Accession Number : AD0273626


Title :   INVESTIGATION OF ESCAPE CAPSULE SYSTEMS FOR MULTI-PLACE AIRCRAFT. PART II. PRELIMINARY DESIGN AND WIND TUNNEL TESTING OF AN INDIVIDUAL ESCAPE CAPSULE


Corporate Author : GOODYEAR AEROSPACE CORP AKRON OHIO


Personal Author(s) : MILHOAN,F M ; VORACHEK,J J ; D'ALLURA,J


Report Date : Dec 1961


Pagination or Media Count : 1


Abstract : Design and dynamic model and wind tunnel model testing is reported for an individual escape capsule as part of a program for the investigation of escape capsule systems for a hypothetical multi-place aircraft. The capsule provides safe escape over an aircraft performance envelope having a maximum equivalent airspeed of 800 knots through an altitude range from sea level to 55,000 ft and a Mach number of 4.0 from 55,000 to 100,000 ft with a flight duration of 30 hr. The preliminary design is described. Results from stress and weight analyses are included. A preliminary performance and stability analysis of 3 capsule stabilization systems, including fins, boom-balloon configurations, and trailing drag bodies, was made, and a system comprised of a variable sized inflatable drag body was selected and further analyzed. Data used for the analysis was obtained from quarter-scale model freeflight tests and transonic and supersonic wind tunnel tests from Mach 0.5 to 3.0. Graphical results from the wind tunnel tests are included. (Author)


Descriptors :   *AVIATION SAFETY , *MODEL TESTS , DRAG , EJECTION SEATS , HUMAN FACTORS ENGINEERING , LIFT , MOMENTS , PARACHUTE DESCENTS , PITCH(MATERIAL) , PITCH(MOTION) , PNEUMATIC EQUIPMENT , PRESSURE VESSELS , RECOVERY , SEA RESCUES , STABILITY , STABILIZATION , STABILIZATION SYSTEMS , SUPERSONIC AIRCRAFT , TABLES(DATA) , TOWED BODIES , TRACKS(AERODYNAMICS) , WIND TUNNEL MODELS , YAW


Distribution Statement : APPROVED FOR PUBLIC RELEASE