NASA Schedules Four-Day Manned Gemini Flight from Cape Kennedy
Gemini 4 manned orbital space flight - plan for launching, maneuvers, rendezvous, docking, and reentry
GEMINI SPACECRAFT↗
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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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Detection of, and communication with space vehicles during atmospheric entry, problems in simulation
In considering the problem of communicating with outer space and detection of spacecraft from the ground, one usually has to worry about only the propagation characteristics of electromagnetic waves of vacuum wavelength falling within either one of the two well known "atmospheric windows," namely; (1) the "optical window" extending from about 0.3 microns to a few microns, and (2) the "RF window" extending from a few millimeters to about 30 meters in the wavelength scale. However, during entry (or reentry) of a spacecraft into the earth's atmosphere, there exists two physical phenomena which tend to complicate the communication problem on the one hand, and to simplify the detection problem on the other hand.
Detection↗
The gemini program.
Gemini program including system and component description, orbital and rendezvous problems, extravehicular operations and controlled reentry
SPACE PROGRAM↗
The gemini program - progress and plans.
Powered flight, rendezvous, reentry, orbital and extravehicular operational aspects of Gemini Project
MANNED SPACE FLIGHT↗
Thermal balance and heat protection.
Protection of spacecraft against thermal environment during launching, flight and reentry phases, emphasizing charring and melting ablator systems
THERMAL PROTECTION↗
Laser excitation of powdered solids.
Spectroscopic investigation of laser excited molecular spectra from powdered solids for meteor and reentry physics
LASER OUTPUT↗
Thermocouples electrically checked while connected to data system
Constant current source is connected across the input of the millivolt measuring system to monitor the electrical continuity and resistance of multiple thermocouple installations without disconnecting them from a data system. This technique monitored gage thermocouple leads during the assembly and preflight testing of the Project Fire reentry packages.
Source record↗
Accurate depth control provided for thermocouple junction locations
Flight reentry experiments define the total heating on a large blunt-nosed body by means of imbedded thermocouples. The thermocouples, installed in a beryllium layered forebody, were designed to provide minimum feasible disturbance of local heat flow with accurate depth control of the thermocouple junction locations.
Richardson, N. R.↗
Performance evaluation of ''Thermo-lag'' material for entry heat protection of advanced manned spacecraft Material development report, 1 Oct. 1962 - 1 Apr. 1963
Performance evaluation of Thermo-lag material for advanced manned spacecraft reentry heat protection
HIGH TEMPERATURE MATERIAL↗
Aerodynamic damping and oscillatory stability in pitch and yaw of Gemini configurations at Mach numbers from 0.50 to 4.63
Aerodynamic damping and oscillatory stability in pitch and yaw of Gemini abort and reentry configurations at transonic and supersonic speeds
DAMPING IN YAW↗
Summary of high-altitude and entry flight control experience with the X-15 airplane
High altitude performance and reentry flight control of X-15 aircraft
HIGH ALTITUDE FLYING↗
The oxidation and sublimation of graphite in simulated re-entry environments
Graphite oxidation and sublimation in simulated reentry environments
TEMPERATURE EFFECT↗
Experiments program summary
Gemini mission experimental results on zodiacal light photography, radiation effects on blood, cloud-top spectrometry, star occultation navigation, and reentry communications
SPECTROMETRY↗
Apollo plasma sheath in-flight diagnostics
Electron density probes for potential application to Apollo in-flight plasma sheath diagnostics in reentry radio blackout investigations
BLACKOUT↗
Convective heat transfer to a lifting flat-faced-cone entry body
Convective heat transfer and pressure distribution measurements on lifting blunt cone reentry body
LIFTING BODY↗
State-of-the-Art Study for High-speed Deceleration and Stabilization Devices
Documented aerodynamic deployable decelerator performance data above Mach 1. 0 is presented. The state of the art of drag and stability characteristics for reentry and recovery applications is defined for a wide range of decelerator configurations. Structural and material data and other design information also are presented. Emphasis is given to presentation of basic aero, thermal, and structural design data, which points out basic problem areas and voids in existing technology. The basic problems and voids include supersonic "buzzing" of towed porous decelerators in the wake of the forebody, the complete lack of dynamic stability data, and the general lack of aerothermal data at speeds above Mach 5.
STABILIZATION↗
Operating characteristics, velocity and Pitot distribution, and material evaluation tests in the Langley one-inch-square plasma accelerator.
Performance and operation of one-inch-square plasma accelerator to simulate reentry velocities
VELOCITY MEASUREMENT↗
Evaluation of flow properties in a combustion- driven expansion tube operating at 7.5 km/sec.
Convective and radiative heat transfer during atmospheric reentry examined, using double- diaphragm shock tube operated in expansion tube mode
RADIATIVE HEAT TRANSFER↗