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High Temperature Investigation of Various Crew Escape Concepts for the Reentry Flight Regime.

AD461713

Publication Date	1964
Personal Author	Cohan, C. J.; Campbell, G.; Herman, W.; Nugent, W.; Heathman, J.
Page Count	310
Abstract	This report presents the results of an analysis of escape system separation techniques from a maximum heating re-entry trajectory. Four escape capsule concepts applicable to a lifting type flight vehicle were considered. These are (1) a separable-noise ballistic body; (2) a separablenose lifting body; (3) a pod capsule; (4) a turnaround capsule. The objective of the study was to determine the applicability of these capsules and various thermal protection schemes to providing escape capability from the maximum heating point of a typical lifting re-entry trajectory. The compatibility of escape techniques developed at the maximum heating point with providing escape capability throughout the complete mission profile was also investigated. It was determined that all concepts except the turnaround capsule could provide escape capability throughout the mission. (Author)
Keywords	Reentry vehicles Jettisonable cockpits Abandonment Lift Drag Recovery Retro rockets Pitch (Motion) Yaw Roll Design Configuration Time Graphics Tables(Data) Atmosphere entry Aerodynamic heating Aerodynamic loading Aerodynamic characteristics Hypersonic characteristics Supersonic characteristics Low orbit trajectories Descent trajectories Control jets Thrust Specific impulse Hight temperature research Structural properties Stabilization systems Heat shields Separation Ablation Deflection Interference Pressure Performance (Engineering) Crews Escape systems
Source Agency	Non Paid Delimited ADS
NTIS Subject Category	51C - Aircraft 84C - Manned Spacecraft
Corporate Authors	General Dynamics/Astronautics San Diego Calif
Document Type	Technical Report
Title Note	Final technical rept.
NTIS Issue Number	197721
Contract Number	AF33 615 1131

High Temperature Investigation of Various Crew Escape Concepts for the Reentry Flight Regime.

High Temperature Investigation of Various Crew Escape Concepts for the Reentry Flight Regime.
AD461713

Publication Date	1964
Personal Author	Cohan, C. J.; Campbell, G.; Herman, W.; Nugent, W.; Heathman, J.
Page Count	310
Abstract	This report presents the results of an analysis of escape system separation techniques from a maximum heating re-entry trajectory. Four escape capsule concepts applicable to a lifting type flight vehicle were considered. These are (1) a separable-noise ballistic body; (2) a separablenose lifting body; (3) a pod capsule; (4) a turnaround capsule. The objective of the study was to determine the applicability of these capsules and various thermal protection schemes to providing escape capability from the maximum heating point of a typical lifting re-entry trajectory. The compatibility of escape techniques developed at the maximum heating point with providing escape capability throughout the complete mission profile was also investigated. It was determined that all concepts except the turnaround capsule could provide escape capability throughout the mission. (Author)
Keywords	Reentry vehicles Jettisonable cockpits Abandonment Lift Drag Recovery Retro rockets Pitch (Motion) Yaw Roll Design Configuration Time Graphics Tables(Data) Atmosphere entry Aerodynamic heating Aerodynamic loading Aerodynamic characteristics Hypersonic characteristics Supersonic characteristics Low orbit trajectories Descent trajectories Control jets Thrust Specific impulse Hight temperature research Structural properties Stabilization systems Heat shields Separation Ablation Deflection Interference Pressure Performance (Engineering) Crews Escape systems
Source Agency	Non Paid Delimited ADS
NTIS Subject Category	51C - Aircraft 84C - Manned Spacecraft
Corporate Authors	General Dynamics/Astronautics San Diego Calif
Document Type	Technical Report
Title Note	Final technical rept.
NTIS Issue Number	197721
Contract Number	AF33 615 1131