Numerical optimization was employed on the Apollo Command Module to
modify its external shape. The Apollo Command Module (CM) that was
used on all NASA human space flights during the Apollo Space
Program is stable and trimmed in an apex forward (alpha of
approximately 40 to 80 degrees) position. This poses a safety risk
if the CM separates from the launch tower during abort.
Optimization was employed on the Apollo CM to remedy the
undesirable stability characteristics of the configuration.
Geometric shape changes were limited to axisymmetric modifications
that altered the radius of the apex (R(sub A)), base radius (R(sub
O)), corner radius (R(sub C)), and the cone half angle (theta),
while the maximum diameter of the CM was held constant. The results
of multipoint optimization on the CM indicated that the cross-range
performance can be improved while maintaining robust apex-aft
stability with a single trim point. Navier-Stokes computations were
performed on the baseline and optimized configurations and
confirmed the Euler-based optimization results. Euler Analysis of
ten alternative CM vehicles with different values of the above four
parameters are compared with the published experimental results of
numerous wind tunnel tests during the late 1960's. These
comparisons cover a wide Mach number range and a full 180-degree
pitch range and show that the Euler methods are capable of fairly
accurate force and moment computations and can separate the vehicle
characteristics of these ten alternative configurations.
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