. Krülle,et al.  Plug Nozzle Flowfield Calculations for SSTO Applications , 1995 .