The fourth phase is given of a continuing program to develop the means to stabilize and control aircraft without moving parts or a separate source of power. Previous phases have demonstrated the feasibility of (1) generating adequate control forces on a standard airfoil, (2) controlling those forces with a fluidic amplifier and (3) cascading non-vented fluidic amplifiers operating on ram air supply pressure. The foremost objectives of the fourth phase covered under Part I of this report were to demonstrate a complete force-control system in a wind tunnel environment and to measure its static and dynamic control characteristics. Secondary objectives, covered under Part II, were to evaluate alternate configurations for lift control. The results demonstrate an overall response time of 150 msec, confirming this technology as a viable means for implementing low-cost reliable flight control systems.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Wind tunnel tests of the dynamic characteristics of the fluidic rudder


    Contributors:

    Publication date :

    1976-12-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Development of a fluidic rudder

    Belsterling, C. A. | NTRS | 1976


    Development of a fluidic rudder

    BELSTERLING, C. | AIAA | 1976


    Design and test of the 172K fluidic rudder

    Belsterling, C. A. | NTRS | 1978


    Design and Test of the 172K Fluidic Rudder

    C. A. Belsterling | NTIS | 1978