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Restoration of Full Power Capability on International Space Station Following Leak in the Radiator
Technical Paper
1999-01-1974
ISSN: 0148-7191, e-ISSN: 2688-3627
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English
Abstract
Recent Leonid meteor showers have rekindled general awareness that meteoroid/orbital debris (M/OD) will impact the International Space Station (ISS) hardware and may cause damage and disruption of service. Large surface areas, photovoltaic (PV) arrays and PV radiators, have a higher probability of such an impact.
The power generation, storage, and distribution system on the ISS is a channelized system, such that a malfunction affects only one channel. At assembly complete configuration, the ISS consists of eight power channels, and a temporary loss of one channel can be easily accommodated. However, during early stages, the ISS consists of only one PV module, which has two power channels, and a loss of one channel results in a significant loss of capability.
Each PV module is supported by a photovoltaic thermal control system (PV TCS), which consists of two independent recirculating cooling loops. Each coolant loop collects heat from actively cooled components and radiates it to space via a radiator. An M/OD impact may rupture a tube in the radiator causing the coolant to escape and half of the PV TCS to shut down. Without active cooling, electrical components will overheat and shutdown, resulting in the loss of one power channel.
The first PV module also contains an Early External Active Thermal Control System (EEATCS), which consists of two independent re-circulating coolant loops. The EEATCS collects waste heat from the US Laboratory (USL) and radiates it to space via its own two radiators. The radiators used for the PV TCS and EEATCS are almost identical in design and both systems use the same coolant - anhydrous ammonia.
This paper describes features incorporated in the PV module design to permit restoration of full power capability following M/OD impact on a PV radiator or other events resulting in loss of ammonia. These design features enable isolation of the leaky radiator channel, refilling the PV TCS loop with ammonia, rerouting of the coolant loop to one of the EEATCS radiators, and restart of the power channel.
Authors
Citation
Hajela, G., Allen, R., and Mouradian, E., "Restoration of Full Power Capability on International Space Station Following Leak in the Radiator," SAE Technical Paper 1999-01-1974, 1999, https://doi.org/10.4271/1999-01-1974.Also In
References
- Thermal Control Subsystem for the Photovoltaic Module on the International Space Station Alpha hajela, G. Goldbergy, v. Gombos, F. IECEC 94
- Early External Active Thermal Control for the International Space Station hajela, G. Gombos, F. delgado, A. Goldbergy, v. IECEC 94
- Specification for the Pump and Flow Control Assembly RC2814, Rev. L October 1997
- PV TCS System Hydraulic Analysis with EEATCS Replacement Radiator EID-03742, Eileen Mouradian December 15 1998
- Early Ammonia Servicer, Cargo Element Conceptual Design Review Package Art Itow February 1999
- PV TCS Contingency Coolant Plan for a Failed PVR Loop A or B Bob Allen, EID-03728 December 1998