Micro Laser Plasma Thrusters for Small Satellites
Abstract
We developed and tested a preprototype micro laser plasma thruster (micro-LPT). This is a new departure in sub-kilogram micropropulsion modules, which we believe can compare favorably with the micro-PPT in total impulse/dry mass and thrust/power ratios. A lens focuses the light output of a group of fiber-coupled diode lasers onto a special ablatant tape. The tape is composed of a transparent supporting layer through which the light passes without perforating it, and a proprietary absorbing fuel layer which is ignited and further heated by the laser to produce a miniature jet. The device is repetitively pulsed, operates on spacecraft bus voltage, and weighs 0.85 kg. The diodes have 50% electrical to optical efficiency. Best performance from a non-energetic fuel material was obtained with black polyvinyl chloride (PVC), which produced an average of 66 micro-N thrust and coupling coefficient (C(sub m)) of 8O micro-N/W. A proprietary energetic material was also tested, in which the laser initiates a non-propagating detonation. This material produced 500 micro-N of thrust and C(sub m) was 300 micro-N/W. Data are summarized from over 200 single-shot and full thrust tests on dozens of combinations of ablatant materials and supporting transparent polymers.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 2002
- Accession Number
- ADA410142
Entities
People
- Claude Phipps