Abstract
Solid Rocket Motors (SRMs) serve as the propulsion
devices for satellite-launchers. High stiffness values, high
strength to weight ratios and greater mechanical/structural
properties of composite materials make composite SRMs more
efficient than metallic SRMs. The disadvantage of composite
SRMs lies in the joining of segments. Segmented SRMs are
essential when requirement is of large size and high payload. In
segmentation the reliability of the whole structure depends upon
the efficiency of the segment joint. Therefore the joint must be
proficient enough to withstand the structural and dynamic loads.
The progressive damage analysis is used to evaluate the
mechanical performance of composite structure, the damage
mechanism and its progression. Internal combustion of exhaust
gases creates hoop stresses inside the SRMs case. These hoop
stresses induce the bending moments in the joint section of
segmented SRMs. In this study the various segment joint
parameters are analyzed i.e. number of pins, pin material and
pin diameter. The effect of each parameter on joint strength of
SRM is evaluated to conclude the optimum joint parameters.
After the selection of optimum joint parameters, the progressive
damage analysis is carried out to analyze the behavior of
composite segment joint against the proposed operating
conditions. The proposed joint design is analyzed at different
operating pressures to find out the critical failure mechanism of
composite SRM.
Samia Fida, Asif Israr. (2017) Design and Analysis of Case to Case Segment Joint for Aerospace Applications, Journal of Space Technology , Volume 7, Issue 1.
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