Experiments were conducted in 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 stabiliser having six fins disposed in a symmetrical triform arrangement. The results show that the control effectiveness increases markedly with Mach number. Trim curves are non-linear at subsonic speeds and approach linearity at supersonic Mach numbers. The results were applied to a small hypothetical missile configuration and indicate that the nose control is powerful enough to provide a terminal control capability. For the case considered, in subsonic flight the missile must fly on a near-ballistic trajectory. However, 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. Detailed control system assessments were not made. (Author)


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    Titel :

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


    Beteiligte:
    K. D. Thomson (Autor:in)

    Erscheinungsdatum :

    1983


    Format / Umfang :

    32 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch