Civil Engineering Reference
In-Depth Information
Chapter 2
Satellite Configuration Design
Abstract This chapter discusses the process of integration of the subsystem
components and development of the satellite configuration to achieve a final layout
for a satellite; the process will be applied on a test case and it is called ''Small
Sat''. The Small Sat structural configuration is designed to accommodate all of the
mission components. All mechanical requirements are derived from the satellite's
configuration. The process used to create the satellite configuration of Small Sat is
described. It begins with mission definition, launch vehicle selection, and sub-
system identification. This is followed by a description of the satellite composition,
and the major design constraints that guide the configuration design. Then a
configuration development process is presented to create the preliminary config-
uration. Finally, the issued layout drawings and the calculated mass properties for
the developed satellite are presented.
2.1 The Process of Configuring a Satellite
The first step in designing a satellite, once its top level requirements are identified,
is to define (at least roughly) the orbit and the payload's function, field of view,
required power, mass, and size. From the payload's features, the satellite's total
mass and volume can be estimated based on the data collected from previous
missions. This information allows us to select a launch vehicle, which dictates the
allowable physical envelope of the stowed satellite.
Before we have a preliminary configuration, identifying and trading options are
begun to answer many questions related to the design process, like the method of
satellite control, the communication system, the need for a propulsion system, and
the total power estimated, which determines the solar panel surface area and the
battery size. These and many other questions in designing a satellite are not
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