Skyrora XL
Skyrora
Three-stage small satellite orbital launch vehicle targeting Sun-Synchronous and Polar orbits.
Technical specifications
- Length
- 22.7 m
- Diameter
- 2.2 m
- Lift-off mass
- 55,838 kg
- Payload mass to SSO
- Up to 315 kg
- Propellant
- HTP / Kerosene
- Max G-load
- 5 g
- Target orbits
- SSO (500–1,000 km), Polar (200–1,000 km)
- Number of stages
- 3
- Stage 1 engines
- 9 × Skyforce (turbopump)
- Stage 1 thrust (sea level)
- 70 kN
- Stage 1 thrust (vacuum)
- 79.7 kN
- Stage 1 ISP (sea level)
- 250.24 s
- Stage 1 ISP (vacuum)
- 284.91 s
- Stage 2 engine
- 1 × Skyforce (turbopump)
- Stage 2 thrust (vacuum)
- 85 kN
- Stage 2 ISP (vacuum)
- 306 s
- Stage 3 engine
- 1 × LEO engine (pressure-fed, multi-ignition)
- Stage 3 thrust (vacuum)
- 3.5 kN
- Stage 3 ISP (vacuum)
- 305 s
About
Skyrora XL is a three-stage light-class orbital launch vehicle developed by Skyrora Limited (UK). It is designed to place payloads into Sun-Synchronous Orbit (SSO) between 500 km and 1,000 km altitude, and into Polar Orbit between 200 km and 1,000 km altitude. The vehicle uses HTP (High Test Peroxide) and kerosene as propellants across all stages.
First Stage: Nine Skyforce engines, turbopump-fed, producing 70 kN (sea level) / 79.7 kN (vacuum) of thrust, ISP of 250.24 s (sea level) / 284.91 s (vacuum).
Second Stage: One Skyforce engine, turbopump-fed, producing 85 kN of thrust in vacuum, ISP of 306 s.
Third Stage: One LEO engine, pressure-fed, producing 3.5 kN in vacuum, ISP of 305 s; capable of multiple re-ignitions.
The launch infrastructure uses a modular design with components not exceeding standard 40 ft ISO container dimensions, enabling rapid assembly and portable launch from multiple locations. The payload module uses a carbon-fiber composite fairing released by push-rod springs at altitude.
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.