Stages

Third Stage

Propulsion: 1 x LEO engine
Propellant feed system: Pressure fed
Thrust in vacuum: 3.5kN
ISP in vacuum: 305s
Engine has the ability to re-ignite multiple times

FIRST STAGE

Propulsion: 9 x Skyforce engines
Propellant feed system: Turbopump

Thrust:
Above sea level: 70kN
In vacuum: 79.7kN

ISP:
At sea level: 250.24s
In vacuum: 284.91s

SECOND STAGE

Propulsion: 1 x Skyforce engine
Thrust in vacuum: 85kN
Propellant feed system: Turbopump
ISP in vacuum: 306s

specifications

  • Length 22.7 m
  • Diameter 2.2 m
  • Lift-off mass 55,838 kg
  • Payload mass Up to 315 kg
  • Propellant HTP / kerosene
  • Max G-load 5 g

Flight profile

MOBILE LAUNCH COMPLEX

All of the engineering systems of the launch site are of a modular design. Any module size will not exceed a standard 40ft ISO container. Launch vehicle and spacecraft assembly and testing is achievable through rapid erectable methods of construction, whereby the launch pad for the orbital launch vehicle is a sectional and portable unit.

THIS VERSION OF THE LAUNCH SITE ALLOWS:
  • The launch site location to be interchangeable
  • Launch services to be provided without impacting the spaceport infrastructure
  • Launch services to be provided that involve the spaceport infrastructure
  • Rapid preservation and de-preservation of a site to be ensured
launch complex mobile

PAYLOAD MODULE

The payload module within the orbital launch vehicle hosts the payload. In order to meet the requirements of the customer’s payload during installation, maintenance, and operation, Skyrora utilise an encapsulated payload module whereby assembly is achieved as a standalone to the launch vehicle. The payload module consists of the payload fairing and adapter, dispenser (if required), and other systems to ensure safe operation during pre-launch processes and flight.

The payload fairing casing consists of two halves composed of a 3-layer composite shell with a honeycomb filler. Bearing layers are made of a carbon-fiber composite. When the rocket reaches the required altitude, the halves of the payload fairing are released with the help of push-rod springs installed on the payload fairing casing.

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