Due to the fact that it is a guided vehicle, Skylark L has an onboard control system and thrust vector control system, as well as a roll control system. During flight, the onboard control system operates guidance algorithms to correct the flight course when any disturbance factors occur. Control of the launch vehicle at the boost phase of launch along pitch and yaw axes is ensured by the deviation of the combustion chamber of the main engine. Control of the launch vehicle at the boost phase of launch along the roll axis and control of the pitch and yaw at the coast stage of launch is ensured by the roll control system.
- Length 11.65 m
- Diameter 0.7 m
- Lift-off mass 2,466 kg
- Payload mass 50 kg
- Propellant HTP / KEROSENE
- Apogee altitude 102 km
- Time to apogee (from launch) 225 s
- Max G-load 3.7 G
- Maximum velocity 950 m/s (MACH 3.5)
Regeneratively cooled liquid rocket engine using a pressure fed system.
Nominal thrust of the main engine:
- 31kN above sea level
- 35kN in vacuum
Nominal specific impulse:
- 229 seconds above sea level
- 272 seconds in vacuum
Skyrora utilise high grade materials, namely polymers such as epoxy, vinyl ester, polyester resins and fibres, glass, carbon, and aramid in order to provide the best physical and mechanical properties of composite parts to maintain a high standard of quality that is essential within the aerospace industry.
All of the parts used to make up the launch system have been developed by Skyrora, with the majority of these parts having already undergone successful testing and now in operation, the remaining parts are undergoing the latter stages of testing.
The command centre is designed for centralised control of launch vehicle preparation, as well as launch and control of various system processes.
COMPRESSED GAS SUPPLY SYSTEM
The compressed gas supply system is designed to fill the pressurised tank with compressed helium.
FUEL FILLING SYSTEM
The purpose of the fuel filling system is to allow the location of the launch site to be changed; to provide short-term storage of fuel; to fill the launch vehicle itself with fuel; and to drain fuel from the launch vehicle.
FUEL FILLING SYSTEM
The purpose of the oxidiser fuel filling system is to provide short-term storage of oxidiser; to fill the launch vehicle with itself with oxidiser; and to drain oxidiser from the launch vehicle.
MOBILE POWER STATION
The mobile power station is intended to power the launch site parameters, powering the 160 kVA diesel generator which will power all of the units within the area of launch.