Full-scale hydrolox space launch vehicles impose prohibitive upfront R&D costs, extreme orbital velocity requirements, and extended capital amortization cycles. Direct commercial development of an all-hydrolox reusable launcher without auxiliary solid boosters creates high technological risk.
By restructuring development into a phased, sub-system level dual-use roadmap, core hydrolox technologies achieve rapid deployment, operational validation, and economic returns through tactical defense and point-to-point logistics before scaled integration into orbital launch architectures.
Phase I: Tactical Missile Risk Reduction & Subsystem Validation
Instead of demanding full orbital insertion on initial tests, core hydrolox components are validated on long-range cruise missile and strike platforms where range performance scales continuously rather than binary mission success.
Core Subsystems: Initial iteration focuses on compact HTS trans-wall valve arrays, superconducting electric turbopumps, compact high-efficiency fuel cells, and non-venting nested tank structures.
Operational Advantages: Lower system mass, rapid iteration cycles, and minimal infrastructure overhead. Systems take off vertically or horizontally without solid rocket boosters, heavy ramps, or complex launch pads.
Logistics & ISRU Integration: Sub-scale hydrolox operations integrate directly with naval nuclear architecture, using onboard seawater electrolysis and cryogenic liquefaction for underway replenishment. This establishes operational doctrine for automated ISRU interfaces later deployed to extraterrestrial surface pads.
Phase II: Dual-Use Hydrolox VTOL Platforms
Adapting the self-contained vertical launch dynamic of Phase I enables direct transition into VTOL Unmanned Aerial Vehicles utilizing a high-stability trimaran structural configuration.
Civil & Tactical Utility: Early-generation trimaran VTOLs handle high-payload surveillance, emergency response, and heavy logistical distribution to remote or infrastructure-deprived regions.
Architectural Overlap: Propulsion manifolding, fluidic control, and nested tank geometry remain common with Phase I strike systems, lowering cross-platform production costs.
Phase III: Scaled Reusable Launch & Commercial Aviation
With turbomachinery, cryo-valves, and automated fueling routines validated across high-volume operational cycles, integration scales to full-size orbital systems and commercial aviation.
Orbital Launch Architecture: Eliminates solid rocket boosters to achieve competitive payload-to-LEO fractions through high specific impulse hydrolox efficiency.
Advanced Aeroshell Engineering: The nested tank system transitions from atmospheric single-use structures to high-temperature entry-capable assemblies utilizing open-cell metallic foam and structural thermal insulation.
Commercial Heavy Aviation: Scaled manufacturing routines matured during spaceframe production directly seed high-capacity cargo and human-rated long-range commercial VTOL aircraft.
Implementation Summary
----- Original Article by İbrahim
I would like to aggregate my ideas on hydrolox systems. Hydrolox rocketry is not something startups can excel at. However, it has broader advantages for a country that utilizes this capability. The ultimate hydrolox rocket design I had proposed required many new technologies to be developed. Coupled with the rocket's demand to deploy a competitive payload to LEO without using solid boosters, it is a challenging task that would take a long time and require a considerable R&D budget with long-term return.
I propose a more feasible unified strategy that yields many returns much sooner. The key parts of my hydrolox design are the superconducting valves and pump systems, high-efficiency compact fuel cells, and the nested propellant tank architecture. All of these can be developed and tested on a missile. Unlike space rockets, missiles—especially cruise missiles—do not have extreme requirements. A rocket that cannot reach orbital speed has no use, while the range of a missile is far more flexible. Due to the compact size and flexible requirements of a missile, iterations can be made rapidly with much less cost. In the meantime, ISRU hydrolox production capability can be developed. It would allow missiles to be fueled by a nuclear navy. Later, that capability will allow a Mars shuttle to refuel itself using an ISRU-capable launch pad.
As the missile system is developed, a VTOL UAV design can be made. Since the missile also has the capability of taking off by itself without requiring a solid booster or large ramps, that feature enables VTOL UAV development as well. For the hydrolox VTOL, I had proposed a trimaran architecture. The early models can be designed for surveillance and small cargo deployment in rural areas, giving the system civil utility while overlapping considerably with the missile design.
As the critical features of my idea are developed and perfected, a space rocket design can be accelerated. While the core propulsion part of the rocket is being developed by military and civilian VTOL projects, the nested foamed tank architecture I proposed for the rocket (as well as for the VTOL and missile) can be developed to withstand atmospheric entry (which is not required for the missile and VTOL). Additionally, the capability to manufacture this design on a large scale can be developed. This capability is also important for larger VTOL designs, which can extend to commercial high-capacity cargo and human-capable aircraft.
As a result, my idea can be developed in small pieces with quick returns and broad impact.
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