The Initium I
The INITIUM's fairing houses the payload, protecting it during takeoff. Upon reaching orbit, the fairing will split in half, freeing the payload for deployment.
The satellite housing keeps the payload stable during flight. Upon reaching orbit, it detonates small explosive charges beneath itself, propelling the payload away from the second stage, ensuring no accidental collisions.
The INITIUM's second stage is propelled by a single vacuum optimized Genesis 1 Engine (Gen. 1). Fed from 2 bulkhead tanks containing High Test Peroxide (HTP) and Rocket Propellant 1 (RP-1) Capable of producing 25kN of thrust, guides the payload to its desired orbit.
The interstage connects the launch vehicle's first and second stage, while protecting the vacuum optimized Gen. 1 Engine, and housing the components for stage seperation.
The first stage holds the majority of the INITIUM I's propellants, and houses 9 sea-level optimized Gen. 1 Engines. The Gen. 1 is the primary innovation of the INITIUM I, replacing a traditional pre-burner with a catalyzer, decomposing hydrogen peroxide over a catalyst bed to power the turbopump. This eliminates internal soot buildup and the need for an ignition system, and significantly simplifies plumbing, as the gas generator is a monoprop.
The recovery system consists of a combination of a parachute, in order to vertically align the rocket upon re-entry, 4 solid motors, fired to slow its descent, and landing legs designed to break in case of a hard landing, absorbing significant damage and protecting the INITIUM's internal systems
Genesis 1 Engine
The Gen. 1 Engine uses Hight Test Peroxide as its Oxidizer, and Rocket Propellant 1 as its fuel. The HTP is decomposed over a catalyzer. And the RP-1 is run through regenerative cooling channels throughout the nozzle.
The Catalyzer is a platinum electroplated monolith structure, reducing weight significantly in comparison to pellets, and eliminating the breakage and melting issues associated with potassium permanganate and silver, allowing it to be reused for multiple launches.
Thrust vector control is facilitated through the engine's gimbal, allowing for real-time adjustments both within and without the atmosphere.
Capable of producing 25kN of thrust, the Gen. 1 Engine's Catalyzer system eliminates internal soot buildup, simplifies plumbing, allows for rapid reusability, and negates the requirement of an ignition system.
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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