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Record Details

Record 18 of 1564
Development of Polymer Coatings for the ProSEDS Tether
Author and Affiliation:
Vaughn, Jason A.(NASA Marshall Space Flight Center, Huntsville, AL United States)
Kamenetsky, Rachel R.(NASA Marshall Space Flight Center, Huntsville, AL United States)
Finckenor, Miria(NASA Marshall Space Flight Center, Huntsville, AL United States)
Wright, Ken(Alabama Univ., Huntsville, AL United States)
Abstract: The ProSEDS mission is designed to provide an on-orbit demonstration of the electrodynamic propulsion capabilities of tethers in space. The ProSEDS experiment will be a secondary payload on a Delta 11 unmanned, expendable booster. A 5 km conductive tether is attached to the deployer baseplate on the Delta 11 second stage and collects current from the low Earth orbit (LEO) plasma to facilitate de-orbit of the Delta II second stage. The conductive tether is attached to a 10-15 km non-conductive tether, which in turn is attached to an endmass. A bare metal tether would have the best conductivity but thermal concerns preclude this design. A conductive polymer developed by Triton Systems has been optimized for optimum conductivity and thermo-optical properties. The current design for the ProSEDS conductive tether is seven individually coated strands of 28 AWG aluminum wire, coated with 12.7 micrometers (0.5 mil) atomic oxygen-resistant conductive polymer composed of a mixture of COR and PANi, wrapped around a braided Kevlar 29 core. Extensive testing has been performed at the Marshall Space Flight Center to qualify this material for flight on ProSEDS. Atomic oxygen exposure has been performed, with solar absorptance and infrared emittance measured before and after exposure. Plasma chamber tests have been completed, as well as tether deployment tests. Also developed for the ProSEDS mission was the insulating polymer TOR-BP. Approximately 200 meters of the conductive tether closest to the Delta II second stage is insulated to prevent any electron reconnection to the tether from the plasma contactor. The insulating material is TOR-BP with a dielectric strength of TBD.
Publication Date: Jan 01, 2000
Document ID:
19990094256
(Acquired Oct 22, 1999)
Subject Category: NONMETALLIC MATERIALS
Document Type: Preprint
Meeting Information: Aerospace Sciences; 10-13 Jan. 2000; Reno, NV; United States
Meeting Sponsor: American Inst. of Aeronautics and Astronautics; United States
Contract/Grant/Task Num: RTOP 242-81-40
Financial Sponsor: NASA Marshall Space Flight Center; Huntsville, AL United States
Organization Source: NASA Marshall Space Flight Center; Huntsville, AL United States
Description: 1p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: TETHERING; ALUMINUM COATINGS; SPACE MISSIONS; PROPULSION; OXYGEN ATOMS; KEVLAR (TRADEMARK); SOLAR ENERGY ABSORBERS; INFRARED RADIATION; DIELECTRIC PROPERTIES; TEST CHAMBERS; SPACE SHUTTLE PAYLOADS
Availability Source: Other Sources
Availability Notes: Abstract Only;
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