LUNAR EXPEDITION PLAN

4.2.4 FLIGHT VEHICIB ?OWEfi
4.2.4.1
Electrical pover will be required to operate the Lunex
Re-entry Vehicle subsystem such as life support, navigation
and guidance. Instrumentation, and communications. She pover
requirement for these subsystems has been analysed and determined
to je approximately 3 kv average during a ten-day
manned trip to the moon and return. Jteak power requirements
will be approximately 6 lev.
4.2.4.2
Solar, nuclear, and chemical powered systems were evaluated
against these requirements. Vhile all of these systems
may be capable of meeting these requirements the chemically
powered systems have been selected for early adaptation Into
the program. Specifically, fuel cells and turbines, or positive
displacement engines appear to offer the most advantageous'
solution. The final selection will be made during the final
re-entry vehicle design when a detailed analysis of the trade'
offs between various available systems considering relative
velgit, efficiency, reliability, and growth potential la
available. The optimum system may be a combination of fuel
cells and chemical dynamic systems with one system specifically
designed to supply peak demand. MLth this approach the system
to provide peak load capacity, will also provide backup power
in the case of equipment malfunction during a large part of the
mission. A battery supply may be used to furnish emergency
power required for crev safety during critical periods in the
flight.
4.2.4.3
Present level of technology is such that a satisfactory
flight vehicle pover system will be available when required for
the LUNEX mission. Additional development effort should be
Initiated In certain specific areas, such as a reliability
evaluation program for fuel cells and an Investigation of the
problems of operating chemical dynamlc^systeafi la-a-zero-**0"
environment. "
Close coordination must also be maintained with the manager
of project 3145 (U) Energy Conversion, to Insure the availability
of the required secondary power sources.
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