The report represents the results of a program of design analysis and test evaluation of the feasibility of a concept to provide a flyaway capability for a crew member who has safely ejected from a damaged aircraft. The escape/rescue capability demonstrated represented essentially a configuration comprised of a rigidized, heavily loaded conical Parawing and of an instrumented test vehicle with provisions for installing a small jet engine to conduct powered flights. A series of twenty-one successful flight tests were conducted and two different configurations were flown. The ability to control the flight path of the vehicle at various wing loadings was conclusively demonstrated using manual flight controls operated from a remote radio control ground station. The use of a simple closed loop gyro stabilization system to stabilize the vehicle about the roll axis was also demonstrated. (Author)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Parawing aerodynamics

    Sleeman, Jr., W.C. / Johnson, Jr., J.L. | Engineering Index Backfile | 1963


    AERCAB Parawing Deployment and Articulation Flight Tests

    R. F. Speth / J. L. Rust | NTIS | 1971



    PARAWING AERODYNAMICS

    Johnson, J. L., Jr. / Sleeman, W. C., Jr. | NTRS | 1963


    Large parawing development project

    Clemmons, D. L., Jr. | NTRS | 1967