Heat rejection system technology demonstration model, phase 3
Abstract
A fluid loop radiator system to be used for environmental control of advanced spacecraft and/or payloads is discussed. A technology demonstration model (TDM) was built and tested in a vacuum chamber to verify its thermohydraulic performance and the achievement of the requirements previously defined. The model characteristics include Freon coolant at 8 bar loop pressure, automatic control capability, 60 days maximum mission duration, 1 side only radiating panel, 6 Kg weight per sq m, 200 min to 350 max Watt/sq m heat rejection at 40 C fluid inlet temperature, and 910 Kg/hr flow rate in coldest case. The performance test results are presented.
- Publication:
-
Final Report Aeritalia S.p.A
- Pub Date:
- February 1985
- Bibcode:
- 1985aers.rept.....C
- Keywords:
-
- Fluid Flow;
- Freon;
- Spacecraft Design;
- Spacecraft Models;
- Spacecraft Radiators;
- Cooling Systems;
- Performance Tests;
- Radiative Heat Transfer;
- Vacuum Chambers;
- Fluid Mechanics and Heat Transfer