Dedicated two-stage smallsat launch vehicle for payloads up to 100 kg
C6 Rocket
Dedicated two-stage smallsat launch vehicle for payloads up to 100 kg
Description
The C6 Rocket is C6 Launch Systems' dedicated small-satellite launch vehicle, designed to maximize the use of proven, commercial-off-the-shelf (COTS) technology to de-risk launch for customers. Proprietary systems integration, avionics, telemetry and communications, and fuel tank design bring the components together into a reliable rocket serving nano and micro satellites. The vehicle is a two-stage design: the first stage uses three LOX-kerosene engines and the second stage a single LOX-kerosene engine, together generating 20 kN of sea-level thrust. It carries a clamshell fairing for reliable payload separation and deployment, and is sized to loft up to 100 kg to a 600 km Sun-Synchronous Orbit (SSO). The rocket is easily transportable and can be launched from multiple sites, bringing the launch to the customer rather than the customer to the launch, with full access to all orbits from 0° to 110° inclination. C6 Launch has signed a Letter of Intent with SaxaVord Spaceport in Unst, Scotland as its preferred smallsat launch location, and has been awarded a contract by the Brazilian Space Agency (AEB) and Brazilian Air Force (FAB) to bring orbital launches to the Alcântara Space Center on Brazil's equatorial northern coast. Additional launch sites in Scandinavia are under discussion to extend the launch network and provide backup options for weather or scheduling. The primary nominal orbit from SaxaVord is a 600 km SSO, while equatorial and low-inclination orbits are available from Alcântara, with polar and inclined orbits also serviceable. C6 Launch targets a minimum of 24 launches per year to help eliminate existing launch backlogs for smallsat payloads.
Specifications
| Height | 13 meters |
|---|---|
| Diameter | 1 meter |
| Number of stages | 2 |
| Stage 1 configuration | Three LOX-kerosene engines |
| Stage 2 configuration | Single LOX-kerosene engine |
| Payload capacity | 100 kg to 600 km Sun-Synchronous Orbit (SSO) |
| Fairing type | Clamshell, for reliable separation and deployment |
| Fairing diameter | 1.5 meters |
| Second stage length | 4 meters |
| First stage length | 7.2 meters |
| Engine propellant | LOX-kerosene |
| Engine thrust | 20 kN sea-level thrust |
| Orbit inclination range | 0° to 110° |
| Target launch cadence | Minimum 24 launches per year |