Compendium of Single Event Effects Test Results for Commercial Off-The-Shelf and Standard Electronics for Low Earth Orbit and Deep Space Applications

We present the results of Single Event Effects (SEE) testing with high energy protons and with low and high energy heavy ions for electrical components considered for Low Earth Orbit (LEO) and for deep space applications

Analytic Shielding Optimization to Reduce Crew Exposure to Ionizing Radiation Inside Space Vehicles

A sustainable lunar architecture provides capabilities for leveraging out-of-service components for alternate uses. Discarded architecture elements may be used to provide ionizing radiation shielding to the crew habitat in case of a Solar Particle Event. The specific location relative to the vehicle where the additional shielding mass is placed, as corroborated with particularities of the vehicle design, has a large influence on protection gain. This effect is caused by the exponential- like decrease of radiation exposure with shielding mass thickness, which in turn determines that the most benefit from a given amount of shielding mass is obtained by placing it so that it preferentially augments protection in under-shielded areas of the vehicle exposed to the radiation environment. A novel analytic technique to derive an optimal shielding configuration was developed by Lockheed Martin during Design Analysis Cycle 3 (DAC-3) of the Orion Crew Exploration Vehicle (CEV). [1] Based on a detailed Computer Aided Design (CAD) model of the vehicle including a specific crew positioning scenario, a set of under-shielded vehicle regions can be identified as candidates for placement of additional shielding. Analytic tools are available to allow capturing an idealized supplemental shielding distribution in the CAD environment, which in turn is used as a reference for deriving a realistic shielding configuration from available vehicle components. While the analysis referenced in this communication applies particularly to the Orion vehicle, the general method can be applied to a large range of space exploration vehicles, including but not limited to lunar and Mars architecture components. In addition, the method can be immediately applied for optimization of radiation shielding provided to sensitive electronic components

International Science Aboard Orion EM-1: The Matroshka AstroRad Radiation Experiment (MARE) Payload

No abstract availabl

INTERNATIONAL SCIENCE ABOARD ORION EM-1: THE MATROSHKA ASTRORAD RADIATION EXPERIMENT (MARE) PAYLOAD

The natural ionizing radiation environment present in space poses risks to human exploration that require mitigation. Space ionizing radiation consists primarily of highly energetic charged particles including protons and heavy ions. Solar energetic particles (SEP) originate from the Sun and are emitted during transient events referred to as Solar Particle Events (SPEs). Galactic Cosmic Rays (GCR) originate outside the solar system and form a slowly varying background modulated by the solar cycle. Spacecraft designed for Exploration beyond Earth orbit (BEO) do not benefit from the Earth’s magnetosphere protection and are subject to stricter radiation design requirements than their low Earth orbit (LEO) counterparts. Spacecraft flying beyond Earth orbit may also be exposed to the Van Allen (trapped radiation) belts environment depending upon their trajectories. Orion is NASA’s next generation crewed spacecraft, developed specifically for Exploration missions. [...