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SKYLARK L


THE SUBORBITAL LAUNCH VEHICLE

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.

engine

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
skylark L engine
skylark L rocket

advantage

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.

CHARACTERISTICS

  • Length 10870 mm
  • Diameter 712 mm
  • Lift-off Mass 2466 kg
  • Payload Mass 50 kg
  • Propellent HTP/Kerosene
  • Thrust above sea level 30 kN
  • Apogee Altitude 102 km
  • Time to Apogee (from launch) 225 s
  • Maximum Acceleration 3.7 g
  • Maximum Velocity 950 m/s (Mach 3.5)

materials

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 3D printing.

We use advanced technologies and process automation.

flight profile

skylark L flight profile

launch site

If necessary, there is the potential for co-investment in equipment to allow for future use at the location.

The required equipment includes the following:
  • Telemetry ground station
  • Tracking ground system
  • FTS ground station
skylark L fuel filling system

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
skylark L transporter erector launcher

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
  • Rocket launch
skylark L command centre

COMMAND CENTRE

The Command Centre is designed for centralised control of launch vehicle preparation for the launch and control of pressure systems.
skylark L oxidiser filling system

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
skylark L compressed gas supply system

COMPRESSED GAS SUPPLY SYSTEM

Compressed gas supply system is designed for filling the pressurised tank with compressed helium of required parameters.
skylark L mobile power station

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.
skylark L  payload module

PAYLOAD MODULE

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.
Indicate interest

Indicate interest
skylark L render
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