Literature Review - Finite Element Analysis for Satellite Structures - page 9

Fig. 1.1 Iso grid Structure

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1.4.2 Multifunctional Structures

Multifunctional structure (MFS) technology includes several functions into the
primary structure of a spacecraft. The main objective of these members is to
minimize parasitic mass by incorporating chassis, cables, connectors, and thermal
control components into the satellite primary structural walls. The walls are typ-
ically constructed out of fiber composites or sandwich panels, and the electrical
components are embedded during manufacturing. The traditional ground plane/
printed circuit board design is performed by copper/polymide (CU/PI) patches,
multi-chip modules (MCMs), and the current cabling functions are performed
using CU/PI flexible jumpers. The design allows for an easily accessible,
removable, and modular electrical system. The benefits of this technology include
a 70 % reduction in electronic enclosures and harnesses, a 50 % reduction in
spacecraft volume required for these conventional components, a reduction in
labor required for spacecraft assembly, and an extremely robust system with wide
applicability to several missions. Lockheed Martin has recently proven the tech-
nology as an experiment aboard the Deep Space 1 mission.

1.4.3 Isogrid Structures

Isogrid uses an array of equilateral triangle cutouts to increase the stiffness per
weight of a structure. The pattern may be manufactured by machining a metallic
panel, or it may be constructed using fiber composite materials. The concept began
in the early 1960s using metal structures and development continues today with
research focusing primarily on composite applications (Fig. 1.1 ).