Garuda is an affordable launch vehicle under development at Bellatrix Aerospace. It falls in the medium lift category. It's a two stage rocket designed for complete re-use. It will feature a revolution in the field of rocket engineering by incorporating several innovations such as a next generation propulsion system and ingenious stage recovery mechanisms. Garuda will employ carbon composites in more than 80% of its construction.
1010kg to 700km Sun Synchronous Orbit
Designed to take multiple satellites to their dedicated orbits
Simple to integrate the payload
Payload Fairing Height 4m
Payload Fairing Diameter 3m
Garuda, for the first time, will feature a unique thermodynamic cycle for its first stage engine. This engine called Kalam, will feature combustion tap-off cycle, i.e. it uses a pump-fed engine design with a tap-off cycle to take small amount of combustion gases from main combustion chamber to power the engine turbopumps. This produces high impulse and is much simpler than pre-burning staged combustion because of its single combustion chamber and graceful shut down mode. This engine is designed to generate 800kN thrust in vacuum.
The second stage of Garuda will use a single Aeon engine. This stage is designed for multiple restart capability. The Aeon engine will feature turbo-pumps driven by Brushless DC motors powered by advanced batteries. This will eliminate the need for complex turbo-machinery and highly complex plumbing. This engine is designed to generate 41kN thrust in vacuum.
to 700km sso
sea level thrust
Both the stages of Garuda will use Liquid Methane and Liquid Oxygen as its propellants. These are clean burning fuels. Clean burning do not produce carbon compounds (coking), making it easier for reuse. This propellant combination also provides high specific impulse. Many rocket engines employ helium pressurization system is extremely complex and carries certain risk.
Garuda is designed to launch payloads in sun synchronous orbits and inclined orbits. The vehicle is capable of launching remote sensing satellites into polar sun synchronous orbits and small communication satellites to GTO. It is designed to be capable of launching multiple satellites in the same launch mission and placing satellites in equatorial, inclined as well as polar orbits.
The avionics are responsible for control and monitoring of the engines, launch sequencing, trajectory planning, guidance, navigation and control from the beginning of the countdown all the way to orbit. To shrink our development time and costs, we use distributed computing architecture with a focus on common hardware and modularity across each rocket stage and function.