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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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which usually result in mirror tilts ( ~ 0 to 400 micro-radians) and drastically
reduced beam power, thus maintaining beam power output at maximum design
value.
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Figure 32. High-Power FEL Optical Resonator (courtesy of the Naval Post-Graduate School
FEL Lab).
ESTIMATED PAYLOAD COST FOR LIGHTCRAFT LAUNCH USING A 10
MW BSSSL, HPFL, OR RBFEL SYSTEM
No detailed Lightcraft nano- or pico-satellite payload launch cost estimates can be
performed at this time because the high-power solid-state and FEL laser devices are
emergent technologies still under development and testing; operational deployment is
expected to take place within the next two to five years depending on near-future
funding and programmatics. However, Table 1 shows that the average cost to launch a
laser-propelled Lightcraft (including payload) to LEO is $3,052 per kg. This figure was
based on operations, life-cycle, and maintenance costs plus the cost of using a high-
power bulk solid-state laser system that is 50% shared with another user.
The cost estimates shown in Table 1 were compiled in 2003, so this (average) launch
cost estimate will likely go down significantly at present (possibly by 20% or more) due
to significantly increased system efficiencies realized within each of these emergent
advanced laser technologies, reduced system costs due to widespread acceptance,
operational deployment along with dual-use commercialization, and system costs that
trend downward as technology matures over time, etc. IPG Photonics sells their
industrial HPFL systems (e.g., see Figure 27) for prices ranging from $50,000 to
$500,000 depending on the beam power (higher beam power = higher price) and
system application. Based on these factors, a simple back-of-the-envelope cost
estimate for Lightcraft launch of a payload to LEO is approximately $100 to $300 per
kg,~-. while the average cost to launch a laser-propelled Lightcraft (including payload) to
LEO will be approximately $800 to $2,000 per kg which includes the operations, life-
cycle, maintenance, and laser system costs. An in-depth study will be needed to obtain
more precise cost estimates for Lightcraft launch using BSSSL, HPFL, and RBFEL
systems.
HIGH ENERGY LASER BEAM CONTROL
··costs could be reduced to as low as $20 per kg of payload if Buckytubes are used to construct the Lightcraft.
62
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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.