Magnetic propulsion for spacecraft, from very low Earth orbit to deep space.
Leyden Space is developing LAUREN, a variable specific impulse magnetic propulsion system for spacecraft from the CubeSat class upward.
To remove propulsion as the limiting factor in spacecraft mission lifetime, operating altitude and range.
Propulsion sets the limits of a space mission.
- 01
Propellant mass bounds mission life
A spacecraft's total velocity change is fixed by the propellant it carries at launch. When that budget is exhausted, an otherwise functional satellite must be retired.
- 02
Aerodynamic drag at low altitude
Lower orbits improve imaging resolution and link performance, but the residual atmosphere causes orbital decay. Near 300 km, an unpropelled satellite reenters within months.
- 03
Constraints of existing thrusters
Conventional electric thrusters operate at a fixed specific impulse, depend on high-cost propellants such as xenon, and contain erosion-prone components that limit operating life.
LAUREN: one engine core, two configurations.
LAUREN, the Low Activation Unit for Repositioning and Electromagnetic Navigation, is a magnetic propulsion system for spacecraft. A common engine core, power electronics and controller are offered in two configurations, selected according to operating altitude.
Sustained operation in very low Earth orbit.
Between approximately 250 and 450 km, atmospheric drag limits unpropelled missions to weeks or months. This configuration collects residual atmospheric gas along the flight path and uses it as propellant, supplemented by a small onboard reserve, to compensate for drag continuously.
- Higher ground resolution for a given optical aperture
- Reduced path loss and latency on communications links
- Passive reentry at end of mission, leaving no long-lived debris
High-efficiency propulsion for LEO, GEO and beyond.
Above the altitude range in which atmospheric collection is practical, LAUREN operates from an onboard propellant supply. High specific impulse reduces the propellant mass fraction required for a given velocity change, releasing mass and volume for the payload.
- Station-keeping and collision-avoidance maneuvers
- Orbit raising and phasing after rideshare deployment
- Post-mission disposal
- Low-thrust transfers to geostationary orbit, cislunar space and beyond
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Variable specific impulse
Thrust and specific impulse are adjustable in flight, so a single engine can perform both time-critical maneuvers and propellant-efficient transfers.
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Extended operating life
The architecture avoids the erosion-limited components that determine the service life of conventional electric thrusters.
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Low-cost propellants
Compatible with inexpensive, widely available propellants, reducing exposure to xenon cost and supply constraints.
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Common engine core
Both configurations share one engine core, power electronics and controller, designed to scale from CubeSat-class spacecraft to larger platforms.
Target markets across four orbital regimes.
Each regime places a different demand on propulsion. The two LAUREN configurations are intended to address all four.
Very low Earth orbit
Earth-observation and communications operators gain resolution and link margin at lower altitude. Sustained operation there has previously required a large propellant load or acceptance of a short mission life.
Air-breathing configurationLow Earth orbit constellations
Constellation spacecraft must reach operational orbits after rideshare deployment, maintain them, perform collision-avoidance maneuvers, and meet post-mission disposal requirements.
Stored-propellant configurationGeostationary orbit
Geostationary spacecraft expend propellant each year on station-keeping. Higher propulsive efficiency reduces launch mass or extends service life.
Stored-propellant configurationCislunar and deep space
Beyond Earth orbit, the required velocity change is large and propellant dominates spacecraft mass. Higher specific impulse reduces that mass and widens the range of missions a spacecraft can perform.
Stored-propellant configurationOperational and regulatory drivers.
Improvement in ground resolution for a given imaging system at 300 km relative to 550 km.
Approximate orbital lifetime of an unpropelled 100 kg-class satellite at 300 km under average solar activity.
Maximum post-mission orbital lifetime for LEO satellites under the FCC rule adopted in 2022.
Development roadmap.
LAUREN is currently in development. Commercial availability follows ground validation and an in-orbit demonstration.
- Current phase
Laboratory validation
Vacuum-chamber testing of engine hardware to verify modeled performance.
- Next phase
In-orbit demonstration
A dedicated demonstration spacecraft to characterize both configurations in the orbital environment.
- Subsequent
Commercial availability
Flight units in both configurations for satellite manufacturers and operators.
Founded at the Colorado School of Mines.
Leyden Space originated in the Colorado School of Mines Rocket Research Lab and is based in Golden, Colorado.
Partnership and mission inquiries.
Contact us to discuss partnership, mission integration or the LAUREN development program.