Computer Analysis of Radiation Shielding
Report Number: AMRL TDR 64-11
Author(s): Fortney, R. E.
Corporate Author(s): Northrop Space Laboratories
Laboratory: Biophysics Laboratory
Date of Publication: 1964-02
Pages: 97
Contract: AF 33(657)-8762
DoD Project: 6301
DoD Task: 630101
PB Number: PB125081
Identifier: AD0435737
Abstract:
The purpose of this study was to develop mathematical methods to assess the biological hazards of space radiation and to program these methods for the IBM 7090 using FORTRAN language. A semianalytical approach was utilized to write machine programs for geocentric trajectories and a model astronaut inside a space vehicle. The trajectory program is used to solve the two body problem with pertubations to correct for the oblateness of the earth. The earth's magnetosphere is the space of principle interest for lunar missions, therefore lunar impact and return trajectories are considered to be two body geocentric orbits. An astronaut's head and torso are represented by two right elliptical cylinders. This model is placed inside a mathematically described space vehicle with known thicknesses in designated areas. An existent mahine program was utilized to define the radiative environment in McIlwain (B,L) coordinates and supplemental computer programs were used to determine radiation doses resulting from electron and proton environments. Results from the CARS program are obtained with a small amount of maching time. For example, one tenth (.1) of an hour was required to determine the radiation dose due to two spectra (electrons and protons) at ten points in the model astronaut within the APOLLO Command Module (CM) for a given orbital mission.
Provenance: RAF Centre of Aviation Medicine
Author(s): Fortney, R. E.
Corporate Author(s): Northrop Space Laboratories
Laboratory: Biophysics Laboratory
Date of Publication: 1964-02
Pages: 97
Contract: AF 33(657)-8762
DoD Project: 6301
DoD Task: 630101
PB Number: PB125081
Identifier: AD0435737
Abstract:
The purpose of this study was to develop mathematical methods to assess the biological hazards of space radiation and to program these methods for the IBM 7090 using FORTRAN language. A semianalytical approach was utilized to write machine programs for geocentric trajectories and a model astronaut inside a space vehicle. The trajectory program is used to solve the two body problem with pertubations to correct for the oblateness of the earth. The earth's magnetosphere is the space of principle interest for lunar missions, therefore lunar impact and return trajectories are considered to be two body geocentric orbits. An astronaut's head and torso are represented by two right elliptical cylinders. This model is placed inside a mathematically described space vehicle with known thicknesses in designated areas. An existent mahine program was utilized to define the radiative environment in McIlwain (B,L) coordinates and supplemental computer programs were used to determine radiation doses resulting from electron and proton environments. Results from the CARS program are obtained with a small amount of maching time. For example, one tenth (.1) of an hour was required to determine the radiation dose due to two spectra (electrons and protons) at ten points in the model astronaut within the APOLLO Command Module (CM) for a given orbital mission.
Provenance: RAF Centre of Aviation Medicine