Evaluation of trapped radiation model uncertainties for spacecraft design
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Evaluation of trapped radiation model uncertainties for spacecraft design by T. W. Armstrong

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Published by National Aeronautics and Space Administration, Marshall Space Flight Center, Available from NASA Center for AeroSpace Information, National Technical Information Service [distributor in MSFC, Ala, Hanover, MD, Springfield, VA .
Written in English

Subjects:

  • Computer programs.,
  • Ionizing radiation -- Mathematical models.,
  • Magnetohydrodynamics -- Mathematical models.,
  • Radiation trapping.,
  • Space ships -- Design and construction.,
  • Van Allen radiation belts -- Mathematical models.

Book details:

Edition Notes

StatementT.W. Armstrong and B.L. Colborn.
GenreMathematical models.
SeriesNASA CR : -- 2000-210072, NASA contractor report -- NASA CR-2000-210072.
ContributionsColborn, B. L., George C. Marshall Space Flight Center., United States. Office of Space Science. Space Environments and Effects Program .
The Physical Object
Paginationiii, 47 p. :
Number of Pages47
ID Numbers
Open LibraryOL18876555M

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The standard AP8 and AE8 models for predicting trapped proton and electron environments have been compared with several sets of flight data to evaluate model uncertainties. Model comparisons are made with flux, dose, and activation measurements made on various U.S. low-Earth orbit satellites (APEX, CRRES, DMSP. LDEF, NOAA) and Space Shuttle flights, on Russian satellites (Photon-8, Author: T. W. Armstrong and B. L. Colborn.   The standard AP8 and AE8 models for predicting trapped proton and electron environments have been compared with several sets of flight data to evaluate model uncertainties. Model comparisons are made with flux, dose, and activation measurements made on various U.S. low-Earth orbit satellites (APEX, CRRES, DMSP, LDEF, NOAA) and Space Shuttle flights, on Russian Cited by: The standard AP8 and AE8 models for predicting trapped proton and electron environments have been compared with several sets of flight data to evaluate model uncertainties. Model comparisons are made with flux, dose, and activation measurements made on various U.S. low-Earth orbit satellites (APEX, CRRES, DMSP, LDEF, NOAA) and Space Shuttle flights, on Russian satellites (Photon-8, Author: B. L. Colborn and T. W. Armstrong.   Space mission planners continue to experience challenges associated with human space flight. Concerned with the omnipresence of harmful ionizing radiation in space, at the mission design stage, mission planners must evaluate the amount of exposure the crew of a spacecraft is subjected to during the transit trajectory from low Earth orbit (LEO) to geosynchronous orbit (GEO) and beyond (free space).

  The spacecraft radiation shielding evaluation metric proposed here examines existing data in a new way in order to aid designers in calibrating and tying the calculated performance regarding shielding materials and designs for the cislunar environment to the only long-term human exposure medical data available: that from the astronauts who have flown on the International Space Station (ISS). NASA's proposed space radiation cancer risk assessment model for radiation-induced cancer in astronauts is described in the NASA report Space Radiation Cancer Risk Projections and Uncertainties— (Cucinotta et al., ). That NASA report, as it is called hereafter, is divided into discussions of the various components of the proposed model, including the discussion of the key.   The trapped proton peak flux environment is typically used to evaluate SEE (mostly SEU). Figures 10a and 10b show the peak integral proton spectra referenced to 10 MeV. Contrary to the IESD design environment, we commonly use the peak proton flux environment for the SEE evaluation without any additional margin even when using the AP8 model output. • Characterize polyethylene-shielded radiation environment on International Space Station including the Service Module Zvezda crew quarters in order to optimize retro-fit shield design for ISS. Approach • Perform detailed modeling of ionizing radiation environment and measurements using in situ shielding material and radiation detectors.

Therefore, in an effort to reduce risk uncertainty for cancer development during deep space travel, we employed an Mlh1+/− mouse model to study the effects high-LET 56Fe ion space-like radiation. The radiation belts and plasma in the Earth’s magnetosphere pose hazards to satellite systems which restrict design and orbit options with a resultant impact on mission performance and cost. For decades the standard space environment specification used for spacecraft design has been provided by the NASA AE8 and AP8 trapped radiation belt models. There are well-known limitations on their.   1. Introduction. A standard method for estimating trapped radiation for Earth orbiting spacecraft utilizes the spacecraft’s orbital parameters to compute the magnetic field B, and McIlwain’s L coordinates at the spacecraft as a function of location and time. With these orbital data in hand, various versions of trapped radiation models, e.g., AP8 (Sawyer and Vette, ), AE8 (Vette, The designer should be aware of design guidelines to avoid surface and internal charging problems (Sections and ). All guidelines should be considered in the spacecraft design and applied appropriately to the given mission. Analysis. Analysis should be used to evaluate a design for charging in the specified orbital environment.