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THE NATIONAL aeronautics and Space Administration requirements for the Delta Space Research Vehicle imposed conditions of accuracy, flexibility, and an extended period of operation never attained before by United States space vehicles. In order to meet these requirements a new flight controller had to be designed and manufactured. This new design included other salient features; such as: minimum weight and power requirements, a minimum number of relays, and a high degree of reliability. The flexibility in the design had to allow for interchangeability of components or subsystems with a minimum of time and effort due to changes in the flight sequence or trajectory that could occur shortly before the vehicle is launched.