Russia Patent RU2046210C1: Electric Rocket Engine with Nuclear Ionizer (Disc Craft)

Patent Number: RU2046210C1 Title: Electric Rocket Engine Inventor: Игорь Глебович Богданов (Igor Glebovich Bogdanov) Filed: October 5, 1992 (priority SU5064411); Granted October 20, 1995 Jurisdiction: Russia (foreign) Source: patents.google.com/patent/RU2046210C1/en Track Directory (Physics_Math): 1_Track/ — toroidal plasma jet with nuclear ionizer on disc-shaped vehicle; electric rocket engine with coaxial electrode geometry directly related to rotating EM disc propulsion

Image files:

• patents_intl/tweets/raw_download/1971417026011992485_1.jpg (Google Patents abstract page with disc craft thumbnails)
• patents_intl/tweets/raw_download/1971417026011992485_2.jpg — _4.jpg (additional diagrams)

Overview

The Google Patents page shows five images for RU2046210C1, with the thumbnail strip revealing: (1) a cross-section schematic of the electromagnetic coil assembly with electrodes; (2) a side-view drawing of a disc-with-dome shaped craft; (3) a different perspective showing the disc from below-rear angle revealing the thruster geometry; (4) what appears to be a linear electrode array cross-section (the spiral element visible in the thumbnail); (5) a detailed wiring diagram.

Abstract

The abstract states the engine includes a charged-particle accelerator (17), electric power supply system (4), ionizing radiation source on the lateral engine surface, magnetic field coil (1) for generating a field beyond the engine, plasma source (5) connected to passages (6, 7) for propulsive mass flow, inner walls (8, 9) made as coaxial electrode bodies of revolution, neutralizer (32), nuclear charge storage and ejector, coaxial electrodes (21, 22) with axes perpendicular to the coil axis for free-flow atmospheric gas ionization along the coil axis direction.

Nuclear Ionizer: Key Distinguishing Feature

The "nuclear charge storage and nuclear charge ejector" specification is highly significant. Standard electric propulsion systems (ion drives, Hall-effect thrusters) use electric fields to accelerate ionized propellant. The RU2046210C1 system adds a nuclear ionization source — likely a radioactive isotope or compact fission source — to maintain propellant plasma density at power levels or in environments where purely electrical ionization would be insufficient. This gives the drive operational capability in low-density environments (high altitude, space) where a plasma source relying on ambient gas ionization would fail.

Physics Mechanism: Toroidal Plasma Jet with Coaxial Electrode Geometry

The disc-shaped craft in the side-view diagram has the same form factor as CN111038740A and RU2106287C1 — disc with dome on top — with the difference that the RU2046210C1 system is explicitly an engine designed to be mounted on a disc-shaped vehicle rather than an integrated vehicle design.

The engine's charged-particle accelerator, nuclear ionizer, and coaxial electrode geometry produce a toroidal plasma jet expelled from the engine's circular exit plane, propelling the craft by direct momentum transfer. The coaxial geometry ensures the thrust vector is centered on the craft's axis of symmetry, and the lateral electrode pairs (21, 22) perpendicular to the main axis provide pitch and yaw control by differential thrust.

Engineering and Historical Significance

This patent represents a significant escalation over atmospheric-only EM drives: it is explicitly designed for space operation (electric rocket engine), uses nuclear ionization, and was filed in 1992 by a Russian private inventor with priority dating to the Soviet-era application SU5064411.

The survival of this concept from Soviet to Russian patent systems and the 19 citing documents indicate it was considered technically credible by subsequent researchers. The Soviet-era priority date (SU5064411) establishes this as a technology concept developed during the Soviet defense program, partially declassified into the civilian patent system after 1991.

Comparison with Standard Electric Propulsion

Feature	Hall-Effect Thruster	Ion Drive	RU2046210C1
Ionization source	Electrical discharge	Electrical discharge	Nuclear + electrical
Propellant	Xenon gas	Xenon gas	Free atmospheric + injected
Geometry	Linear nozzle	Linear nozzle	Toroidal coaxial
Space operation	Yes	Yes	Yes (nuclear ionization)
Atmospheric operation	Limited	No	Yes (ambient air ionization)

Sources

• RU2046210C1 on Google Patents
• Soviet priority application SU5064411 (predecessor filing, Soviet-era)

This information was compiled from Break_thrus.mdx staging file.