Low Orbit Launch Vehicle (LOLV)


Dedicated, Low-Cost Orbital Launch Services for Small Satellites


Launch System Update

Low Orbit Launch Vehicle (LOLV)

The Manned Spacecraft Low Orbit Launch Vehicle (LOLV) is a cutting-edge spacecraft designed to transport astronauts and essential payloads to low Earth orbit (LEO) safely and efficiently. Leveraging advanced propulsion systems, composite materials, and state-of-the-art avionics, the LOLV is engineered to meet the rigorous demands of modern space exploration. With a focus on crew safety, reliability, and reusability, the LOLV is poised to revolutionize human access to space.

200-400 km


LEO insertion altitude

3 to 5 minutes


Mission Duration

Up to 6 astronauts


Crew Module Capacity

Launch Vehicle Configuration

  • Stages: Two-stage configuration
  • Height: 70 meters (including payload)
  • Diameter: 5.2 meters
  • Mass: 600,000 kg (fully fueled)

Payload Capacity

  • Crew Module Capacity: Up to 6 astronauts
  • Payload to LEO: 22,000 kg
  • Cargo Compartment Volume: 50 m³ (including life support systems and crew equipment)

Crew Module

  • Interior Volume: 15 m³
  • Life Support Duration: 7 days (independent of station resupply)
  • Environmental Control: Closed-loop life support system (oxygen generation, CO2 scrubbing)
  • Safety Features: Redundant systems, emergency abort capability, heat shield for re-entry
  • Communication Systems: High-bandwidth communication link, real-time telemetry, and audio/video uplink

Propulsion Systems

  • First Stage:
    • Engines: 9 liquid rocket engines (Methane/Liquid Oxygen)
    • Thrust: 8,000 kN (vacuum)
    • Burn Time: 180 seconds

  • Second Stage:
    • Engines: 1 vacuum-optimized liquid rocket engine (Methane/Liquid Oxygen)
    • Thrust: 1,200 kN (vacuum)
    • Burn Time: 420 seconds
  • Thrust-to-Weight Ratio: 1.25 (at liftoff)

Avionics and Guidance

  • Flight Control: Triple-redundant fly-by-wire system
  • Navigation: Inertial navigation system with GNSS augmentation
  • Guidance: Autonomous trajectory correction and docking system
  • Sensors: Multi-spectral imaging, LIDAR for docking, radar altimeters

Reusability

  • First Stage: Fully reusable with vertical landing capability
  • Second Stage: Partially reusable (engine and avionics recovery)
  • Refurbishment Cycle: 10 flights with minor refurbishment, major overhaul every 50 flights

Launch Operations

  • Launch Site: Cape Canaveral Space Launch Complex
  • Launch Window: 1-hour daily launch window (adaptive to multiple orbital inclinations)
  • Turnaround Time: 2 weeks for stage refurbishment

Mission Profile

  • Orbit Insertion: LEO insertion at 200-400 km altitude
  • Mission Duration: Typically 1 to 3 weeks (dependent on mission parameters)
  • Return and Recovery: Splashdown in designated ocean recovery zones, or runway landing for the first stage

Safety and Redundancy

  • Abort System: Integrated launch escape system with high-thrust abort motors
  • Redundancy: Dual-redundant avionics and propulsion controls, independent power systems for critical functions
  • Crew Safety: Extensive simulation and testing, with a focus on fail-safe mechanisms

Materials and Construction

  • Primary Structure: Carbon-fiber reinforced polymer (CFRP) with titanium alloys
  • Heat Shield: Ablative material with thermal protection system (TPS) tiles
  • Propellant Tanks: Cryogenic tanks with composite overwrapped pressure vessels (COPV)

Building a Global Spaceport Network

Vertotech’s launch services are currently available from two U.S. spaceports to a broad range of orbital inclinations.

We plan to provide more access to space from more places on Earth – with additional spaceports coming online in 2026 & beyond.

World Map