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)
Parawing Aercab Feasibility Flight Demonstration
1971
309 pages
Report
No indication
English
Aircraft , Aeronautics , Parawings , Ejection seats , Jet fighters , Aerospace systems , Design , Feasibility studies , Jet engines , Aerodynamic characteristics , Flight control systems , Thrust , Communication and radio systems , Telemeter systems , Gyro stabilizers , Parachutes , Ejection , Flight testing , Aercab(Aircrew escape rescue capability) , Aercab self rescue system , Aircrew escape rescue capability , Sailwings , S/L change 8418
Engineering Index Backfile | 1963
|AERCAB Parawing Deployment and Articulation Flight Tests
NTIS | 1971
|NTRS | 1963
|Large parawing development project
NTRS | 1967
|