[Paper Review] Determination of the Stopping Power and Failure-time of Spacecraft Components due to Proton Interaction Using GOES 11 Acquisition Data

N. N. Jibiri, Victor U. J. Nwankwo+1 more|arXiv (Cornell University)|Mar 2, 2013

Advanced Battery Technologies Research7 references4 citations

TL;DR

This study uses GOES-11 satellite data to model proton-induced radiation effects on spacecraft components, calculating stopping power, range, and total ionizing dose to predict failure times. It finds that an aluminum alloy spacecraft with 20 mm thickness faces a 3-year safe period and up to 29 years of risk due to cumulative radiation damage in geosynchronous orbit without mitigation strategies.

ABSTRACT

One of the several ways to describe the net effect of charged-particles' interaction is the rate of energy loss along the particles' path. In this study, the mass stopping power (Sp) of selected spacecraft composite materials, through which the particle traverses, its range (R) and the distance (d) travelled (by the particles) through the materials have been calculated and analyzed. The dose (in Gy) as a function of particle flux and deposited energy was also determined. Predictions of their possible effects on space system operations and life-span were made, especially as values exceeded certain threshold (limit). Using GOES 11 acquired data for 3 months, estimations and/or calculations were made to determine the risk and safe period of a satellite in the geosynchronous orbit. Under certain space radiation environmental conditions (without mitigation of any sort), a spacecraft whose body is 20 mm thick and with Al alloy casing, was theoretically estimated to have a safe period of about 3 years and risk period of about 29 years (due to total ionizing dose) within which it would experience a catastrophic failure.

Motivation & Objective

• To assess the impact of space radiation, particularly protons, on spacecraft components using real-time data from the GOES-11 satellite.
• To determine the stopping power and range of protons in common spacecraft materials like aluminum alloy, germanium, and silicon.
• To estimate the total ionizing dose (TID) and failure time of electronic components under prolonged exposure in geosynchronous orbit.
• To evaluate the risk of single-event effects and surface charging due to electron and proton flux variations.
• To provide material selection and shielding recommendations to enhance spacecraft radiation resilience and extend operational lifespan.

Proposed method

• Utilized 3-month proton and electron flux data from the GOES-11 satellite, collected via NOAA's Space Weather Prediction Center.
• Calculated mass stopping power (Sp) using energy loss rate per unit mass, derived from proton energy and material density.
• Computed proton range (R) and distance traveled (d) through materials using empirical and theoretical stopping power models.
• Estimated total ionizing dose (TID) as a function of flux and energy deposition, with dose rate calculated in Gy per year.
• Applied TID thresholds (10 krad and 100 krad) to predict safe operation and catastrophic failure times.
• Evaluated surface charging risks by analyzing electron flux peaks and their potential to induce discharge events.

Experimental results

Research questions

• RQ1 What is the stopping power and range of protons in common spacecraft materials such as aluminum alloy, germanium, and silicon?
• RQ2 How does the total ionizing dose accumulate over time in a 20 mm thick aluminum alloy spacecraft body in geosynchronous orbit?
• RQ3 What is the predicted safe operating period and failure time for spacecraft components under continuous proton exposure without radiation mitigation?
• RQ4 How do variations in electron and proton flux over time affect the risk of surface charging and single-event effects?
• RQ5 Which material compositions (e.g., Al with added Mg, Si) offer improved radiation shielding and reduced failure risk?

Key findings

• The mass stopping power of aluminum alloy was found to be higher than pure aluminum, indicating better shielding against proton penetration.
• Electron flux peaked between April 2nd and 11th, 2010, increasing the risk of surface charging and potential discharge-induced anomalies.
• Proton flux peaked between June 10th and 13th, 2010, indicating a possible solar particle event that elevated radiation exposure risks.
• For a 20 mm thick aluminum alloy spacecraft body, the safe operating period was estimated at approximately 3 years (10 krad TID threshold).
• The risk period extended to 29 years, at which point accumulated dose reached 100 krad, triggering a catastrophic failure due to total ionizing dose.
• The study recommends multi-layer coatings and increased use of high-stopping-power elements like Mg and Si in aluminum alloys to improve radiation resistance.