AAWSAP DIRD, Laser Lightcraft Nanosatellites, November 2010

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Froning and Davis [26] also determined that the ground-based laser selected (). = 1.62
µm, 10 MW radiated power, 10 m diameter aperture) would enable a Lightcraft takeoff
mass of 8 kg and Lightcraft propellant mass of 4 kg. Therefore, this would allow
approximately 4 kg of mass to be placed into orbit with the selected ground-based
laser. And vehicle synthesis work determined that the remaining masses for the
Lightcraft airframe, propulsion, and control systems would be 0.63 kg, 0.46 kg, and
0.45 kg, respectively, together with a 30 percent contingency (of 0.47 kg).
Takeoff Mass =4.0 kg
Frontal Area= 0.78 m1
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Takeoff Mass =8.0 kg
Frontal Area "' .096 m2
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Half-Apell Angle ofForebody (degrees)
Figure 9. Lightcraft Vehicle Evolution (in 3 steps) 1261.
Froning and Davis [26] further indicated that small COTS chemical propulsion systems,
with sufficient thrust, would be about a factor of 7 to 12 heavier than those needed to
meet Lightcraft orbit circularization needs. However, such mass reductions were
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