Resistojets, arcjets, ion engines, radioisotope thrusters, and catalytic monopropellant engines are compared for low-thrust propulsion systems for vehicles of Manned Orbital Research Laboratory (MORL) class; descriptions, specifications, stabilization and control requirements are given for zero-g and artificial-g spin modes with solar cell and Brayton cycle power system configurations; liquid hydrogen, ammonia, and hydrazine are considered as propellants; liftoff, resupply, and 5-yr mission weight comparisons suggest that resistojets and radioisotope thrusters may afford weight savings for MORL-type missions.
Low-thrust propulsion for MORL
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 4 , n 2
1967
5 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Low-thrust propulsion for the MORL.
NTRS | 1967
|Low-thrust propulsion for the MORL.
AIAA | 1967
|Low-thrust propulsion for the MORL
AIAA | 1966
|MORL design studies -- Significant results
Engineering Index Backfile | 1967
|NTIS | 1964
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