Space Weather Monitor

About This Project

Fly a magnetometer and particle detector to measure geomagnetic field variations and charged particle flux in LEO. Correlate data with solar activity to contribute to space weather research and forecasting models.

Overview

Space weather — the stream of charged particles and magnetic field variations emanating from the Sun — affects everything from satellite electronics and astronaut safety to GPS accuracy and power grid stability on the ground. A space weather monitor flies instruments that measure the local magnetic field and charged particle environment as the satellite orbits, building a continuous record of conditions along its orbital track. Over weeks and months, this data reveals how space weather varies with geographic location, altitude, solar activity, and proximity to features like the South Atlantic Anomaly. The payload is compact — a precision magnetometer measuring Earth's magnetic field vector and a particle detector counting radiation hits — but the science is substantial. Data can be correlated with solar observatory records, ground magnetometer networks, and space weather forecasts to validate prediction models. Universities with space physics or radiation effects research groups can integrate this data directly into ongoing research programs. This payload has more successful student flight heritage than any other concept in the catalog, with multiple universities having flown similar instruments over the past fifteen years.

Technical Details

Same sensor suite as Radiation Mapping (project 3) but with emphasis on magnetometer data for geomagnetic field mapping. PNI RM3100 tri-axis magnetometer (~$50, I2C, 2.7 nT resolution, radiation-tolerant >150 krad) as primary instrument. Add Teviso BG51 PIN diode for particle flux correlation. VEML6075 UV sensor for solar flux proxy. GPS position tagging for geographic correlation. Sample at 1-10 Hz, store time-tagged vectors, downlink via PyCubed radio. Calibrate against IGRF model to separate spacecraft magnetic signature from geomagnetic field.

Research & Notes

Identical flight heritage to project 3 — Vanderbilt ISDE RadFxSat/AO-91 (2017) and RadFxSat-2/Fox-1E (2021). PNI RM3100 has been characterized for CubeSat use in published literature (Copernicus GI journal, "Quad-Mag board for CubeSat applications"). Key challenge: spacecraft magnetic cleanliness — reaction wheels, magnetorquers, and power bus switching create magnetic noise that must be characterized and subtracted. Deploy magnetometer on a short boom (even 5-10 cm helps) or sample during magnetically quiet periods. RM3100 radiation tolerance >150 krad makes it suitable for multi-year LEO missions. Cost: $200-$1,500. Complexity: intermediate. Tier 1 recommendation — lowest risk, highest heritage, strong ISDE mentorship pipeline.

Required Disciplines

This project spans 3 disciplines, making it suitable for interdisciplinary student teams.

Next Steps

Ready to take on this project? Here's a general roadmap that applies to most CubeSat missions:

1. Build your foundation: Complete the core modules in the CubeSat Academy to understand spacecraft subsystems, mission design, and development workflows.
2. Form a team: Recruit students across the required disciplines and identify a faculty advisor. Plan for knowledge transfer between graduating and incoming members.
3. Write a mission concept: Draft a 1–2 page document outlining your objectives, target orbit, payload requirements, and success criteria.
4. Connect with a chapter: Join a Blackwing chapter for mentorship, shared resources, and access to the platform ecosystem.
5. Explore the developer tools: Visit the Developer Portal for platform documentation, SDKs, and hardware specs.
6. Plan your timeline: Map milestones to your academic calendar. Most projects align well with a 2–4 semester capstone or research sequence.
7. Reach out: Contact us to discuss your project goals, platform selection, and path to orbit.