Spacecraft landing systems - design criteria and components.
Landing systems including events sequencing devices, deceleration, stabilization and main descent subsystems
SEARCH · Search NASA
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Landing systems including events sequencing devices, deceleration, stabilization and main descent subsystems
Spacecraft deceleration upon entry into Mars orbit by aerodynamic braking, considering vehicle shape and velocity effects on entry heating
Method estimating relative magnitude of magnetoaerodynamic drag/MADD/ or Lorentz drag used for decelerating space vehicle reentry
Elevator-type emergency escape system evacuates personnel from tall structures, especially when the possibility of explosion or fire exists. The system consists of a spike shaped rescue cabin which descends along a vertical guide cable, penetrates the dome shaped roof of an underground blast shelter and stops in a deceleration bed of granular material.
Process of energy dissipation through radiation and evaporation, deceleration by drag, and ablation through evaporation of spherical stony micrometeorites in earth atmosphere
Venus swingby used to decelerate manned spacecraft returning from Mars
Structural design of components for launch, space and reentry vehicles, noting materials, mirrors and antennas for high speed flight, deceleration and landing systems
Four female and two male chimpanzees were secured in various positions on a Daisy Decelerator and subjected to forces ranging from 54 to 180 G. It was found that forces in excess of 54 G may rupture the tympanic membranes and cause subepithelial hemorrhages in the middle ear. The majority of cases showed proteinaceous material, with or without cells in the petrous air spaces. When exposed to forces above 119 G, there was engorgement and often rupture of the pericarotid venous plexus. When supine, distortion of both superior and posterior semicircular canals was found. With forces in excess of 54 G, the cupulae of the cristae ampullaris were either elevated or destroyed. The hair processes were also often broken off. The otolithic membranes, especially of the maculae utriculi were also elevated or otherwise distorted and the saccule was often partially collapsed. In several instances, there was an overabundance of a proteinaceous substance in the lumina of the vestibular apparatus and in the cochlear ducts with their associated scalae. In half the cases, the cochlear duct was narrowed by the depression of the vestibular membrane. Although there seems to be considerable individual variation in ability to withstand these forces, neither age, sex nor weight appear to directly influence the results. The possible sources for the materials found both in the air cells and labyrinth are discussed.
Inflatable parachute system developed for deceleration of ionospheric probe instrumentation descending after expulsion from rocket
Ballistic camera data reduction methods for determining reentry body position, velocity, and deceleration
Computerized simulation of aircraft landing deceleration with stored energy lift
Biosatellite terminal parachute recovery system test proved noting drag, deceleration, descent velocity and deployment
Aerothermoelasticity problems for Mars entry vehicles, discussing deceleration loads, separated hot gas flow, shield thermal gradients and oscillatory body motion
Turbulence and longitudinal heat transfer for accelerating and decelerating flow using Navier- Stokes, continuity and energy equations
Electromechanical rotary actuator, which operates over wide temperature range, contains a spring stop which has been calculated to limit internal deceleration loads to a magnitude equal to stall torque. Cryogenic capability is obtained by using dry lubricant on the gears and no lubrication on the bearings.
Intensity modulation and deceleration dynamics of solar wind by cosmic rays
Static liquid-vapor interface after sudden deceleration using Saturn S-4B stage
Aerothermoelasticity problems for Mars entry vehicles, discussing deceleration loads, separated hot gas flow, shield thermal gradients and oscillatory body motion