Russia Patent RU2266420C2: Aerospace Laser Jet Engine (Omnidirectional LSD)

Patent Number: RU2266420C2 Title: Aerospace Laser Jet Engine Assignee: Федеральное государственное унитарное предприятие Научно-исследовательский институт комплексных испытаний оптико-электронных приборов и систем (ФГУП НИИИКИ ОЭП) — Federal State Unitary Enterprise Scientific Research Institute for Complex Testing of Opto-Electronic Devices and Systems Filed: October 8, 2003; Granted December 20, 2005 Jurisdiction: Russia (foreign); also PCT/RU2003/000581 (WO filing) Source: Google Patents, also PCT/RU2003/000581 (WO filing) Track Directory (Physics_Math): N/A — omnidirectional laser reception / LSD propulsion domain; parallel to US6488233B1 but with 360° beam acceptance; candidate for a future laser propulsion track

Image files:

• patents_intl/tweets/raw_download/1956322284517368174_1.jpg (Google Patents abstract page)
• patents_intl/tweets/raw_download/1956322284517368174_2.jpg (additional images)

Abstract

"FIELD: orbital and aerospace vehicles. SUBSTANCE: proposed engine contains pulsed periodic laser radiation source, optical unit with radiation concentrator and reflectors, system forming plane radiation front, and gas-dynamic unit coaxial to concentrator. Forming system provides reception and matching of laser beam aperture with dimensions of optical unit. First reflector of concentrator is made in form of cone-shaped figure of revolution with surface generatrix in form of part of short-focus parabola. Gas-dynamic unit is made in form of pressure pulse receiver arranged from rear side and on base of first reflector, and jet nozzle installed at a distance from base and forming input slot for laser rays. Concentrator is provided with additional reflector coaxial to first reflector and made in form of figure of revolution with arc-shaped surface generatrix. Said additional reflector is placed on way of beam focused by first reflector so that focus area of concentrator is arranged in zone of said slot. EFFECT: possibility of mounting engine on board the craft, building of thrust irrespective of relative orientation of craft and laser energy source."

Key Innovation: Omnidirectional Laser Reception

The critical phrase is "irrespective of relative orientation of craft and laser energy source." The conical primary reflector with parabolic generatrix solves the alignment problem that plagued Myrabo's Lightcraft design (US6488233B1): the Russian system can receive laser power from any direction relative to the vehicle axis, not just along the flight axis. The dual-reflector system (cone-shaped primary + arc-generatrix secondary) is a variant of the Cassegrain telescope design optimized for maximum beam-capture solid angle and minimum aberration, allowing the effective aperture to be maintained as the craft maneuvers freely.

Physics Mechanism: Laser-Sustained Detonation with Omnidirectional Reception

The gas-dynamic unit described is a laser-detonation thruster cavity: the focused beam deposits energy in a localized plasma at the jet nozzle slot, heating gas to expand through the nozzle. The pressure pulse receiver mounted on the rear face of the primary reflector collects the impulse from each laser detonation cycle. This is architecturally equivalent to what Myrabo independently filed in 2001 (US6488233B1), but with the 360-degree reception geometry added and with a different nozzle topology adapted for in-atmosphere and vacuum operation.

Strategic Context

The assignee — a federal state unitary enterprise for testing opto-electronic devices — is the kind of defense-adjacent research institution that would work on directed-energy weapons systems. The filing of a WO (PCT) international application simultaneously indicates Russia was seeking international IP protection for a technology its government considered strategically significant. An aerospace laser engine filed by an opto-electronics testing institute in 2003 points directly to a dual-use program where the laser propulsion component is a derivative of a directed-energy weapon or space-based laser program.

The engine's engineering accomplishment is the omnidirectional reception architecture: a spacecraft using this engine does not need to know the direction to the transmitting laser source — the cone-and-arc reflector system gathers the beam regardless of vehicle attitude. This is essential for vehicles performing rapid maneuvers, for undersea launch (where beam direction through water is impractical), or for operations in clutter environments where the craft cannot maintain a fixed attitude relative to the energy source.

Comparison with US6488233B1

Feature	US6488233B1 (Myrabo)	RU2266420C2 (Russia)
Beam reception	Axial only (along flight axis)	Omnidirectional (360°)
Primary reflector	Parabolic afterbody	Conical with parabolic generatrix
Secondary reflector	None	Arc-generatrix coaxial secondary
Attitude requirement	Must face beam source	None
Filed	2001	2003
Assignee	US Air Force	Russian defense institute

Sources

• RU2266420C2 on Google Patents
• PCT/RU2003/000581 (WO international filing)
• US6488233B1 (Myrabo Lightcraft, parallel US development)

This information was compiled from Break_thrus.mdx staging file.