The Startup Pulsar Fusion is proposing a 2 Megawatt nuclear fusion orbital components for 2027. Pulsar has now proceeded to phase 3, the manufacture of the initial test unit. Static tests are to begin in 2025 followed by an In Orbit Demonstration (IOD) of the core technology components in 2027.
With Sunbird in Orbit: A spacecraft launches to LEO (~9.4 km/s), docks with a Sunbird, and then the Sunbird's fusion propulsion handles the rest. 3-5 km/s to Mars or 6-10 km/s to Jupiter. The initial launch vehicle only needs enough delta-V to reach orbit, not the full interplanetary trip.
It is designed to produce both thrust and electric power for interplanetary spacecraft.
Long-term source of acceleration
Self-sustaining fuel supply
Can potentially propel a spacecraft with a mass of about 1,000 kg (2,200 lb) to Pluto in 4 years
2 MW of power to the payloads
Designers think that this technology can radically expand the science capability of planetary missions
Sunbird's high specific impulse (10,000-15,000 s) and 2 MW power mean it can efficiently provide the additional delta-V with minimal propellant, thanks to its fusion-driven exhaust velocity (~98,100-147,150 m/s). This could cut the total delta-V burden on the launch vehicle by 20-50%, depending on the destination, and massively reduce fuel mass -- making missions cheaper, lighter, and more flexible.
1. Rapid Cargo Delivery to Mars
[CAR_GO > MARS]
Mission Description: Transporting 1000-2000 kg of commercial cargo (e.g., habitats, rovers, or supplies) to Mars orbit in under 6 months, docking with a pre-launched spacecraft in LEO.
Power Generation Advantage: The DDFD's 2 MW output (with ~1 MW auxiliary power) supports high-bandwidth data relays and powers onboard systems (e.g., refrigeration for perishables or laser comms), eliminating solar panel reliance in Mars' weaker sunlight (588 W/m² vs. 1361 W/m² at Earth).
Delta-V Reduction: Launch to LEO requires ~9.4 km/s, but the Sunbird handles the ~3.6 km/s trans-Mars injection (TMI) and ~1.5 km/s Mars orbit insertion (MOI), cutting total mission delta-V from ~14.5 km/s to ~9.4 km/s -- a 35% reduction. This slashes launch vehicle propellant by ~50%
Unique Advantage: Faster transit (150 days vs. 210+ with chemical propulsion) and reduced launch costs enable frequent, cost-effective commercial Mars logistics.
2. Outer Planet Science Probe Deployment (Jupiter/Saturn)
Mission Description: The Sunbird fusion engines ferry a 1000 kg science probe to Jupiter (5.2 AU) or Saturn (9.5 AU) in 2-4 years, deploying it into orbit for detailed study (e.g., Europa's subsurface ocean or Titan's atmosphere).
Power Generation Advantage: The 2 MW DDFD provides ~1 MW to the probe upon arrival, powering high-energy instruments (e.g., radar, plasma detectors) and beaming data back at gigabit rates -- unfeasible with solar power at 5-10% Earth's intensity (50-15 W/m²).
Delta-V Reduction: From Earth, Jupiter requires ~14.4 km/s (9.4 km/s to LEO + 5 km/s transfer) and Saturn ~15.7 km/s. Docking with Sunbird in LEO drops this to 9.4 km/s for launch, with Sunbird covering ~6.1 km/s (Jupiter) or ~7.4 km/s (Saturn) -- a 30-40% delta-V cut. Propellant mass drops by ~60% for the launch vehicle.
Unique Advantage: High power at destination and reduced launch mass enable larger, more capable probes to outer planets, slashing transit time vs. chemical (7-8 years to Saturn).
3. Lunar Orbital Supply Hub
[LEO > MOON]
Mission Description: The Sunbird serves as a reusable LEO-to-Moon transfer vehicle, delivering 1500 kg of supplies (e.g., fuel, water, or equipment) to lunar orbit for commercial stations or landers.
Power Generation Advantage: The ~1 MW auxiliary power supports in-orbit processing (e.g., electrolysis for fuel) and powers docking systems or laser-based debris tracking, critical in the crowded lunar environment.
Delta-V Reduction: A full Earth-to-lunar orbit trip needs ~15.1 km/s (9.4 km/s to LEO + 5.7 km/s). With Sunbird in LEO, the launch delta-V drops to 9.4 km/s, and Sunbird covers the ~4.1 km/s LEO-to-lunar orbit leg (using Oberth effect) -- a 38% reduction. Launch propellant mass decreases by ~55%.
Unique Advantage: Reusability and high power reduce costs for sustained lunar commerce, supporting a cislunar economy with minimal launch overhead.
4. Asteroid Mining Transport
[MINING_EQUIPMENT > NEA]
Mission Description: The Sunbird transports mining equipment (1000 kg) to a near-Earth asteroid (NEA) and returns up to 500 kg of extracted resources (e.g., water, metals) to LEO.
Power Generation Advantage: The 2 MW fusion rockets power mining ops (e.g., drilling, ore processing) with ~1 MW, far exceeding solar capabilities at 1-2 AU, and supports high-rate data transfer for remote operation.
Delta-V Reduction: NEA missions vary (e.g., ~12-14 km/s total from Earth). Docking with Sunbird in LEO cuts launch delta-V to 9.4 km/s, with Sunbird handling ~3-5 km/s to the asteroid and back (often aided by aerobraking on return) -- a 25-40% reduction. Launch mass savings exceed 50%.
EIGHT MARSRANGER 10kW HET 's adjust Sunbird's trajectory for NEA intercept and maintains position during mining to avoid DDFD fuel use for low-thrust manoeuvres.
Unique Advantage: High power and delta-V efficiency enable heavier equipment and faster round-trips (1-2 years vs. 3+), boosting asteroid mining profitability.
5. Deep Space Telescope Ferry
[TELESCOPE > 0RBIT]
Mission Description: The Sunbird delivers a 1000 kg next-gen telescope to a distant orbit (e.g., 100 AU or Sun-Earth L2) for unparalleled astronomical observation.
Power Generation Advantage: The ~1 MW auxiliary power drives advanced cooling systems (e.g., cryogenics for IR detectors) and high-bandwidth comms, enabling real-time data streaming from vast distances where solar power is negligible (<14 W/m² at 100 AU). Delta-V Reduction: L2 requires ~12.7 km/s from Earth (9.4 km/s to LEO + 3.3 km/s); 100 AU needs ~20 km/s+. Sunbird in LEO reduces launch to 9.4 km/s, covering ~3.3 km/s (L2) or ~10-15 km/s (100 AU) -- a 26-50% delta-V cut. Launch propellant drops by 40-60%. FOUR MARSRANGER 10kW HET 's ensure precise LEO station-keeping pre-mission and performs final orbit insertion at L2 or heliocentric drift for long-term stability without DDFD fuel burn. Unique Advantage: High power and reduced launch costs make ambitious observatories feasible, placing them far beyond current limits (e.g., JWST at L2) with shorter transit times.