  Lunar explorations have provided us with information about its abundant
resources that can be utilized in orbiting-resource depots as lunar-derived
commodities. To reduce the energy requirements of a launcher to send these
commodities from the lunar surface to the space depots, this paper explores the
application of the electromagnetic acceleration principle and provides an
assessment of the actual technical characteristics of the launcher's
installation to ensure the acceleration of a payload with a mass of 1,500 kg to
a speed of 2,200 m/s (circumlunar orbit speed). To fulfill a lightweight (fewer
materials and less energy) support structure for the electromagnetic launcher
with strength requirements, the tensegrity structure minimum mass principle
without global buckling has been developed and applied to support the
electromagnetic acceleration device. Therefore, this paper proposes and
develops a minimal mass electromagnetic tensegrity lunar launcher. We first
demonstrate the mechanics of launcher and payload, how a payload can be
accelerated to a specific velocity, and how a payload carrier can be recycled
for another launch. Then, a detailed discussion on the lunar launch system,
procedures of propulsion, the required mass, and energy of the launch barrel
are given. The governing equations of tensegrity minimal mass tensegrity design
algorithm with gravity and without global buckling. Finally, a case study is
conducted to show a feasible structure design, the required mass, and energy.
The principles developed in this paper are also applicable to the rocket launch
system, space elevator, space train transportation, interstellar payload
package delivery, etc.
