The technical design utilizes a monolithic first stage composed of six merged trapezoidal segments sharing internal walls to form a single rigid airframe. This creates a hexagonal geometry with a central divergent void that functions as an expansion chamber. The mission profile follows a direct ascent trajectory, acting as an atmospheric elevator where the booster remains subsonic during the whole flight to minimize aerodynamic drag and structural stress. The first stage transports modular upper stages to an altitude of 80 to 100 km before performing a vertical return-to-base maneuver as a single unit.
Propulsion is handled by a distributed array of aerospike engines located at the base of the hexagonal assembly. These engines provide continuous altitude compensation from sea level to vacuum conditions and utilize differential throttling for attitude control, eliminating the mass and complexity of traditional gimbaling hardware. The central void is utilized as an air-augmentation duct and afterburner during the low-altitude ascent phase below 30 km. In this regime, the high-velocity exhaust from the aerospikes creates a low-pressure zone that entrains atmospheric air through the nose. As the air mixes with fuel-rich exhaust and expands through the divergent rear exit, it increases the effective specific impulse and reduces propellant consumption by approximately 15 to 20 percent.
Stability and recovery are integrated into the airframe geometry. The flat longitudinal surfaces of the hexagonal prism provide passive aerodynamic stabilization and roll damping, removing the requirement for external fins. During descent, the central void acts as a solid parachute by creating high passive drag, which reduces terminal velocity and stabilizes the vertical orientation without extending legs or grid fins. The vertical profile minimizes lateral loads and bending moments, allowing for a lighter structure constructed primarily from standardized flat metal sheets.
The upper stage architecture consists of six independent trapezoidal rockets nested within the booster footprint. These modules can be deployed individually to reach different orbital planes in a single launch event, providing a logistics advantage for satellite constellation deployment. The modules can also be structurally coupled in clusters of two or three for high-energy missions such as geostationary transfer or lunar transport. For a lunar transporter mission, four units provide orbital insertion while the remaining two execute the trans-lunar injection. This modularity allows the system to scale for diverse mission energy requirements without redesigning the core airframe logic.
Strategic and operational benefits include high geographical independence for launch operations. The vertical ascent and return profile require minimal downrange exclusion zones, allowing countries with territorial constraints or neighboring borders to operate launch facilities safely. Because the upper stages achieve orbital velocity before separation or within the vacuum phase, the risk of stage impact on foreign soil is mitigated. The use of standardized components and a single engine type across all stages simplifies the manufacturing process and increases production throughput. This architecture provides a future-proof platform for orbital logistics and interplanetary exploration.
