Optimal control of a reentry vehicle in the presence of measurement uncertainties.
Optimal trajectory control of lifting reentry vehicle under measurement uncertainties
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.
Optimal trajectory control of lifting reentry vehicle under measurement uncertainties
Synoptic density maps for post-reentry altitudes derived from constant pressure charts and horizontal gradients
Isotope reentry vehicle/Brayton cycle space power system design, noting blunt conical aeroshell housing of heat source capsule
Space to reentry environmental sequence simulator for heat shield materials uninterrupted vacuum transfer without exposure to atmosphere
Computer mechanization of reentry equations with four degrees of freedom
Vacuum ultraviolet detector-spectroscopy systems for capsule reentry measurements
Convective and radiative heat transfer during reentry simulation
Analysis of ground and flight tests for reentry experiments
Laminar heat transfer distributions for blunted- cone, cone frustum reentry configuration at hypersonic speed using Reynolds number
Measurements of mutual interference heating for probe antenna mounted on Apollo reentry configuration
Preliminary design and performance considerations for 25 kW Pu 238 heat source Isotope Reentry Vehicle
Mathematical models for low speed reentry guidance of Apollo vehicles
Atmospheric gas composition effects on shock layer radiative heat transfer and heat shield response in Venus entry simulated by earth reentry
Optimal control for minimization of heating and acceleration forces to reduce kinetic energy of reentry vehicle in space missions
Apollo type reentry trajectory optimization numerical methods
Numerical optimization of atmospheric reentry trajectories by sweep method
Radio blackout alleviation and plasma diagnostic results from 25000 foot per second blunt body reentry
Low subsonic aerodynamic characteristics of medium hypersonic L/D reentry spacecraft configuration with variable geometry wing