We derive optimum values of parameters for laser-driven
flights into low Earth orbit (LEO) using an Earth-based
laser, as well as sensitivity to variations from the optima.
These parameters are the ablation plasma exhaust velocity
vE and specific ablation energy
Q*, plus related quantities such as momentum
coupling coefficient Cm and the
pulsed or continuous laser intensity that must be delivered
to the ablator to produce these values. Different optima are
found depending upon whether it is desired to maximize mass
m delivered to LEO, maximize the ratio m/M
of orbit to ground mass, or minimize cost in energy per gram
delivered. Although it is not within the scope of this report
to provide an engineered flyer design, a notional, cone-shaped
flyer is described to provide a substrate for the discussion and
flight simulations. The flyer design emphasizes conceptually
and physically separate functions of light collection at a distance
from the laser source, light concentration on the ablator, and
autonomous steering. Approximately ideal flight paths to LEO are
illustrated beginning from an elevated platform. We believe LEO
launch costs can be reduced 100-fold in this way. Sounding rocket
cases, where the only goal is to momentarily reach a certain
altitude starting from near sea level, are also discussed.
Nonlinear optical constraints on laser propagation through
the atmosphere to the flyer are briefly considered.