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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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Body shape, entry angle and velocity, and weight to area ratio effects on radiative heating rates and total heat input of vehicles entering the earths atmosphere at hyperbolic velocities
Spacecraft piloted entry into earth atmosphere at parabolic velocity investigated on fixed base analog simulator
Launching of Project FIRE spacecraft for reentry heating experiments
This is a compilation of papers on in-flight experiments presented at the first symposium of a series, Manned Space Flight Experiments Symposium, sponsored by the National Aeronautics and Space Administration. The results of experiments conducted during the Gemini Missions III and IV are covered. These symposiums are to be conducted for the scientific community at regular intervals on the results of experiments carried out in conjunction with manned space flights.
Spectral radiance measurement of oxygen, nitrogen, xenon, and argon for simulation of radiant heating associated with spacecraft atmospheric entry
Radiant heater technology for simulation of radiant heating associated with spacecraft atmospheric entry
Entry Monitor System /EMS/ for maneuverable spacecraft, interpreting display relationship to entry trajectory control
Theoretical and experimental data on Apollo command module during water impact
Apollo passive infrared acquisition and tracking system analysis
Trajectory optimization for Apollo-type vehicle under entry conditions during lunar return
Entry flight aerodynamics from Apollo mission AS-202
Manned flight simulators suitable to space research, discussing types, phases of development, operational and performance features, etc
Feasibility of using film cooling as alternate thermal protection system for spacecraft atmospheric reentry
Electrostatic modulator for communicating through plasma sheath formed around spacecraft during reentry
Space simulation facilities and techniques are outlined that encompass thermal scale modeling, computerized simulations, reentry materials, spacecraft contamination, solar simulation, vacuum tests, and heat transfer studies.
The U.S. Space Surveillance Network (SSN) issues formal satellite reentry predictions for objects which have the potential for generating debris which could pose a hazard to people or property on Earth. These prognostications, known as Tracking and Impact Prediction (TIP) messages, are nominally distributed at daily intervals beginning four days prior to the anticipated reentry and several times during the final 24 hours in orbit. The accuracy of these messages depends on the nature of the satellite s orbit, the characteristics of the space vehicle, solar activity, and many other factors. Despite the many influences on the time and the location of reentry, a useful assessment of the accuracies of TIP messages can be derived and compared with the official accuracies included with each TIP message. This paper summarizes the results of a study of numerous uncontrolled reentries of spacecraft and rocket bodies from nearly circular orbits over a span of several years. Insights are provided into the empirical accuracies and utility of SSN TIP messages.
This article is a companion to a paper on heat flux measurements as initiated under a Space Act Agreement in 2011. The current focus of this collaboration between the Institute of Space Systems (IRS) of the University of Stuttgart and NASA Ames Research Center is the comparison and refinement of diagnostic measurements. A first experimental campaign to test different heat flux gages in the NASA Interaction Heating Facility (IHF) and the Plasmawindkanaele (PWK) at IRS was established. This paper focuses on the results of the measurements conducted at IRS. The tested gages included a at face and hemispherical probe head, a 4" hemispherical slug calorimeter, a null-point calorimeter from Ames and a null-point calorimeter developed for this purpose at IRS. The Ames null-point calorimeter was unfortunately defective upon arrival. The measured heat fluxes agree fairly well with each other. The reason for discrepancies can be attributed to signal-to-noise levels and the probe geometry.
Conference on simulation of flight, convective and radiative heat transfer during reentry, material evaluation during atmospheric entry, and spacecraft communication during reentry