Several missiles and projectiles have periods during their flight where the body is spinning and must be controlled. It has been stated that a roll stabilized autopilot may be more appropriate during this phase of the flight. This paper first examines the full nonlinear equations of motion in both the roll stabilized frame and the body axis system assuming a rigid axially symmetric body. Two and three loop autopilots are developed using an optimal control approach for a non-rolling airframe. These autopilots are examined to determine how well they are able to follow inertial commands. An extremely simplified example is presented so that the basic characteristics of the closed loop system can be examined. The results are presented and conclusions drawn. Effects of different acceleration levels, including the axial moment of inertia and very high roll rates are examined.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Control of Spinning Symmetric Airframes


    Beteiligte:
    C. P. Mracek (Autor:in) / M. Stafford (Autor:in) / M. Unger (Autor:in)

    Erscheinungsdatum :

    2006


    Format / Umfang :

    24 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Corrosion Control on Airframes

    Emerald Group Publishing | 1990


    TITANIUM IN AIRFRAMES

    KOSTOCH, F. ROBERT | SAE Technical Papers | 1953


    Elastomers and Airframes

    Evans, G.B. | Emerald Group Publishing | 1967


    Welding of airframes

    Corns, W.S. | Engineering Index Backfile | 1941


    HEAT EXCHANGERS FOR AIRFRAMES

    KOKORICH MIKHAIL / VAN HOVE BART | Europäisches Patentamt | 2025

    Freier Zugriff