Inside JupSat95 — Design, Instruments, and Mission Goals
JupSat95 is a compact, cost‑effective CubeSat-class mission designed to study Jupiter’s magnetosphere, atmospheric dynamics, and auroral processes. Built around a 12U form factor with radiation‑hardened subsystems, JupSat95 combines proven small‑sat hardware with focused science instruments to deliver high‑value measurements during a multi‑year cruise and Jupiter encounter phase.
Spacecraft design and architecture
- Bus: 12U CubeSat (20 cm × 20 cm × 30 cm stackable volume) with deployable solar panels and a xenon micro‑propulsion system for trajectory corrections and orbit insertion maneuvers.
- Structure & thermal: Lightweight composite frame with multilayer insulation and localized heaters; passive thermal control augmented by louvers to maintain instrument temperature during Jupiter approach.
- Power: Triple-junction GaAs solar arrays paired with 150 Wh lithium‑ion battery pack; peak power around 160 W, average operational power ~50 W.
- Communications: X-band high‑gain antenna for science downlink during perijove passes; S-band for telemetry, tracking, and command.
- Avionics & computing: Radiation-tolerant flight computer with redundant watchdogs and fault‑tolerant avionics bus; onboard data processing for event detection to prioritize downlink.
- Propulsion & ADCS: Micro-ion thruster for delta‑v maneuvers; three‑axis reaction wheels with star trackers and sun sensors for precise pointing.
Science instruments
- Magnetometer (MAG): Triaxial fluxgate magnetometer on a deployable boom to measure local magnetic field vectors with high temporal resolution to characterize magnetospheric structure and reconnection events.
- Plasma Analyzer (PA): Electrostatic analyzer for ions and electrons covering energies from a few eV to tens of keV to map plasma density, temperature, and composition near perijove.
- Energetic Particle Detector (EPD): Solid‑state detector stack for measuring high‑energy particles (keV to MeV range), informing radiation environment models and particle acceleration processes.
- Ultraviolet Imager (UVI): Narrowband UV camera to image Jupiter’s aurora and resolve temporal changes linked to magnetospheric dynamics and solar wind interactions.
- Radio & Plasma Wave Instrument (RPWI): Electric and magnetic antenna sensors to detect plasma waves, whistlers, and radio emissions associated with auroral processes and magnetospheric turbulence.
Mission goals and science objectives
- Map Jupiter’s magnetospheric structure at high spatial and temporal resolution. Use MAG and PA data to detail field topology, current sheets, and reconnection sites.
- Characterize particle acceleration mechanisms. Combine EPD and RPWI observations to link wave activity with energetic particle populations.
- Monitor auroral dynamics and coupling to magnetospheric processes. UVI imaging synchronized with in-situ measurements to correlate auroral features with local plasma conditions.
- Provide measurements to improve radiation environment models for future missions. In-situ radiation data will refine shielding requirements and operational planning for larger spacecraft.
- Demonstrate cost-effective CubeSat operations in deep‑space environments. Validate long‑duration micropropulsion, autonomous fault protection, and high‑gain communications at Jupiter distances.
Operations and mission profile
- Cruise phase (3–4 years): Interplanetary transfer with periodic instrument checkouts, cruise science (solar wind monitoring), and trajectory corrections.
- Approach & Jupiter encounter: Multiple perijove passes in a highly elliptical orbit to sample different magnetospheric regions; targeted observations during inbound and outbound traversals of key current sheets and auroral field lines.
- Data handling: Onboard event detection to prioritize high‑value intervals; scheduled high‑gain downlinks during Earth visibility
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