Home / Divisions / Propulsion Systems

Aevum Propulsion Systems

Advanced thrust generation and energy conversion architectures engineered for aerospace, maritime, and heavy industrial applications. Multi-domain capability spanning chemical, electric, and experimental plasma drives.

Active Contracts 47
Certification Level MIL-STD-810H / ISO 9001:2015
Test Facilities 12 Global Sites
Max Thrust Output 2.4 MN
Core Architectures

Propulsion Systems

Modular drive configurations optimized for mission-specific performance envelopes.

STAGE 1 STAGE 2

Cryogenic & LOX/Kerosene

High-efficiency staged combustion cycles with active cooling manifolds. Designed for heavy-lift orbital insertion and atmospheric re-entry vehicle boost phases.

  • ⚙️
    Turbopump Architecture Gearless magnetic bearing drives, 98.2% mechanical efficiency
  • 🌡️
    Thermal Management Regenerative cooling channels, carbon-carbon composite liners
  • 📊
    ISP Performance 310-345s vacuum, throttleable 20%-100%
H2 PLASMA

Electro-Thermal Ion

Resistance and arc-jet heating systems converting electrical energy into thermal expansion. Ideal for satellite station-keeping and deep-space orbital transfers.

  • ⚡
    Power Processing6-30 kW input, MPPT-optimized solar array integration
  • 🔧
    Propellant FlexibilityHydrazine, Ammonia, or direct Hydrogen feed
  • 📈
    Thrust-to-Power0.4-0.6 N/kW, specific impulse 600-900s

Hall-Effect & Gridded Ion

Electrostatic acceleration of ionized xenon or krypton propellant. Ultra-long endurance systems for interplanetary missions and constellation maintenance.

  • 🌀
    Magnetic ConfinementHalbach array optimization, <0.5% leakage
  • 🛡️
    Erosion MitigationAdvanced cermet channel lining, 15,000+ hr LEO
  • 📉
    Mass Efficiency<0.5 kg/kW system mass, 4000s+ ISP

Plasma MHD Drives

Lorentz-force propulsion utilizing superconducting magnetic fields and ionized gas dynamics. Experimental architecture for next-generation hypersonic and orbital vehicles.

  • 🧲
    Field GenerationHigh-temp superconducting coils, 12T peak
  • 🔥
    Ionization ChamberRF helicon source, rapid startup <3s
  • 🚀
    Application ProfileHypersonic cruise, orbital maneuvering, marine
Technical Data

Performance Specifications

Verified operational parameters across certified drive configurations.

System Class Thrust Range Specific Impulse (ISP) Power Requirement Operational Env Status
AZ-LOX/K-400 120 kN – 2.4 MN 310s – 345s N/A (Chemical) Atmospheric / Vacuum FLIGHT CERTIFIED
AZ-ETH-9K 5 N – 45 N 600s – 900s 6 kW – 30 kW Orbital QUANTITY PROD
AZ-HEPT-200 0.05 N – 0.8 N 1600s – 4200s 2 kW – 15 kW Deep Space / LEO MISSION PROVEN
AZ-MHD-X1 10 kN – 85 kN 2800s (est.) 1.2 MW – 4.5 MW High-Alt / Orbital GROUND TEST
R&D Pipeline

Next-Generation Drives

Active research programs targeting breakthrough efficiency and novel propulsion paradigms.

Project Icarus VII Phase III

Nuclear-thermal electric hybrid architecture for rapid Mars transit. Closed-cycle fission reactor coupled with direct electric thrusters.

Ground Testing72%
Vortex Plasma Drive Phase II

Magnetoplasma dynamo configuration eliminating physical grilles. Targets 8000s ISP with ceramic matrix composite channel walls.

Component Validation45%
Quantum-Stabilized MHD Phase I

Theoretical plasma confinement using superconducting quantum interference devices. Requires cryogenic infrastructure and novel power topologies.

Simulation & Modeling18%
Compliance & Standards

Certifications

Globally recognized engineering and safety accreditations.

🛡️ FAA Type Certificate
🌍 EASA Part 21J
⚙️ MIL-STD-810H
📋 ISO 9001:2015
🔒 ITAR Compliant
🔬 AS9100 Rev D
Engineering Integration

Partnership Inquiry

For OEM integration, defense contracting, or academic collaboration requests.