NASA has communicated a need for advanced TPS sensing to improve laboratory performance evaluation of new TPS materials as well as in-situ monitoring for manned and unmanned missions. Testing and evaluation of new TPS materials represents a significant activity in the planning of all missions. Typically, the TPS requirements are fairly well identified with respect to heat flux profile, duration, atmosphere, etc. based upon the specific mission. However, ruggedized sensors for monitoring heat flux in-situ are not yet available for TPS validation or fielding. The Orion capsule, being developed by NASA under the MPCV (Multi-Purpose Crew Vehicle) program, calls for a number of TPS sensors where real time heat flux data would be invaluable. Challenging opportunities exist at JPL in developing TPS systems for unmanned sample return missions from both a Near Earth Object (NEO) and Mars. The competing requirements for low mission weight and increased TPS performance due to increased thermal loads from higher re-entry speeds results in a need for improved sensors for TPS development.