Modular Multi-Chamber Liquid Propulsion

Modular Multi-Combustion Engine Architecture

Our propulsion product line inherits the coaxial turbopump and clustered multi-combustion design concept from mature RD-170 / RD-180 propulsion systems, fully miniaturized for small-thrust application scenarios targeting upper-stage orbital transfer and satellite onboard propulsion replacement for toxic monopropellant systems.

• Dual combustion chamber configuration: combined nominal thrust ~230 kgf
• Quad combustion chamber configuration: combined nominal thrust ~450 kgf
• Single combustion chamber unit configurable at ~130 kgf thrust for flexible combination and capacity scaling
• Supports assembly into low-cost launch vehicles ranging from 1 ton to 2 tons lift-off mass

Three Propellant Configuration Routes

• Standard high-performance route: Liquid Oxygen + Methane / Liquid Oxygen + Kerosene, oriented for formal commercial orbital launch, satellite upper stage and long-duration in-orbit tasks.
• Low-cost rapid iteration route: High-Test Peroxide (HTP) paired with hydrocarbon fuels / aviation kerosene, optimized for fast prototyping, low-threshold customization, short-cycle delivery and lightweight experimental platforms.

Advanced Manufacturing & Structural Material Solution

All thrust chamber assemblies adopt additive manufacturing (3D printing) to shorten prototype iteration cycles and reduce machining costs. Primary structural shells adopt disposable high-performance modified polymer composite materials, including PPS filled with basalt fiber and PEEK high-strength composite formulations.

Customization & Business Model

We deliver standalone engine units instead of complete launch vehicles by default. Customers may independently develop airframes, navigation and control systems, avionics and warhead integration while adopting our standardized propulsion hardware. We support long-term batch ordering, technical documentation delivery and remote technical consultation.