Abstract
The control system adopted for L-SAT is based on a zero-momentum concept relatively insensitive to spacecraft configuration changes. This flexibility is further enhanced by the use of a microprocessor based controller. The overall AOCS configuration adopted is described, the theoretical design aspects outlined and the functions and implementation of the controller discussed. The subsystem electronic configuration concentrates the majority of control sequence algorithm implementation, telemetry, telecommand and power control into the controller. This unit communicates to other subsystem equipments through use of a high reliability serial data bus. A similar data bus is used internally in the controller providing a highly modular design concept which enables a wide range of applications to be met using the flexibility of software.
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