Hello,
we currently use HyperSizer 7.3.50 with ANSYS 18.2 to evaluate various designs of a Reusable Space Launch Vehicle with metallic materials.
First, our understanding of the thermal behavior when connecting HS to ANSYS: The help page on “Thermal Loads” says that “ANSYS thermal loads are not supported.” However, as HyperSizer only imports the resultant element forces from the ANSYS results file and BF-commands are also included in the newly created "*_i.cdb", thermal strains/stresses seem to be considered. Therefore, the only relation HyperSizer cannot build up is which material property to use at which region of the structure, because the current temperature is not known. Is this right?
Now to our problem: Different parts of the structure, such as the tank or the wings, have different temperatures assigned in a wide range. Additionally, these temperatures should change for different load sets, such as liftoff or reentry. Thermal strains/stresses seem to be included in the results, but we cannot change the loads between load sets.
Workaround: For considering temp-dependent material properties in the parts of the structure we created separate materials for different temperatures, such as "Alu 20K" and "Alu 293K". But this obviously neglects temperature changes between load sets, because there is no possibility to change these materials between load sets.
Questions: Is our understanding of the use of temperatures in HS/ANSYS correct? Is there another workaround to include variable thermal setups in load sets?
Thank you in advance,
Jan