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.


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    Title :

    Missile Control System Design and Specification for a Long-Range Supersonic Cruise Missile


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    Aerospace Technology Conference and Exposition ; 2005



    Publication date :

    2005-10-03




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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