PAYLOAD BAY

  • Payload : 200 kg at LEO
  • Volume : 2,8 m3

The payload bay is 1.2 m in diameter and 2.5 m in length, providing a large volume available to accommodate the satellite(s).

Engine

  • Propellant : HDPE / LOx
  • Nozzle : Bell Shaped (vacuum)

This engine provides a maximum thrust of 100 kN with the ability to throttle down for precise orbit insertion. To be compliant with mission requirement and space debris policy, the engine can be reignited multiple times. It is equipped with a bell-shaped nozzle adapted to vacuum conditions.

Engine

  • Propellant : HDPE / LOx
  • Nozzle : Bell Shaped

Each engine provides a max thrust of 100 kN. Combustion from HDPE/LOx propellants do not produce toxic fumes. The fumes are harmless for the inhabitants and wildlife surrounding the launching area. This booster stage engine is equipped with a bell shaped nozzle to benefit from highest propulsive efficiency during ascent and atmosphere pressure variation.

OB1-MK1

upper stage

  • Burn time : 300 s
  • Thrust : 100 kN

The upper stage propel the payload to the targeted orbit. It is powered by a single engine. The upper stage is designed to be capable of delivering multiple satellites on different orbits and it deorbits itself after mission completion.

Boosters

  • Burn time : 150 s
  • Thrust : 700 kN

The booster propels the upper stage and its payload to the edge of space. It is powered by a cluster of 7 engines each of them capable of 100 kN of maximum thrust. The booster is designed to modulate its thrust to reduce the intensity of the maximum aerodynamic pressure. After being jettisoned the booster stage dives back to Earth.