System 112A - The Black Vault

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BELV~
CDmunD.
In an effort to improve the reUabUltyand Ufe
of the RCA AI016 relay magnetron, conferences have
been held w~th the vendor and a program ~:. being
finalized to accompllsh this goal. Under present
conditions, the more reliable magnetrons received
from the vendor are sent to HADC in support of the
flight test program, and it Is sometimes necessary to
use substandard tubes at the Wheatfield facUlty for
Initial teating of the radio repeater set. The ferrite
load isolator being added between the magnetron and
its load is expected to Improve the operaUngenvlronment
of the tube.
Marginal operation has been experienced with
the saturated output level of the I-f amplifier. A
minor circuit change has been processed to provide
an ample safety factor.
Design of the case assemblies for the comm3.ll.d
signal decoder and the radio repeater has been modified
to improve performance and to facllitate manufacture.
Drawll'.g changes are being processed.
C. NONEMANATING GUIDANCE
Inertial P..ar.g~-Comput!.ng System (IRCS)
The IRCS measures range in the horizontal plane
in the direction of the longitudinal axis of the missile.
Directional cOhtrol Is maintained by the autopilot
keeping the missile aligned to a gyroscopic reference
heading.
An accelerometer Is oriented on the stable platform
so that It senses acceleratiolUl along the longitudinal
axis oi the missile. The output is double-Integrated
and compared with the I,nlttal range~to-go valve,
thereby giving an instantaneous range-to-go value.
This output signal Is compared with a preset voltage
corresponding with the desired dive initlation point In
the dive angle computer. Upon COincidence, a dive
command is given to the pitch autopllot and a signal
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i8 sent to turn on the search radar in the nose of the
missile.
Accurate Information on range-to-go and velocity
from the director aircraft navigation system is transmitted
to the IRCS prior to launch. With this information,
the platform Is leveled and the necessary inittal
conditions are Inserted into the Inertial system of the
missile.
An Improved sensitive relay for the dive angle
computed proved satisfactory during evaluation tests.
The relay has since been incorporated In production
assemblies.
Prl;)l1mlnary evaluation of an Improved chopper has
indicated that this unit I) satisfactory for use in the
range and velocity computer-b. Further evaluation is
required for adequately qualifying this new chopper.
A preIlmlnary working model of the repackaged
computer for the IRCS Is undergoing tests. Vibration
testmg haa indicated that the unit is structurally
satisfactory. This repackaging will provide improved
assembly techniques, ease of testingandmaintelWlce,
and operational rellabiUty under extreme environmental
conditions.
Because of the low rellabllity of the cl-c fllament
supply procured from an outside vendor, Bell Alrcraft
designed and developed a filament supply to b·! used
as a direct replacement. Several vendors have been
asked to fabricate a filament supply with the same
characteristics as the Bell design. Samples evaluated
thus far have failed to qualify. One vendor Is redeSigning
a fUament supply and w1ll furnish samples
for evaluation.
Fluid leakage from the accelerometer used in the
IRCS has been investigated. Awltable sealing method
has been developed and referred to the vendor for use
on future units.
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