Accelerated erosion testing of candidate SNAP-8 turbine rotor and nozzle materials
Accelerated wet mercury vapor erosion testing of candidate SNAP-8 turbine rotor and nozzle materials in close pump loop
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Accelerated wet mercury vapor erosion testing of candidate SNAP-8 turbine rotor and nozzle materials in close pump loop
Mechanical testing and metallographic examination of aluminum to copper coldwelded joints after thermal exposure - SNAP-8 electrical terminal
Mercury condenser inventory control system for regulating condensing pressure in SNAP-8 system
Operational characteristics, problems, and failures of ac electromagnetic pumps used in SNAP-8
Alternate lubricant/cooling fluids for SNAP-8
Hydraulic design calculations for SNAP-8 jet centrifugal pump
Thermal performance of SNAP-8 model condenser
SNAP-8 power conversion system development, and test facilities
Space radiator simulator, using finned tube heat exchanger cooled by controllable airflow, for SNAP-8 ground test facility
Voltage distoration effects of SNAP-8 alternator speed controller and alternator performance results
SNAP-8 electrical generating system performance
Conditioning and steady state performance of SNAP-8 tube-in-shell mercury boiler
SNAP-10A high emittance white coating, noting stability at 600 degrees F, irradiation and vacuum and mechanical vibration
SNAP-8, nuclear electric power-conversion system /PCS/ designed for operation in space, using liquid metals as working fluids
Mission performance capabilities of ion engines powered by the 30 kw and 60 kw SNAP-8 power supplies are compared for the following missions: a 24-hr equatorial satellite, a 100 n mi lunar satellite, a 500 n mi Mars satellite, a Mercury probe, and an out-of-the-ecliptic probe. The capabilities of arc- jet engines and chemical engines for the same missions are compared with those of the ion engines. The majority of the comparisons are for 8500-lb spacecraft which are boosted into a 300 n mi orbit by the Atlas-Centaur. Variations in initial orbit altitude, the use of actual launch dates rather than dates based on simplifying assumptions, and the combined use of chemical and electrical propulsion systems were also evaluated in terms of their effect on mission performance.
Guidance perturbations for a low-thrust mars orbit mission using snap-8
Snap fasteners on each side of an electronic assembly rack blank panel give quick access to the interior. Guide pins extending from the inside face easily slip into standard screw holes on the frame and provide additional support.