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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
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
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
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
  • Rocket launch
COMMAND CENTRE
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.
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

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