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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.

  • p. 4 …Influence of Target Velocity and Intercept Angle on Impact Energy and Required Mass .................................................................................................. 33 Table 5…
  • p. 5 …The term "minisatellite" refers to a spacecraft with a wet mass (including onboard propellant) of 100…
  • p. 7 …Nanosatellite Technologies OVERVIEW Nanosats require technologies that radically reduce the mass and power of components without…
  • p. 8 …nanosat presents some unique challenges, with low mass (0.25 kg) and low power (0.5…
  • p. 9 …In order to develop a low mass C&DH, a lightweight and low power electronics packaging…
  • p. 11 …RF COMMUNICATIONS The onboard RF subsystem must be small, low mass, and low power. The system…
  • p. 12 …additional strain on an already challenged nanosat mass and power budget. For this reason, the concept…
  • p. 13 …The material will be selected based on mass, cost, manufacturability, ease of assembly and integration, and…
  • p. 15 …for the spacecraft because a large propellant mass and heavy energy source are not carried onboard…
  • p. 17 …Current Lightcraft designs are limited to about 60 g mass and 15 cm in diameter by…
  • p. 21 …It requires a beam power of 0.1 to 1 MW per kg of vehicle mass…
  • p. 22 …The majority of the system mass required to launch a payload to orbit is left on…
  • p. 24 …Therefore, this would allow approximately 4 kg of mass to be placed into orbit with the…
  • p. 25 …same ply-thickness) to meet Lightcraft airframe mass requirements. Another important finding in the study was…
  • p. 31 …Additional estimated mass for performing the Lightsat function is no more than about 1 kg, if…
  • p. 32 …Lightcraft takeoff masses no more than about 20 kg can be accelerated to orbital velocities by…
  • p. 33 …for missile and maneuvering aircraft interception. • Additional mass along Lightcraft centerline for hardened target penetration. LIGHTCRAFT…
  • p. 34 …Lightcraft sizing assumed a propellant mass fraction of 0.5 and 1.0 MW of laser…
  • p. 35 …Hybrid Rocket Expendible Launch Vehicle - Assumed Perfonnance and Estimated Weights Payload Mass (kg) 1.00 5…
  • p. 37 …It is therefore estimated that the air-to-space Lightcraft dry mass would be about the…
  • p. 38 …Influence of Target Velocity and Intercept Angle on Impact Energy and Required Mass 2 61. Lightcraft…
  • p. 39 …Influence of Lightcraft and Target Velocity on Impact Energy and Required Mass 261. Lightcraft Lightcraft Impact…
  • p. 40 …The lower mass also saves launch costs, so the total system costs less for the same…
  • p. 41 …many spacecraft that the economics of true mass production will come into play in space for…
  • p. 44 …the local vertical, with its center of mass in GEO. The Fresnel zone plate has a…
  • p. 46 …wall plug and optical efficiencies, cost, complexity, mass, and size. Free-electron lasers are another class…
  • p. 47 …P = 2000 Pa (or 0.02 atmospheres). • Mass flow rate, Q = 60 kg/sec per module…
  • p. 48 UNCLASSIFIED//509 AEEJCJOP 11£5 O.-blf + Total mass flow rate, Qtota1 = 240 kg/sec for…
  • p. 50 …sec, and 15 kg/sec of CD2 mass flow represents 2.053 x 1026 molecules/sec…
  • p. 51 …The 60 kg/sec mass flow requirement of the 3: 1 N2/C02 lasing gases means…
  • p. 53 …mass (not including the prime power and cooling systems) to achieve the low specific mass (5…
  • p. 65 …is the undulator period, mis the electron mass, and c is the speed of light. 'MeV…
  • p. 72 …The Lightcraft specific impulse is essentially infinite (several thousand seconds in rocket mode), while payload mass…
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Chapter 4: Summary of Multi-Megawatt Laser Study for
Lightcraft Propulsion Applications
SUMMARY OF LASER STUDY PERFORMED BY TEXTRON SYSTEMS
In 2002, V. Hasson (TEXTRON Systems Corporation) conducted a study of candidate
multi-megawatt laser systems for laser Lightcraft propulsion [29].
Candidate high-power/high-energy lasers identified in the study:
• Carbon Dioxide (CO2) Laser: technical issues include large wavelength and
atmospheric absorption of the laser beam.
• Carbon Monoxide (CO) Laser: technical issues include large wavelength,
atmospheric absorption of the laser beam, and toxicity of the lasing fuel (CO
gas).
• Hydrogen Fluoride (HF) or Deuterium Fluoride (DF) Laser: technical issues include
atmospheric absorption of the laser beam, corrosive lasing fuel chemicals, pulse
energy, running cost, and beam quality.
• Chemical Oxygen-Iodine Laser (COIL): technical issues include fuel chemicals,
pulse energy, and running costs.
• Bulk Slab Solid-State Laser (BSSSL): technical issues include cost, average
power, and run duration.
The first four gas dynamic and chemical laser candidates have already demonstrated
megawatt-class average beam output power. The study then reviewed the
development, testing and operational legacy of the first candidate laser technology,
which included a review of the various system architectures that use other gas mixtures
combined with CO2. The study recommended a new design for a 10 MW (beam output
power) electron gun-driven CO2/gas mixture laser because this technology does not
require additional R&D and can be implemented now. The other gases selected for the
lasing fuel are N2 and H2, which, in combination with CO2, offer superior performance
over systems using helium.
However, very recent technologically disruptive innovations led to the 10-fold increase
in the beam output power of bulk slab SSLs and their newly emergent solid-state
cousin, called high-power fiber lasers, which has made these devices more competitive
with high-power chemical and gas dynamic lasers on the basis of average beam power,
peak beam power, electrical wall plug and optical efficiencies, cost, complexity, mass,
and size. Free-electron lasers are another class of laser technology that was not
reviewed by Hasson, but recent technological innovations are accelerating their
development to the point where their present average beam output power of 20 kW will
be increased to 100 kW or higher within the next 12 to 24 months following the
publication of this report. The output beams of several of these laser devices can be
optically combined to produce a single beam with megawatt-class average output
power. It is for this reason that we will summarize their technology in Summary of
Emergent High-Power Solid-State and Free-Electron Laser Technologies section.
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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.