HyperX Process



Mars EEV Process



Odyssey Process



Structural/Thermal/Optical Process



Mechanical/Electrical/Thermal Process

Solid State Laser

Thermal Management of High Powered Solid State Lasers

HyperX Horizontal Wing Leading Edge

Hyper-X and X-43C Hot Structures

Ares Mars Airplane

ARES (Mars Scout Proposal)

Mars Earth Entry Vehicle

Mars EEV

JIMO Nuclear Reactor

Jupiter Icy Moons Orbiter (JIMO)

Mars Reconnaissance Orbiter Instrument

Mars Reconnaissance Orbiter HiRISE Instrument


A 7000-node PATRAN model shared with few modifications for both structural and thermal analysis -- many parts imported from Pro, with geometry re-done to allow auto hex mesh [from the MIDAS project]:
Pro assembly, PATRAN model, thermal results, structural modal analysis, stress contours on one part:
MIDAS instrument MIDAS thermal model MIDAS thermal results MIDAS structural model MIDAS structural results

A PATRAN model created with a tet mesh direct from a Pro assembly import (about 30 minutes working time from start of import to having results)
Pro assembly, thermal results, close-up of low temperature part:
[Temperatures in K]
Pro/E model of cube MIDAS thermal model/results of cube MIDAS thermal results on cube

An extremely complex geometry part modelled in both PATRAN and Mechanica from direct import of a single Pro part file:


PATRAN thermal results only:
Thermal model of NTF balance Thermal model of NTF balance

A model of 14 waveguides each 9 meters long -- Pro import to PATRAN, temperatures from TRASYS/SINDA imported to PATRAN to get structural deflections
Pro assembly, TRASYS model, thermal results:
Pro/E model of STAR antenna TRASYS model of STAR antenna PATRAN Thermal model of STAR antenna


Several papers have been published which relate to this process: