The Mach number range 0.80 to 2.00 on a tube launched missile configuration with a deflectable nose control and a wrap around fin stabilizer with six fans disposed in a symmetrical triform arrangement were examined. It is shown that the control effectiveness increases markedly with Mach number. Trim curves are nonlinear at subsonic speeds and approach linearity at supersonic Mach numbers. A missile configuration indicates that the nose control is powerful enough to provide a terminal control capability. In subsonic flight the missile must fly on a near ballistic trajectory. In supersonic flight the control is powerful enough to permit horizontal flight above M = 1.5 while retaining a sufficient reserve to provide a terminal correction capability.


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    Title :

    Wind Tunnel Tests on a Tube-Launched Missile Configuration with a Deflectable Nose Control and a Novel Wrap-around Fin Stabiliser


    Contributors:

    Publication date :

    1983


    Size :

    36 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English