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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Manual-control simulation study of nonlifting vehicle during orbit, retrorocket firing, and reentry into earth atmosphere
A study has been made of a flare-cylinder configuration to investigate its feasibility as a reentry body of an intermediate range ballistic missile. Factors considered were heating, weight, stability, and impact velocity. A series of trajectories covering the possible range of weight-drag ratios were computed for simple truncated nose shapes of varying pointedness, and hence varying weight-drag ratios. Four trajectories were chosen for detailed temperature computation from among those trajectories estimated to be possible. Temperature calculations were made for both "conventional" (for example, copper, Inconel, and stainless steel) and "unconventional" (for example, beryllium and graphite) materials. Results of the computations showed that an impact Mach number of 0.5 was readily obtainable for a body constructed from conventional materials. A substantial increase in subsonic impact velocity above a Mach number of 0.5 was possible without exceeding material temperature limits. A weight saving of up to 134 pounds out of 822 was possible with unconventional materials. This saving represents 78 percent of the structural weight. Supersonic impact would require construction of the body from unconventional materials but appeared to be well within the range of attainability.
Sensors measure surface erosion rate of ablating material in reentry vehicle heat shield. Each sensor, which is placed at precise depths in the heat shield is activated when the ablator surface erodes to the location of a sensing point. Sensor depth and activation time determine ablator surface erosion rate.
Approximation of reentry angles of attack for spinning body from rate-gyro and accelerometer data
Ballistic camera data reduction methods for determining reentry body position, velocity, and deceleration
Coordination of reentry plasma measurements with flight data ascertained by RAM, FIRE, Gemini, and Mercury projects
Theoretical and experimental studies of graphite and unspecified reactor material oxidation behavior to determine atmospheric reentry effects
Flight simulator to evaluate lateral-directional handling qualities of piloted reentry vehicles
Performance analysis on Apollo reentry acquisition and tracking radar
Plutonium isotope reentry vehicle experimental design study
Aerodynamic parameters effect on dynamic behavior on reentry vehicle
Reentry control requirements during terminal glide, approach, and landing
Transpiration cooling system for reentry vehicles
Apollo command module radar cross section decrease due to reentry plasma effects
Design evaluation of heat source array for isotope reentry vehicle
Indirect pilot viewing systems for reentry vehicles and SST, discussing overlapping monoculars and panoramic display
Space emergency reentry vehicle - NASA Faculty Systems Engineering Institute Conference, University of Houston, June-August 1967
Apollo antenna design before and after reentry, discussing radio blackout problems and S band helices performance