*
The Thermal Protection System (TPS) for the Space Shuttle consists of an
outer layer of rigid surface insulation tiles. It is important that an
accurate understanding of the thermal behavior of this system be obtained
prior to usage. This computer program was developed to compute the
transient temperature history and the steady-state temperatures of complex
body geometries in three dimensions. Emphasis has been placed on the type
of problems associated with the TPS, but the program could be used in the
thermal analysis of most three-dimensional systems.*

*
The thermal model is subdivided into sections, or nodes, to a level of
approximation which yields the desired level of accuracy. Input to the
program consists of a geometrical description of the physical system, the
material properties, and selected boundary conditions. The boundary
conditions are used to account for heat flux, reradiation, radiation
interchange, convection, fixed temperatures, and phase changes. The program
will accommodate a thermal model with as many as 500 nodes, 4000 conductors,
3600 radiation interchange conductors, and 75 of each type of boundary
condition. The program solves the differential equations describing the
transient and steady state behavior of the model using finite difference
techniques. For the transient analysis, the user may select either a forward
difference method, a midpoint difference (Crank-Nicolson) method, a backward
difference method, or an alternating direction method to numerically solve the
governing equations. For the steady-state analysis, a modified backward
difference method is available. Program output is in the form of temperature
versus time histories for each section of the thermal model.
(Rockwell International Corp. for NASA Marshall).*

This program was released by NASA through COSMIC as MSC-18616. The italicized text above is from the official NASA release.

- There are no references for this program.
- Download tps.zip, containing the original source code and a test case.