Session
Next on the Pad Research & Academia
Location
Salt Palace Convention Center, Salt Lake City, UT
Abstract
The SCION-X (SCintillation and IONosphere eXtended) mission, a 12U CubeSat from National Central University, Taiwan, is scheduled for launch in Q3 of 2026. Designed to perform in-situ ionospheric plasma measurements, hyperspectral aerosol monitoring, and Solar EUV irradiance quantification, the spacecraft integrates a complex multi-payload suite that also includes an amateur radio APRS transponder. As the mission transitions from the Critical Design Review (CDR) phase to flight readiness, the student team implemented a comprehensive FlatSat campaign to bridge the gap between theoretical design and physical reality. This paper presents the "Next on the Pad" status of SCION-X, focusing on the critical lessons learned during the Hardware-In-The-Loop (HITL) verification phase.
While the CDR established the system architecture, the FlatSat phase revealed distinct integration challenges that pure software simulations failed to predict. Specifically, this paper details the identification and systematic remediation of critical hardware anomalies discovered during physical integration, including electrical power subsystem (EPS) thermal plate short-circuits, battery module fixture and adhesive potting misalignments, and communication transceiver clock spikes. In addition, empirical hardware isolation on the FlatSat integration benchtop successfully resolved a critical Ultra-High Frequency (UHF) communication anomaly induced by vendor fabrication defects. By implementing a localized RF absorbing encapsulation paired with a low-impedance structural grounding path, the student team eliminated internal cavity resonance and secured robust end-to-end link propagation margins on the final Flight Model. The discussion also covers the precise mechanical rectification strategies, material selections, friction clearances within the deployable solar arrays, and fastening protocols implemented to secure the final Flight Model (FM) assembly without introducing any mass or power budget penalties.
Furthermore, the study highlights the environmental stress screening strategy, including the management of strict thermal survival constraints during component curing and bake-out procedures to ensure battery safety. By rigorously testing these critical multi-payload integration scenarios and undergoing necessary hardware de-integration and reintegration cycles on the FlatSat, the SCION-X student team has significantly reduced on-orbit failure risks. The paper concludes with the final launch configuration and readiness status, demonstrating how a robust FlatSat philosophy serves as an essential gatekeeper for university-class satellite missions.
Document Type
Event
System Integration and Pre-Launch Verification of the SCION-X Mission: Lessons Learned From a High-Fidelity FlatSat Campaign
Salt Palace Convention Center, Salt Lake City, UT
The SCION-X (SCintillation and IONosphere eXtended) mission, a 12U CubeSat from National Central University, Taiwan, is scheduled for launch in Q3 of 2026. Designed to perform in-situ ionospheric plasma measurements, hyperspectral aerosol monitoring, and Solar EUV irradiance quantification, the spacecraft integrates a complex multi-payload suite that also includes an amateur radio APRS transponder. As the mission transitions from the Critical Design Review (CDR) phase to flight readiness, the student team implemented a comprehensive FlatSat campaign to bridge the gap between theoretical design and physical reality. This paper presents the "Next on the Pad" status of SCION-X, focusing on the critical lessons learned during the Hardware-In-The-Loop (HITL) verification phase.
While the CDR established the system architecture, the FlatSat phase revealed distinct integration challenges that pure software simulations failed to predict. Specifically, this paper details the identification and systematic remediation of critical hardware anomalies discovered during physical integration, including electrical power subsystem (EPS) thermal plate short-circuits, battery module fixture and adhesive potting misalignments, and communication transceiver clock spikes. In addition, empirical hardware isolation on the FlatSat integration benchtop successfully resolved a critical Ultra-High Frequency (UHF) communication anomaly induced by vendor fabrication defects. By implementing a localized RF absorbing encapsulation paired with a low-impedance structural grounding path, the student team eliminated internal cavity resonance and secured robust end-to-end link propagation margins on the final Flight Model. The discussion also covers the precise mechanical rectification strategies, material selections, friction clearances within the deployable solar arrays, and fastening protocols implemented to secure the final Flight Model (FM) assembly without introducing any mass or power budget penalties.
Furthermore, the study highlights the environmental stress screening strategy, including the management of strict thermal survival constraints during component curing and bake-out procedures to ensure battery safety. By rigorously testing these critical multi-payload integration scenarios and undergoing necessary hardware de-integration and reintegration cycles on the FlatSat, the SCION-X student team has significantly reduced on-orbit failure risks. The paper concludes with the final launch configuration and readiness status, demonstrating how a robust FlatSat philosophy serves as an essential gatekeeper for university-class satellite missions.
