ORBITAL LAUNCH VEHICLE

SKYRORA XL

Skyrora XL is a three stage, light class launch vehicle intended to place payloads into Sun-Synchronous Orbit (SSO) between a range of 500km and 1,000km in altitude. The vehicle is also intended to place payloads into Polar Orbit between a range of 200km and 1,000km in altitude.

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

Image Credit: Skyrora

Flight profile

MOBILE LAUNCH COMPLEX

All engineering systems within the launch site are of a modular design. Module sizes do not exceed a standard 40 ft ISO container. Rapid, erectable methods of construction enable launch vehicle and spacecraft assembly and testing, whereby the launch pad for the orbital launch vehicle is a sectional and portable unit.

This version of the launch site allows:

Launch from interchangeable locations
Launch services to be provided without impacting the spaceport infrastructure
Launch services to be provided involving the spaceport infrastructure
Rapid set-up and pack-down of a site

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.