MEOSPS is an electric spacecraft propulsion architecture powered by MEOOPS-MAG high-speed rotating structures capable of interacting with the vehicle transitions into near-vacuum conditions, the propulsion mode shifts from aerodynamic interaction toward electromagnetic operation. The overall vehicle architecture is intended to support both atmospheric and orbital operational environments.

The electric spacecraft architecture utilizes dual adjacent spinning electromagnetic rotor assemblies structured into a quad positioned around a structural pyrolytic carbon interaction frame. During operation, rotating electromagnetic fields are directed toward the pyrolytic carbon structure, utilizing its diamagnetic properties to create controlled force interactions within the propulsion assembly. The synchronized electromagnetic timing, diamagnetic repulsion, and angular momentum management can contribute to spacecraft maneuvering and propulsion in microgravity.

These factual demonstrations show how rotational motion and angular momentum redistribution can influence orientation and movement in a microgravity environment. MEOSPS extends these observations into a propulsion architecture utilizing paired counter-rotating electromagnetic assemblies designed to manage angular momentum while generating controlled electromagnetic interactions.

Potential applications include:

• Long-duration Earth-orbit satellites
• Dark-side Earth observation platforms
• Orbital debris avoidance spacecraft
• Large payload transfer vehicles
• Deep-space transportation systems
• Reusable space launch architectures utilizing electric atmospheric ascent systems

Pyrolytic carbon is one of the strongest room-temperature diamagnetic materials and exhibits measurable repulsion when exposed to magnetic fields. The MEOSPS architecture incorporates:

• Pyrolytic carbon structural interaction frames
• Dual spinning electromagnets
• Dynamic magnetic field timing
• Controlled field exposure zones

Each electromagnetic rotor assembly contains integrated alternator components capable of generating electrical power during operation. The proposed power architecture includes:

• Dual electromagnetic rotor assemblies
• Integrated alternator systems
• Rechargeable battery banks
• Supercapacitor energy storagePower management electronics
• Energy harvesting subsystems

MEOSPS incorporate advanced lightweight structures including:

• Metal foam load-bearing structures
• Hexagonal bellows expansion mechanisms
• Accordion-fold energy absorption systems
• Pyrolytic Carbon composite frames
• Pyrolytic carbon interaction elements
• Modular electromagnetic propulsion units

The long-term vision of MEOSPS is to explore advanced electric propulsion facts capable of supporting future reusable aerospace vehicles operating from atmospheric flight through orbital insertion and long-duration space operations. Research objectives include:

• Electromagnetic propulsion investigation.
• Diamagnetic interaction studies.
• Angular momentum management systems.
• Integrated energy harvesting systems.
• Lightweight spacecraft structural technologies.
• Autonomous orbital maneuvering and debris avoidance.