Shock-Layer Radiation of Blunt Bodies Traveling at Lunar Return Entry Velocities
Shock-layer radiation of blunt bodies traveling at lunar return entry velocities
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Shock-layer radiation of blunt bodies traveling at lunar return entry velocities
Pitch damping at large angles of oscillation for proposed mars atmosphere-entry vehicles - wind tunnel test methods
Subsonic aerodynamics of several blunt, lifting, atmospheric-entry shapes
Investigation in atmosphere entry simulator of nylon as ablative material for ballistic missiles
Anomalous entry of low-rigidity solar cosmic rays into geomagnetic field
Vehicles for circular and hyperbolic entry by manned spacecraft
Optimization of aft configuration of passive-entry capsule
Wind tunnel techniques used to determine pitch damping at large angles of oscillation for proposed mars atmospheric entry vehicles
Experimental studies of radiative heating and static stability in relation to vehicle entry into the atmospheres of mars and venus
Description of ames entry heating simulator, a facility which is capable of simulating both the convective and radiative modes of heat transfer
Heating and heat-shield requirements for maneuverable, lifting body, entry vehicle
Up to the present time we have been concerned with sending small instrumented probes into interplanetary space and larger bodies into near-earth satellite orbits. Only recently we have begun to recover intact some of these orbiting bodies and soon we will carry on this program to the recovery of manned satellites. In the not-too-distant future we will be concerned with transit to and from the moon and the planets. It is with the problems of entry into our atmosphere of these higher speed vehicles that this paper will be concerned.
Multipurpose manned reentry vehicle capable of entry at circular to hyperbolic velocities - design study
Mars atmosphere models for entry vehicle design
The shape of a shell of revolution designed t o have only tensile stresses under axisymmetric aerodynamic loadings has been derived on the basis of linear membrane theory. values of circumferential tension is also given. The results of this paper indicate that the design of an entry vehicle based on the tension shell concept leads to desirable aerodynamic and structural characteristics, namely, high drag and low weight.
Spacecraft piloted entry into earth atmosphere at parabolic velocity investigated on fixed base analog simulator
Inertia product and inertia moment variation effect on spin entry, developed spin, and spin recovery of airplanes
Thermal properties and performance of Thermo-lag material for entry heat protection of manned spacecraft