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Genesis 1
Genesis 1 is an RP-1 & HTP fed, reusable rocket engine capable of producing 25kN of thrust, designed to be fitted onto any micro-satellite launch vehicle, for delivery to Low Earth Orbit (LEO) and Sun Synchronous Orbit (SSO).
By replacing a traditional gas generator with a Hydrogen Peroxide Catalyzer, Genesis is able to significantly decrease internal heat stresses, allowing components to be made smaller and lighter.
The lack of internal combustion within Genesis' gas generator eliminates internal soot buildup, significantly improving maintenance cost and time between launches, with very few components needing to be replaced or processed between individual launches.
The high decomposition temperature of Hydrogen Peroxide causes hypergolicity between the propellants, removing the need for an ignition system, and the monoprop gas generator further simplifies plumbing, allowing for a simple, compact, and reliable system.
Genesis Micro
Genesis Micro is a versatile in-space propulsion unit. Using HTP & RP-1, and capable of producing 5kN of thrust, it is designed for satellite manoeuvring, orbital transfers, and deep-space missions.
Genesis Micro is easily restartable and utilizes storable propellants, allowing it to remain dormant in space for extended periods of time. Its turbomachinery, cooling systems, and combustion chamber are engineered to withstand multiple ignition cycles.
Similarly to Genesis 1, Genesis Micro relies on HTP decomposition to drive the turbopump system, reducing part count and improving reliability.
The use of RP-1 and HTP simplifies logistics, storage, and integration compared to cryogenic systems, affording operators greater mission flexibility, particularly when long-duration orbital operations or delayed launches are required.
Prototype Gen. 1 Engine Development Roadmap
Preliminary Experiments
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Initial Design & CFD
Iterative Optimization & Refinement
Investigation into the decomposition of HTP, the V2 Missile, and the catalyzer system's potential.
Initial CAD models and simulations for a functional system.
Routine improvement of the existing system based on CFD results, and optimizing components to be test-ready.
Catalyzer Test
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Injector Cold FLow Test
Peroxide Compatibility Validation
Validation of the catalyzer's performance in comparison to the multiphysics model.
Validation of injector performance, and collection of empirical data to use in further system optimization.
Subsystem components are submerged in HTP to ensure no defects or incompatible materials are present.
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Hydrostatic Pressure Tests
Stress tests for all components in a simulated environment.
Pneumatic Pressure Tests
Further stress tests and leak detection for all components in real-world conditions.
Impeller Tests
Validation of generated flow rates and pressures given the desired torque.
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Full Turbopump Test
Validation of the turbopump's performance under real-world conditions
Assembly & Full System Cold FLow Test
Preliminary test before the hot engine test, ensuring everything functions as expected.
Hot Engine Test
The final step before flight-readiness.
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