System 112A - The Black Vault

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SECRET
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Testing hal! been completed to determine the
feasibility of using magnetic tubing as a shield for
mlsslle wiring. Test results show that the voltage
induced in a wire as a resultof electromagneUc fields
1s negligible.
An Investigation resulted In Increasing the dl­
X'uenslona of L'le alternator frame so that the T.K.M.
Elect:i"lc Corporation can meet the output requirements
for this unit. Revised drawings reflecting Increased
dimensions were forwarded to the vendor_ The first
prototype of the T .K_M_ alternator Is scheduled for
completion during the next quarter; the unit will be
subjected to thorough evaluation after delivery to Bell
Aircraft.
Electrical evaluations of teflon wire, treated
with an etching agent of metallic sodium and liquid
ammonia, have indicated that the adherence properties
of the \.'ire In conjunction with flexible potting compound
Is satisfactory.
C. SPECIF1C SYSTEM IMPROVEMENTS
1. BoattaU Redesign
Work on the redesign of the circular aft body
and engine cowllng Is approximately 80% complete.
Further engineering of this item was terminated
during the quarter.
2. Thin-Wing Design
The redesign of the aft thin wing (4% root sectlon)
has been terminated.
D. WEIGHTS REPORTS
During this quarter, weights reports were prepared
for mlssUes Ncs. 84 and 95. The Bell Aircraft report
numbers are 56-942-121 and 66-942-001, respectively.
E. FLUTTER ANALYSES
Reports are beingprepared to summarize the flutter
studies performed for the aft horizontal surface and
the rudder. These reports compare computed with test
modes and frequencies.
Tests to determine experimentally the dynamiC
characteristics of the airframe In the pitch, roll, and
yaw planes are essentially complete. These dynamic
characteristics are obtained by feeding a sinusoidal
Input to the controls and recording the response from
several points on the airframe. The experimental
data, together with discussion, associated stability
anaiyses, and conclusions, are being assembled intoa
report.
The program of measuring the free play of the control
surfaces Is continuing. Data have been examined
from the flights of seven missiles wlthknownamounts
of free play. While In some cases the free play exceeded
that allowed in ParagraphA-17 of Specification
66-947-011, no detrimental effects on flutter stabU1ty
have been Indicated. Although the free play measured,
using the regular procedure, compared satisfactorily
with the free play determined during the test of the
controls (see Quarterly Report 56-981-021-45), improvements
were noted which increase the reliability
of the measurements by compensating for the effects
of elasticity and friction. A reVisedprocedure will be
used to make all future free-play measurements.
2
propulelon eyet_""
A. SYNOPSIS
The GAM-63A is powered by a liquid-propellant
rocket propulsion system incorporatinga turbine pump
drive unit. The thrust rectUired to propel the missile
to supersonic speed is provided by three identical
chambers that develop 12,000 pounds thrust at an altitude
of 40,000 feet. 1'he liquid propellants are pumped
to the thrust chambers by a gas-driven turbine pump
which &1so furnishes auxiliary power to drive the
hydraulic pump and alternator through suitable takeoff
pads. The turbine pump, utilizing fue iiil:!.\e ~::'C "
pellanUi as the rocket engine, may be operated Inde-
pendently of the thrust chambers by passing the
pumped propellants back to the tanks. Thus, the
tul'blne pump assembly continuE:': t., furnish the required
electric and hydrauUc power during peri0