Solar Thermionic Test in a Thermal Receiver

Details Solar Thermionic Test in a Thermal Receiver Solar Thermionic Test in a Thermal Receiver

Jan 2006

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2006aipc..813..598c&link_type=abstract

SPACE TECH.& APPLIC.INT.FORUM-STAIF 2006: 10th Conf Thermophys Applic Microgravity; 23rd Symp Space Nucl Pwr & Propulsion; 4th C

Computer Science

Performance

Thermionic Conversion, Performance Characteristics Of Energy Conversion Systems, Figure Of Merit, Spaceborne And Space Research Instruments, Apparatus, And Components

Scientific paper

A single cell cylindrical inverted thermionic converter (CIC) was tested at the Solar Thermal Propulsion Test Facility of the NASA Marshall Space Flight Center (MSFC). The inverted design is well suited to heating via solar power. For testing the CIC was installed in a thermal receiver into which the concentrated solar flux was focused, achieving temperatures of ~1700 K. A high temperature secondary concentrator was used at the entrance of the receiver to reduce re-radiation losses and to help disperse the solar illumination within the receiver. The molybdenum secondary concentrator is a Winston cone design and reached operating temperatures approaching 1700 K. Ray tracing and thermal modeling of the receiver was performed to evaluate component operating temperatures and to develop a relation between input power and operating temperatures. Inefficiencies in the optical train coupled with a marginal solar irradiance peaking at 830 W/m2 resulted in lower than desired test temperatures. The maximum emitter temperature achieved was 1670 K. Nevertheless electric power was produced by the thermionic converter driven solely by solar power. This test demonstrates the feasibility of using solar heating to produce electrical power by thermionic converters for future satellite power needs.

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