INVESTIGATION OF ESCAPE CAPSULE SYSTEMS FOR MULTI-PLACE AIRCRAFT. PART II. PRELIMINARY DESIGN AND WIND TUNNEL TESTING OF AN INDIVIDUAL ESCAPE CAPSULE
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1961
- Accession Number
- AD0273626
Entities
People
- F.m. Milhoan
- J. D'allura
- J.j. Vorachek
Organizations
- Goodyear Aerospace