Investigation Of Escape Capsule Systems For Multi-place Aircraft . Part I: Preliminary Investigation
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Report Number: WADC TR 57-329 Part 1
Author(s): Vorachek, J. J. , Milhoan, F.
Corporate Author(s): Goodyear Aircraft Corporation
Laboratory: Flight Dynamics Laboratory
Date of Publication: 1961-12
Pages: 85
Contract: AF 33(616)-5017
DoD Project: 1362 - Crew Escape for Flight Vehicles
DoD Task: 13438
Identifier: AD0273625
Abstract:
Findings are summarized of an investigation of 4 escape capsule systems for a hypothetical multi-place aircraft. The aircraft has been assumed to operate in a 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. Four capsule configurations are evaluated: cockpit, nose section, tandem and individual. All the configurations tested provide the required escape potential, necessary crew comfort and access to work areas, and adequate survival potential. The individual capsule concept was the most desirable arrangement of the 4 concepts due to its weight factor, the least effect on aircraft availability, greatest escape potential, least susceptibility to damage, and the most positive separation factor from the aircraft.
Provenance: Lockheed Martin Missiles & Fire Control
Author(s): Vorachek, J. J. , Milhoan, F.
Corporate Author(s): Goodyear Aircraft Corporation
Laboratory: Flight Dynamics Laboratory
Date of Publication: 1961-12
Pages: 85
Contract: AF 33(616)-5017
DoD Project: 1362 - Crew Escape for Flight Vehicles
DoD Task: 13438
Identifier: AD0273625
Abstract:
Findings are summarized of an investigation of 4 escape capsule systems for a hypothetical multi-place aircraft. The aircraft has been assumed to operate in a 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. Four capsule configurations are evaluated: cockpit, nose section, tandem and individual. All the configurations tested provide the required escape potential, necessary crew comfort and access to work areas, and adequate survival potential. The individual capsule concept was the most desirable arrangement of the 4 concepts due to its weight factor, the least effect on aircraft availability, greatest escape potential, least susceptibility to damage, and the most positive separation factor from the aircraft.
Provenance: Lockheed Martin Missiles & Fire Control