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Defense Intelligence Reference Document Laser Lightcraft Nanosatellites

Defense Intelligence Agency · 77 pages · text from the file's own layer

This Defense Intelligence Reference Document from the Defense Intelligence Agency, dated 1 November 2010, was produced under the Advanced Aerospace Weapon System Applications (AAWSA) Program. It describes nanosatellite technologies and proposes launching nanosats into orbit with laser Lightcraft propulsion. It also covers a weapon mission selection study and multi-megawatt laser options. The author recommends that the Department of Defense and NASA bring Lightcraft R&D back to the United States and restart the X-50LR flight demonstration program.

Open the PDF at page 35 Original source ↗

“Earth orbit”13 pages

  • p. 8 …The sensor must be capable of detecting Earth over a range of orbital radii with a…
  • p. 13 …Earth. The schedulers will prioritize the contacts, with the nanosats in the higher period orbits getting…
  • p. 17 …For the purpose of this report, we envision a Lightcraft Earth-to-Orbit (ETD) transportation system…
  • p. 25 …It is seen that beam propagation distances through the Earth's atmosphere are short during initial…
  • p. 26 …0.J 0.1 0 0 °""\\ \ \ \ • Earth-to-Orbit Trajectory • End ofl.uer Ab-bru,tbiog…
  • p. 31 …Ground-to-Space (Earth-to-Orbit) / / / t:l / Pico or Nano Satellites Figure 14. Ground/Sea…
  • p. 33 …Air to Space (Air to Orbit) 261 If hypersonic magnetohydrodynamic (MHD) airbreathing propulsion research and development…
  • p. 34 …space telescope for viewing military targets on Earth and in space. And structural panels on the…
  • p. 41 …surface footprint even when deployed in geosynchronous Earth orbit (GEO) separates different sources in proximity and…
  • p. 42 …Each picosat is gravity- gradient stable, has a dipole array facing Earth, and a broader beam…
  • p. 43 …811L¥ push broom scanning mode for complete Earth coverage rather than only sampling coverage. The constellation…
  • p. 72 …The system is single-stage-to-orbit and completely reusable with no onboard propellant required (the…
  • p. 75 …J., et al. (1991), "System Requirements for Low-Earth-Orbit Launch Using Laser Propulsion," in Proc…
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Table 2. Performance and Estimated Weights for a Hybrid Rocket and
Lightcraft [261.
Hybrid Rocket Expendible Launch Vehicle - Assumed Perfonnance and Estimated Weights
Payload Mass (kg) 1.00 5.00 10.0
3"' Stage Wt. (kg) 36.8 71.2 108
3"' Stage Isp (s) 295 295 295
Propellant Fraction ,737 .766 .782
Impulsive Veloeity (km/s) 3.62 3.62 3.62
2"d Stage Wt. (kg) 283 311 341
2nd Stage Isp (s) 300 300 300
Propellant Fraetion .800 .814 .830
Impulsive Velocity (km/s) 3.58 3.58 3.58
I"' Stage Wt. (kg) 394 427 462
1"' Stage Isp (s) 305 305 305
Propellant Fraction .860 .868 .891
Impulsive Velocity (km/s) 1.92 1.92 1.92
Total Velocity (km/s) 9.12 9.12 9.12
Total Weight (kg) 715 815 921
I .ightcraft Expl·odablc Lauoth \lehkle----Assumed Performance and Estimated Weights
Payload Mass (kg) 1.00 5.00 10.0
Stage Wt (kg) 2.00 10.0 20.0
UTeetive hp (s) 1,452 1,452 1,452
Propellant Fraction .500 .500 .500
lmpusive Vdocity (km/s) 9.84 9.84 9.84
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Report, from the dia collection. The PDF is mirrored here; the original link is under it. 77 pages are in the text index: search them above, or from the library's search.