Exploring the Unknown: Selected Documents in ... - The Black Vault

500
Project Apollo: Americans to the Moon
Rendezvous Concepts
Order of Preference
by each committee member
Total
A B C D E F
Earth RV with 5-7 C-2’s 4 4 4 6 3 3 24
Earth RV with 2-3 C-3’s 2 1 1 1 2 1 8
Lunar RV with 1 C-3 5 3 2 3 4 4 21
Earth and Lunar RV with C-2’s 6 6 3 5 5 5 30
RV on Lunar Surface 3 5 6 4 1 6 25
Earth RV with NOVA and C-l 1 2 5 2 6 2 18
The concept of a low altitude earth orbit rendezvous utilizing Saturn C-3’s
is a clear preference by the group.
[Sections III-VI not included]
[ 26]
Mission staging by rendezvous offers two advantages of particu lar
significance to such large, complex, and long-range missions as a manned lunar
landing. Because both future payload requirements and vehicle capability are
uncertain at best, the ability to increase payload by adding a vehicle to the
operation reduces the critical dependance [sic] of future mission capability on
decisions relating to launch vehicle design and development. The inherently
smaller vehicles associated with this method also permit the development of
effective and efficient launch vehicles with engines currently in development.
Of the various orbital operations considered, the use of rendez vous
in earth orbit by two or three Saturn C-3 vehicles (depending on estimated
payload requirements) was strongly favored. This preference stemmed largely
from the small number of orbital operations required and the fact that the C-3 is
considered an efficient vehicle of large utility and future growth.
The rendezvous technique itself, in terms of launch operations, guidance
and control, and orbital operations, is considered feasible of development within
the time period of interest. Some justification for this point of view is found in both
current technology and in the fact that many of the technological advancements
required for the lunar landing and take-off operations are applicable to the
rendezvous with an artificial satellite.
[27]
The principal difficulties involved in the development of a new
4,000,000 pound RP-LOX engine for a NOVA vehicle are associated with size and
the development time span required through PFRT is estimated at 6 years. If a
NOVA vehicle incorporating a new large engine development is contemplated, the
Phoenix concept possesses sufficient attractive features to warrant serious study.
The utiliza tion of pressurized storable propellants for a large first-stage engine offer