System 112A - The Black Vault

~-------------------.----~.--------~------------------------~--~,--~------,
..
SECRET
---------------------------------------
4 oontrol .ylS~~rn
".
A. SYNOPSIS
Following early design studies that included experience
gained from the Shrike missile program,
laboratory development of the autopilot systemfor the
missUe portion of the Rascal Weapon System was put
on a full-scale basis in January 1951. In September
of 1952, the first Rascal missile was dellvered to
HADe for filght testing.
Th~ autopilot systems for the first Rascal misslles
were Similar to that used in the Model 59 Shrike
missUes. Deslgr. of the autopllotfor subsequent GAM-
63's, however, show .& significant increase in complexity
when such cclpablllties as acceleration limiting,
guidance loop tie-in, antenna stab1llzatlon, and
altltude control were added. These features were
included in the basic Model B and D configurations
(missiles 11 through 35). The Model F configuration
of subsequent misslles is further modified to accommodate
the inertial range-computing system designed
to meet the requirements of the weapon system.
With the development of this basiC autopUot system,
major emphasis has been shifted to the simplification
of products and to the improvement of reUab1l1ty
;md design characteristics. This program is
proceeding satisfactorily. Concurrently with autopilot
development, a series of terminal guidance control
studies was conducted and this contributed significantly
to the ovar-aU design of the autopilot system.
The two main servo systems of the GAM-63A are
the servopUot and the antellJUl stab1l1zatlon systems.
These systems utll1ze electronic amplifiers, an azimuth
computer, potentiometers, hydraulic valves,
actuators, a single-axis stablllzed platform. and
associated hydraulic plumbing and electrical wtr ~ng.
The power supply is common to both systems.
The servopllot stablllzes the GAM-63A missile
about its three axes: longitudinal (roll), lateral
(pitch), and vertical (yaw). The rollsystemmaintalns
the lateral axls of the missile horizontal throughout
its flight. During portions of the flight, the pitch and
yaw systems are programmed and receive guidance
commands which direct the missile to the target.
The antenna stablllzatlon systems perform three
functions: (1) maintain the search anteMa horizontal
about the pitch axls with respect to the earth's
horizon (since the search antenna is fixed to the rollstabllized
a!rfl"ame, a separate antenna roll servo is
Dot required); (2) maintain the rotating searchantenna
at a constant angular velocity in space; and (3) orient
the relay antenna in pitch so that its major lobe is
aimed toward the director aircraft.
B. FLIGHT CONTROL SYSI'EM
The environmental re-evaluatlon program on the
Rascal fllght control system and the inertial rangecomputing
system is continuing.
Thus far, 1612 environmental tests had been completed
on electronic and hydraulic components. Of the
units presently IUtdergoing tests, 31 units have completed
three cycles, 9 units have completed two
cycles, and 14 units have completed one cycle. The
remaining units art'! in various stages of testing.
The mechanical coupling tests on missUe No. 46
were completed during this quarter. A report ill being
written to summarize this activity.
The Investigation of the spin drive system for the
misslle search antenna has proceeded to the point
where revised specifications have been prepared to
ensure a minimum of difficulty with this system tn the
future.
Reliabll1ty testlDg of the PhaseI repackaged amplifiers
has been completed at Federal Telecommunication
Laboratories. Preliminary results indicate that
the ampilliers performed rellably during these tests.
Development work on the Phase n redesign of the
fUght control system was carriedto a conclusion during
this quarter. No further work is pla.nned on this program
untll a specific missUe effectivity is establlshed
for the redesigned equipment. Reports on the actlvity
have been forwarded to the WSPO.
An analytical report on the platform levellng system
is nearly complete.
The feasibUity of transistorizing the Rascal fUght
control system is being studied. This work has not
yet progressed to the point where specifiC conclusions
can be made.
C. SERVO VALVES
Development work on the double-nozzle, dryfirst-stage
servo valves for the Phase n redesign
effort is being held in abeyance until a specific mlasUe
effectivity is establlshed for the new servo valves.
D. HYDRAULICS
The eearch for more-rellable fUters, accumulators,
and seals Is contlnulng.
R,~port No. 56-981-021-48
!iECRET
37
--t
I