Design Analysis of a High Temperature Radiator for the Variable Specific Impulse Magnetoplasma Rocket (VASIMR)

The Variable Specific Impulse Magnetoplasma Rocket (VASIMR), currently under development by Ad Astra Rocket Company, is a unique propulsion system that could change the way space vehicle propulsion is performed. VASIMR’s propulsion efficiency, when compared to that of a conventional chemical rocket, reduces the propellant needed for exploration missions by a factor of 10. Current plans include an International Space Station flight test of the VF-200, a 200 kW VASIMR system. The VF-200 will consist of two 100 kW thruster units packaged together in one engine bus. Each thruster core generates 27 kW of waste heat during its 15 minute firing time. A pumped thermal control loop will maintain the rocket core within its design limits of 283 to 573 K. The design of the high temperature radiator for this loop poses a unique challenge for the vehicle design. This paper will discuss the path taken to develop the heat transport system and the transient-based radiator for the VF-200 thermal control system.