S
8.2 ENGINEERING AND OPERATION OF SAMPLER AND INSTRIMENTIATIN BOCETS
8.2.1 Vehicle Description
Figure &.1 shows rhe priscinal feacures of Soth the sicgle- and the reostage instrment carriers.
Both vehicles are 16 inches in dizeter.
single-stage vehicle is approximately 153.5 inches long awerall.
length, payload space is available aft as far as Station 65.5
vehicle is approxinately 233.3 inches long overall.
aft as far as Station 60.5.
The
Of this
The two-stage
Payload space is svailable
The single-stage vehicle end the second stage of
the two-stage vebicle are each made up of four major asseublies:
(1) nose as-
sembly, (2) midsection coapartaent, (3) rocket engine, and (%) tail asseably.
The recoverrble nose assembly, which is identical on both instmoectation
vehicles, extends aft as far as Staticu 53.5
A bulkhead at Station 48.5 cakes
the instrument compartaent ahead of that station pressure tight.
The compart-
ment between che pressure bulxiead and Station 53.5 houses parachute, dyemarker containers, and electrical junction boz.
The sidsection extends from Station 53.5 to Station 65.5 on the singleStage vehicle.
On the two-stage carrier it extends only ta Station 60.5.
This
compartaent is used for carrying instrumentation, ballast for altitude control,
or both.
Ir is not pressurized and is mt recoverable.
Oa the single-stage
vehicles the midsection compartment is used for carrying ballast only.
The
rockets with predicted apogees of 222,000 and 242,000 feet (see Fig. 8.2) bave
X-ray and thermal instrumentation as well as a small amount of ballast mounted
in this cogpartment.
The recoverable nose assembly {s held to the midsection by a ring which
engages a circumferential groove around each of the two parts.
The ring is
held together at two diametrically opposite locations by pins which, at the
separation signal, are driven out of the ring by pressure scquibs.
the ring free to fall away.
This leaves
The ring parts are thrown clear by centrifugal
force resulticg from the spin of the vehicle, leaving the nose free to fall.
Nose separation occurs as a result of aerodynamic and isertial loads.
The
parachute is deployed by oears of a static line which is of sufficient length
to assure that the noose is clear of the remainder of the webicle.
with che exception of aodifications made to the case and nozzle to reduce
weight and adapt it co this particular application, the IX-52 (see Section 8.1.2)
ie)
“J
a