Environmental diagnostic package for NMP technology validation flights
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Engineering topics
Publications and source records attributed to Garrett, H..
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Missions to Europa and other moons of Jupiter will experience the most severe radiation environment in the Solar System outside the Sun.
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Twenty years after the landmark SCATHA program, spacecraft charging and its associated plasma interactions continue to be major issues for Earth-orbiting spacecraft. Although typically thought of as a surface effect on geosynchronous spacecraft, internal charging and low-altitude phenomena are increasingly causing concern.
This paper describes NASA-HDBK-4002, 'Avoiding Problems Caused by Spacecraft On-Orbit Internal Charging Effects'.
The report will close with a detailed discussion of the current status of modeling of the radiation environment and recommend a long range plan for enhancing capabilities in this important environmental area.
The NASA Orbiting Technology Test-bed Inititative (OTTI) will evaluate the effects of real-time space environments on advanced spacecraft technologies.
This paper describes NASA-HDBK-4002, 'Avoiding Problems Caused by Spacecraft On-Orbit Internal Charging Effects'.
Studies of the Earth with the ATS-5, ATS-6, and SCATHA spacecraft led to the development of several simple tools for predicting the potentials to be expected on a spacecraft in the space environment.
Coupled with the increasing concern over trapped radiation effects on microelectronics, the availability of new data, long term changes in the Earth's magentic field, and observed variations in the trapped radiation fluxes have generated the need for better, more comprehensive tools for modeling and predicting the Earth's trapped radiation environment and its effects on space systems.
Grounding architecture, including its implementation, is an important part of overall mission success for spacecraft.
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This paper presents radiation dosimetry results from the radiation and reliability experiments on the Clementine spacecraft and Interstage Adapter Satellite. The dosimetry instruments used low dose response p-channel field effect transistor and proton sensitive static random access memory dosimeters. They were an order of magnitude lower in mass and power than previous systems. A solar proton event early in the mission allowed comparison with another dosimeter in orbit.
The Clementine RRELAX radiation monitor chip consists of a p-FET total dose monitor and a 4-kbit SRAM particle spectrometer. Eight of these chips were included in the RRELAX and used to detect the passage of the Clementine (S/C) and the innerstage adapter (ISA) through the earth's radiation belts and the 21-Feb 1994 solar flare. This is the first space flight for this 1.2 micron rad-soft custom CMOS radiation monitor. This paper emphasizes results from the SRAM particle detector which showed that it a) has a detection range of five orders of magnitude relative to the 21-Feb solar flare, b) is not affected by electrons, and c) detected microflares occurring with a 26.5 day period.
A methodology is presented for reviewing various interactions between power systems and the environment that affect the longevity, calibration, maintenance, and accuracy of sensors. The analysis uses the low-earth-orbit environment and interactions with the space station power system as a case study in system compatibility. Space-based power systems and sensor systems are described, compatibility modeling is discussed, and the analysis of the space station case is presented. Steps to be taken during design to promote compatibility are outlined.