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This paper presents an overview of two long-range supersonic cruise missile prototypes and the preliminary design of the Missile Control System (MCS). The MCS provides command and control of all flight-critical subsystems. It is responsible for aerodynamic effector, propulsion flowpath, and embedded digital engine control. The flowpath control system, based on the SR-71flowpath design, includes a movable inlet spike, engine bypass flow control, and ram burner inlet flow valve. The engine controller provides all High Speed Turbojet engine effector commands: variable inlet guide vanes, fuel pumps, and movable exhaust spike. System development leverages model-based specification, design, integration, and verification & validation testing.