The challenge of this task is to provide an order of magnitude reduction in thermal control power using half the mass while accommodating high heat fluxes and milli-Kelvin stability required for enhanced science.
This task will develop a 2-φ mechanically pumped fluid loop thermal control system for small spacecraft that minimizes system resources, manages spacecraft temperatures, reclaims and redistributes waste heat, and provides science-enabling thermal stability.More »
This technology •Provides order of magnitude reduction in TCS power and 50% reduction in mass over current state-of-the-art. •Accommodates high heat fluxes up to 5 W/cm2; isothermalization of < 2 oC over a 1-m payload bench; temporal stability of < 0.05 oC/minute. •Modular, scalable, configurable to enable integration and at reduced costs. High degree of control authority results in less thermal vacuum testing time.More »
|Organizations Performing Work||Role||Type||Location|
|Jet Propulsion Laboratory (JPL)||Lead Organization||NASA Center||Pasadena, CA|