IO Aircraft - U-TBCC - Unified Turbine Based Combine Cycle
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Graphene | Hypersonics | U-TBCC |  U-GTG | Motors & Rotors | Conforming Tanks | Primary ION Drives (Space)

 

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U-TBCC (Unified Turbine Based Combined Cycle)

 

High Super Sonic - Hypersonics - SSTO

 

 

Propulsion Type

Propriety Turbine and Dual Mode Ramjet/Scramjet

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Fuel

 Hydrogen (Hydro Carbon Free)


Plus Oxygen for outside atmosphere

Operation Range

 0 - Mach 15 in Atmosphere

 

  

 

  

 

  

 

  


Unified Turbine Based Combine Cycle is a propulsion that mates a turbine (jet engine) and a dual mode ramjet/scramjet into a single propulsion platform. Not like conventional TBCC today which are 2 separate platforms mounted separately and use a common inlet, which is what corporate entities like Lockheed are developing or RBCC that China is developing.

Instead, it becomes a singular unit, all in one.

 

U-TBCC uses a modified REST inlet developed by Nasa's HAPB at Langley, which is controlled using an active dynamic shock system, which then transitions into a conical scramjet.  The turbine spins around the dual mode ramjet/scramjet.

Unlike other platforms, such as Reaction Engines Sabre which is limited to Mach 4.5 and is a bypass ramjet, the U-TBCC platform is engineered for 0 through Mach 15 velocities in atmosphere (normalized cruise capabilities at Mach 8-10 safely), and can transition internally to outside atmosphere propulsion, ie rocket mode. In general, Reaction Engines Sabre, is only able to operate at around one half the velocity as U-TBCC is capable of in atmosphere.

 

This propulsion platform is highly scalable, from smaller long range hypersonic missile platforms, through large fixed wing aircraft able to fly at hypersonic velocities and emerging technologies for single stage to orbit capabilities.

 

Since it is meant to become plug and play, and takes up much less airframe space, it become ideal as a standardized propulsion system throughout the aerospace and space sectors.

 

Individual Technologies Involved with U-TBCC

  • Active adaptive dual mode ramjet/scramjet ignition

  • Active inlet, shock redirection (Variable Geometry, in Flight)

  • Lower velocity ignition in ramjet mode with seamless transition to scramjet mode

  • Adaptive isolator and combustion geometry

  • Ability to convert internally to outside atmosphere rocket propulsion

  • Internal starter mechanics (no longer externally mounted)

  • Free floating frictionless turbine assembly

  • Thermal management to beyond 5,000-6,000F

*Note, all technologies internally, engineering, and physics involved with U-TBCC are proprietary and non disclosable.

 

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