System Requirements for Low-Earth-Orbit Launch Using Laser Propulsion
- Sandia National Laboratories (SNL-NM), Albuquerque, NM (United States)
- Lawrence Livermore National Laboratory (LLNL), Livermore, CA (United States)
The use of ground-based lasers to launch small payloads but large total masses into low-Earth orbit may prove to be the most innovative and potentially economical approach for accomplishing this important mission. Of the several possible schemes for laser propulsion, two are examined: (1) ablative momentum transfer using pulsed lasers; and (2) heat exchanger thrusters in conjunction with CW lasers. For an entry-level payload of ~50 kg it is found that the former yields payload-to-power ratios of < 0.5 kg/MW with a requirement for an average laser power of at least 100 MW, whereas the latter might yield 1 to 3 kg/MW with a laser power of several 10s of MW. One of the promising approaches that could yield a driver for such a system is the reactor-pumped laser FALCON, which scales to these power levels with the potential for long run times.
- Research Organization:
- Sandia National Laboratories (SNL-NM), Albuquerque, NM (United States); Lawrence Livermore National Laboratory (LLNL), Livermore, CA (United States)
- Sponsoring Organization:
- USDOE
- DOE Contract Number:
- AC04-76DP00789; W-7405-ENG-48
- OSTI ID:
- 5477875
- Report Number(s):
- SAND--91-1687C; CONF-910626--6; ON: DE91017455
- Journal Information:
- Fusion Technology, Journal Name: Fusion Technology Journal Issue: 4P2 Vol. 20; ISSN 0748-1896
- Publisher:
- American Nuclear Society
- Country of Publication:
- United States
- Language:
- English
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