top of page
Initium I
INITIUM's fairing houses the payload, between 50-250kg, protecting it from the atmosphere during ascent. It separates once the vehicle reaches space, deploying the payload without exposing it to aerodynamic stress during launch. It is designed to be constructed from composite materials, minimizing weight and maximizing structural stability.
The payload adapter mechanically secures the payload to the launch vehicle. Its separation system allows for clean deployment into orbit once the desired altitude and trajectory has been reached.
The avionics bay sits beneath the payload adapter, housing the flight computer, telemetry system, and various navigation and sensory instruments, allowing for real-time in-flight adjustments and constant information relay to ground control.
The upper stage is powered by 1 25kN, vacuum-optimized Genesis 1 Engine, delivering payloads across the final stretch of orbital deployment to SSO or LEO. The stage separator disconnects the upper stage from the lower stage, allowing the latter to return safely to earth to be reused.
The recovery parachute sits below the stage separator, allowing for reusability of the lower stage.
Reinforced intertank structures support loads between oxidizer and fuel tanks.
The propellant tanks store HTP and RP-1 slightly above atmospheric pressure, allowing for both fast deployment, and long-term storability due to the nature of the propellants.
The lower stage is powered by 9 25kN, sea-level-optimized Genesis. 1 Engines, delivering the launch vehicle most of the way to orbit, before returning back to the earth to be safely recovered.
Crumple-zone landing legs ensure that even in the case of a rough landing, the important components remain undamaged.
Genesis 1
Genesis 1 is an RP-1 & HTP fed, reusable rocket engine capable of producing 25kN of thrust, designed to be fitted onto INITIUM I 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.
Prototype Gen. 1 Engine Development Roadmap
Preliminary Experiments
.png)
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
.png)
.png)
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.
.png)
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.
.png)
.png)
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.
bottom of page