Members that have more supports or constraints than the minimum
required for static equilibrium are called statically indeterminate.
They can be analyzed if a suf?cient number of additional relationships
are available. These are fundamentally similar to one another in terms
of compatibility for displacements, and are described separately
for special cases.
Statically Indeterminate Axially Loaded Members
Several subsets of these are common; three are shown schematically
in Figure 1.5.27.
1. From a free-body diagram of part (a), assuming upward forces
FA and FB at ends A and B, respectively, the force equilibrium
equation is
FA + FB ? P = 0

FIGURE 1.5.27 Statically indeterminate axially loaded members.
The displacement compatibility condition is that both ends are ?xed, so
? A/B = 0
Then

Alternatively, ?rst assume that FB = 0, and calculate the total downward
displacement (tensile) of the free end B. Then calculate the required force
FB to compressively deform the rod upward so that after the superposition
there is no net displacement of end B. The results are the same as above
for elastically deforming members.
2. Constrained thermal expansion or contraction of part (b) is handled as
above, using the expression for thermally induced deformation,
?r =? ? TL
where ? = linear coef?cient of thermal expansion
?T = change in temperature
3. The force equilibrium equation of part (c) is
P?FA ? FB = 0
Here the two different component materials are deforming
together by the same amount, so

providing two equations with two unknowns, FA and FB.
Note that rigid supports are not necessarily realistic to assume
in all cases.
Statically Indeterminate Beams
As for axially loaded members, the redundant reactions of beams
are determined from the given conditions of geometry
(the displacement compatibility conditions). There are various
approaches for solving problems of statically indeterminate beams,
using the methods of integration, moment-areas, or superposition.
Handbook formulas for the slopes and de?ections of beams are
especially useful, noting that the boundary conditions must be well
de?ned in any case. The method of superposition is illustrated
in Figure 1.5.28.

FIGURE 1.5.28 A statically indeterminate beam.
Choosing the reaction at C as the redundant support reaction
(otherwise, the moment at A could be taken as redundant),
and ?rst removing the unknown reaction Cy, the statically
determinate and stable primary beam is obtained in Figure 1.5.28b.
Here the slope and de?ection at A are both zero. The slopes
at B and C are the same because segment BC is straight. Next the
external load P is removed, and a cantilever beam ?xed at A and with
load Cy is considered in Figure 1.5.28c. From the original boundary
conditions at C, y1 + y2 = 0, and the problem can be solved easily
using any appropriate method.
Statically Indeterminate Torsion Members
Torsion members with redundant supports are analyzed essentially
the same way as other kinds of statically indeterminate members.
The unknown torques, for example, are determined by setting up a
solution to satisfy the requirements of equilibrium (?T = 0),
angular displacement compatibility, and torque-displacement
(angle = TL/JG) relationships. Again, the boundary conditions must
be reasonably well de?ned.
Buckling
The elastic buckling of relatively long and slender members under
axial compressive loading could result in sudden and catastrophic large
displacements. The critical buckling load is the smallest for a given
ideal column when it is pin-supported at both ends; the critical load is
larger than this for other kinds of supports. An ideal column is made
of homogeneous material, is perfectly straight prior to loading,
and is loaded only axially through the centroid of its cross-sectional
area.
Critical Load. Eulers Equation
The buckling equation (Eulers equation) for a pin-supported
column gives the critical or maximum axial load Pcr as

where E = modulus of elasticity
I = smallest moment of inertia of the cross-sectional area
L = unsupported length of the pinned column
A useful form of this equation gives the critical average stress prior
to any yielding, for arbitrary end conditions,

where r = ?I/A= radius of gyration of cross-sectional area A
L/r = slenderness ratio
k = effective-length factor; constant, dependent on the end constraints
kL/r = effective-slenderness ratio
The slenderness ratio indicates, for a given material, the tendency for
elastic buckling or failure by yielding (where the Euler formula is not applicable).
For example, buckling is expected in mild steel if L/r is approximately 90
or larger, and in an aluminum alloy if L/r > 60. Yielding would occur ?rst at
smaller values of L/r. Ratios of 200 or higher indicate very slender
members that cannot support large compressive loads.
Several common end conditions of slender columns are shown
schematically in Figure 1.5.29.

FIGURE 1.5.29 Common end conditions of slender columns.
Secant Formula
Real columns are not perfectly straight and homogeneous and are likely
to be loaded eccentrically. Such columns ?rst bend and de?ect laterally,
rather than buckle suddenly. The maximum elastic compressive
stress in this case is caused by the axial and bending loads and is
calculated for small de?ections from the secant formula,

where e is the eccentricity of the load P (distance from the neutral
axis of area A) and c is measured from the neutral axis to the outer
layer of the column where ?max occurs. The load and stress are
nonlinearly related; if there are several loads on a column, the loads
should be properly combined ?rst before using the secant formula,
rather than linearly superposing several individually determined stresses.
Similarly, factors of safety should be applied to the resultant load.
Inelastic Buckling
For columns that may yield before buckling elastically, the generalized
Euler equation, also called the Engesser equation, is appropriate.
This involves substituting the tangent modulus ET (tangent to the
stress-strain curve) for the elastic modulus E in the Euler equation,

Note that ET must be valid for the stress ?cr, but ET is dependent on
stress when the deformations are not entirely elastic. Thermal or
plastic-strain events may even alter the stress-strain curve of the
material, thereby further changing ET. Thus, Equation 1.5.49 should
be used with caution in a trial-and-error procedure.