FEM/SINDA: Combining the strengths of NASTRAN, SINDA, I-DEAS, and PATRAN for thermal and structural analysis

This paper describes the interface/integration between FEM/SINDA, a general purpose geometry driven thermal analysis code, and the FEM software: I-DEAS, PATRAN, and NASTRAN. FEM/SINDA brings together the advantages of the finite element method to model arbitrary geometry and anisotropic materials and SINDA's finite difference capability to model thermal properties, loads, and boundary conditions that vary with time or temperature. I-DEAS and PATRAN thermal entities are directly supported since FEM/SINDA uses the nodes of the FEM model as the point at which the temperature is determined. Output from FEM/SINDA (as well as the FEM/SINDA input deck) can be used directly by NASTRAN for structural analysis

Designing And Optimizing Missiles In An Interactive Environment

Designing missiles is a highly multidisciplinary engineering task. Involved in the design is geometric modeling, aerodynamics, propulsion, thermal analysis, weight estimation, trajectory analysis, lethality, structural analysis, controls analysis, packaging of components, and cost estimation. In the past these disciplines have been separated making it difficult to agree on a design that will satisfy the needs of each of the disciplines. Interactive Missile Design (IMD) is a somftware integrating the disciplinary tools involved in the conceptual design of missiles. With IMD, the designer can concentrate on improving the design instead of spending time on ensuring continuity between the disciplines. IMD will enable better missile designs and also reduce the design cycle time. IMD is built in an object-oriented dependency-tracking webenabled language called AML (Adaptive Modeling Language). With the integration of the disciplinary software optimization has become a natural extension of the capabilities of IMD. This paper will discuss the development of the interactive missile design environment, the optimization functionality integrated with it, as well as a missile optimization example. © 2002 by M. Alexandra Ahlqvist

Using Response Surface Approximations To Cover Holes In The Design Space: Conceptual Design Of A Missile

The objective of this paper is to demonstrate an innovative and practical technique in which multidisciplinary optimization can be carried out while there exist points in the design space for which a response cannot be evaluated. It will also be demonstrated how design of experiment and response surface approximations are used to eliminate other complications associated with optimization of large-scaled designs. A multidisciplinary highly coupled air-to-air sparrow like missile design problem will be introduced to demonstrate the practical side of design optimization. The intention here is to provide practical engineering recommendations to others attempting to optimize industrial type design problems. © 2002 by ASME