Characterization of laser propulsion technology for on-orbit thruster
- Paper number
IAC-05-C4.6.09
- Author
Dr. Shigeaki Uchida, Tokyo Institute of Technology, Japan
- Year
2005
- Abstract
Laser propulsion has very unique advantage of producing exhausting gas (ions) of very high velocity. On the other hand, laser irradiation condition can be altered to achieve completely opposite condition, that is, a laser propulsion system can be operated in very high thrust generation. In this case the ratio between thrust and required laser energy is quite high. It is most probable that in a practical propulsion system, high propellant usage and high thrust generation have to be balanced Laser propulsion technology can adapt itself to wide variety of space transportation mission easily. A series of laboratory experiments has been conducted to clarify laser irradiation and target i.e. propellant conditions. Specific impulse as high as 10,000 s has been measured when target surface was irradiated by a laser intensity larger than plasma generation threshold. On the other hand when reduced laser intensity is absorbed by a volume of propellant, a significant amount of propellant mass is ejected resulting in large thrust generation for a given laser power. The conversion efficiency of as high as 0.1 mN/W has been realized for a designed propellant and laser irradiation condition. The first realization of laser thruster is expected to be a micro thruster applicable to an on-orbit maintenance mission for small satellites. A basic design of such thruster and the present status of laser devise that could be used for the purpose will be described.
- Abstract document