Skylark L is a guided single-stage suborbital launch vehicle.
Launch is performed vertically from a fixed launching pad.
As Skylark L is a guided vehicle, it has onboard control system, thrust vector control
system and roll control system. During the flight, the launch vehicle control system
operates guidance algorithms which correct the flight when disturbance factors may appear.
During powered flight the vehicle is steered by moving the rocket engine to direct the thrust,
with small additional cold thrusters to control roll.
Regeneratively cooled liquid rocket engine with a pressure fed system.
Nominal thrust of the main engine:
30 kN above sea level
35 kN in vacuum
Nominal specific impulse:
229 sec above sea level
272 sec in vacuum
The original purpose of Skylark L was to complete final checks on sub systems prior to use in Skyrora XL.
Completion of the prototype vehicle has created a new market with universities and research facilities.
Skylark L can be used for micro gravity experiments at a lower cost than an orbital vehicle,
while taking advantage of Skyrora’s environmentally conscious fuel combination.
Lift-off Mass2466 kg
Payload Mass50 kg
Thrust above sea level30 kN
Apogee Altitude102 km
Time to Apogee (from launch)225 s
Maximum Acceleration3.7 g
Maximum Velocity950 m/s (Mach 3.5)
Skyrora uses high grade materials, namely polymers:
epoxy; vinyl ester; polyester resins and fibres;
glass; carbon and aramid to create the best physical
and mechanical properties of composite parts to
allow for the high quality that is required in the aerospace industry.
Engine parts produced using
We use advanced technologies and process automation.
If necessary, there is the potential for co-investment in equipment to allow for future use at
The required equipment includes the following:
Telemetry ground station
Tracking ground system
FTS ground station
FUEL FILLING SYSTEM
Fuel Filling System is designed for:
The launch site location to be changed
Short-term fuel storage
Filling the launch vehicle with fuel
Draining fuel from the launch vehicle
TRANSPORTER ERECTOR LAUNCHER
Transporter erector launcher is designed for:
Transportation of the launch vehicle to the launch position
Mounting the launch vehicle on the launch position
The Command Centre is designed for centralised control of launch vehicle preparation for
the launch and control of pressure systems.
OXIDISER FILLING SYSTEM
Oxidiser Filling System is designed for:
Short-term storage of oxidiser
Filling the launch vehicle with oxidiser
Draining oxidiser from the launch vehicle
COMPRESSED GAS SUPPLY SYSTEM
Compressed gas supply system is designed for filling the pressurised tank with
compressed helium of required parameters.
MOBILE POWER STATION
Mobile power station is intended to power launch site parameters – 160kVA, 400V, 3Ph,
50Hz (diesel generator). The 160kVA generator powers all units along the launch area.
For the purpose of the launch mission,
Skylark L can ensure separation of the payload
or its integration with customer’s separation systems.
One of the basic features of the suborbital launch vehicle
is to provide the customer with long-continued microgravity
of a specified quality. The diagram covers
the performance capabilities of Skylark L.
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