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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    Titel :

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


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:

    Kongress:

    Aerospace Technology Conference and Exposition ; 2005



    Erscheinungsdatum :

    03.10.2005




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




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