Phoenix Launch Vehicle

22 kg to 400 km LEO
Rapid Launch

Plug Nozzles-The Ultimate Customer Driven Propulsion System – This classic paper provides a good description and understanding of our vision for the optimal launch vehicle.

First Stage

  • 80 kN “plug cluster” aerospike engine with 6 individual combustors
  • Differential throttling thrust vector control
  • High-pressure electric pumps
  • Additively manufactured components
  • Environmentally-friendly hypergolic propellant
  • Composite primary airframe structure


Second Stage

  • Single engine derived from first stage combustor optimized for altitude
  • Environmentally-friendly hypergolic propellant
  • Composite primary airframe structure


Third Stage

  • High-performance conventional solid rocket motor
  • Multiple configurations tailored to specific mission requirements
  • Autonomous Flight Safety System
  • Built upon the design for NASA’s reference Autonomous Flight Termination Unit and CASS software from the U.S. Air Force
  • Lower-cost than traditional FTS hardware (transceiver,transcoder, radio, etc)
  • Eliminates the need for range-based assets like radar which dramatically lowers small vehicle launch cost

Low-Cost Avionics

  • Based on existing sounding rocket avionics evolved to support advanced high-fidelity control and powered landing
  • Leverages state of the art COTS components to minimize hardware cost


Nanosatellite Payload

  • Accommodates a mix of cubesat 1,2 and 3U configurations up to 3 6U spacecraft or one 16U satellite
  • Compatible with almost any cubesat that conforms to the Cubesat Standard
  • Non-standard configurations can be accommodated on dedicated missions
  • Spacecraft may be powered on during countdown and ascent and may transmit telemetry via vehicle interface
  • Spacecraft may contain pressure vessels and propulsion systems