Errors from geometric approximations introduc- ed in three computational models for space vehicle electron dose prediction
Errors from geometric approximations of three computational models for space vehicle electron dose prediction
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Errors from geometric approximations of three computational models for space vehicle electron dose prediction
Rigid polyurethane foam encapsulation of high- voltage aerospace electronic systems, noting vacuum effect
Design of complex electronic circuits for space environment applications
Theoretical analysis of electron beam array propagation from spacecraft
Feasibility of developing plasma electron beam welding system for earth orbiting vehicle
Free electron electric and magnetic fields for plasma radiation shielding of astronauts from energetic protons produced by solar flares
High power TWT tube cooling in space vehicle, discussing thermal control system based on heat pipe radiator
Digital computer system for automatic prelaunch checkout of spacecraft
Development of method for measuring electron density gradients of plasma sheath around space vehicle during atmospheric entry
Single Event Transients in analog and digital electronics from space generated high energetic nuclear particles can disrupt either temporarily and sometimes permanently the functionality and performance of electronics in space vehicles. This work first provides some insights into the modeling of SET in electronic circuits that can be used in SPICE-like simulators. The work is then directed to present methodologies, one of which was developed by this author, for the assessment of SET at different levels of integration in electronics, from the circuit level to the subsystem level.
Since the United States of America is moving into an age of reusable space vehicles, both electronic and photographic materials will continue to be an integral part of the recording techniques available. Film as a scientifically viable recording technique in astronomy is well documented. There is a real need to expose various types of films to the Shuttle environment. Thus, the main objective was to look at the subtle densitometric changes of canisters of IIaO film that was placed aboard the Space Shuttle 3 (STS-3).
Temperature and radiation tolerant electronics, as well as long life survivability are key capabilities required for future NASA missions. Current approaches to electronics for extreme environments focus on component level robustness and hardening. However, current technology can only ensure very limited lifetime in extreme environments. This paper describes novel experiments that allow adaptive in-situ circuit redesign/reconfiguration during operation in extreme temperature and radiation environments. This technology would complement material/device advancements and increase the mission capability to survive harsh environments. The approach is demonstrated on a mixed-signal programmable chip (FPTA-2), which recovers functionality for temperatures until 28 C and with total radiation dose up to 250kRad.
Radiation environmental testing of diode, transistor, and thermistor for use in nuclear space vehicle
Real time analog computer simulation of traveling wave effects, bending modes, rigid body motions, and transfer functions in electronic model of elastic space vehicle
Ionospheric plasma disturbances due to moving space vehicle, investigating by electron density measurements in rarefied wake regions using gyro- plasma probe
The evaluation and environmental testing of zinc orthotitanate pigments for use as space stable thermal control coatings on large space vehicles are discussed. Electron paramagnetic resonance spectra of the pigments and their precursor compounds are examined. A continuing study of the spectral intensity of mercury-argon and mercury-xenon sources in reported. Results of long term environmental testing of commercially available, strippable, protective coatings are discussed.
Coherent radiation effect on stability of crossed field electron beam, noting raising of potential of space vehicle
Vacuum, electron, proton, and ultraviolet radiation stress results for space vehicle materials