ROCKET FAMILY

Suborbital rocket

Orbital rocket / Mk1

Orbital rocket / Mk2

Suborbital rocket

Orbital rocket / Mk1

Orbital rocket / Mk2

ORBITAL ROCKET / Mk2

PAYLOAD BAY

PAYLOAD

250 kg @ LEO

VOLUME

2.6 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

PROPELLANTS

HTPB/LOx

NOZZLE

BELL-SHAPED (vacuum)

This engine provides a nominal thrust of 30 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

PROPELLANTS

HTPB/LOx

NOZZLE

AEROSPIKE

Each engine provides a nominal thrust of 200 kN and peaks to 300 kN at lift-off. Combustion from HTPB/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 an aerospike nozzle to benefit from highest propulsive efficiency during ascent and atmosphere pressure variation.

UPPER STAGE

BURN TIME

300 s

THRUST

30 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.

BOOSTER

BURN TIME

150 s

THRUST

200 kN

The booster propels the upper stage and its payload to the edge of space. It is powered by a single engine capable of 200 kN of nominal 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. It is reignited several times during reentry and for soft landing into the ocean.

PAYLOAD BAY

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).

PAYLOAD

250 kg @ LEO

VOLUME

2.6 m3

UPPER STAGE

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.

BURN TIME

300 s

THRUST

30 kN

UPPER STAGE ENGINE

This engine provides a nominal thrust of 30 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.

PROPELLANTS

HTPB/LOx

NOZZLE

BELL-SHAPED (vacuum)

BOOSTER

The booster propels the upper stage and its payload to the edge of space. It is powered by a single engine capable of 200 kN of nominal 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. It is reignited several times during reentry and for soft landing into the ocean.

BURN TIME

150 s

THRUST

200 kN

BOOSTER ENGINE

Each engine provides a nominal thrust of 200 kN and peaks to 300 kN at lift-off. Combustion from HTPB/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 an aerospike nozzle to benefit from highest propulsive efficiency during ascent and atmosphere pressure variation.

PROPELLANTS

HTPB/LOx

NOZZLE

AEROSPIKE

HEIGHT

250 kg

PAYLOAD

250 kg

STAGES

2

DIAMETER

1.6 m

LIFTOFF MASS

20 T

BOOSTER

Recoverable/Reusable