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of pressure loads. The idealized model used in
this calculation is shown in Fig. 1.1.3, and the
net pressure loads at various points are indicated.
This model represents approximately the cross
section indicated in Fig. 1.1.4. It includes some
of the longest spans which appear in the design,
and the results obtained from this model are there-
fore conservative.
The configuration of Fig. 1.1.3 was analyzed
by writing the deflection equation for each member
in terms of its load and edge conditions and solving
the resulting system of eleven simultaneous equa-
tions on the Oracle. The results were obtained
in terms of the moments and reactions at the joints
and edges of the members. The stresses due to
these loads were then computed. The largest
stress, as indicated on Fig. 1.1.3, was found to
be 2100 psi. Since the highest temperature which
will occur in the north-head structure during full-
power operation will be approximately 130O0F,
this 2100-psi stress value is to be compared to
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PERIOD ENOlNC JUNE 10. 1956
the creep properties of lnconel in the fuel mixture
at about 1300OF. Creep tests have indicated that
the tensile stress required to produce rupture in
1000 hr at 1300°F is about 10,000 psi. The design
criterion for creep which has been selected for
the ART requires that the total deformation in
any member not exceed 0.2% strain in 1000 hr,
At 1300OF in the fuel mixture this corresponds to
a tensile stress of about 2000 psi.
The experimental program, designed as a check
on the calculations for the north-head structure,
is under way at the University of Tennessee. It
is believed that the combined results of the ana-
lytical studies and the model tests will reveal
any defects in the proposed design.
NortbHead Thermal Stress
With the completion of the analysis for the
mechanical stresses in the north-head structure,
attention is now being directed to the determina-
tion of the thermal stress distributions. For this
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bmt.v.
ORNL-LR-WIG 44945
Fig. 1.1.3. Idealized Configuration of North-Head Composite Structure (Section A-A of Fig. 1.1.4).
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