Technical Description
This invention relates to an efficient hybrid rocket engine designed with a bluff body to achieve higher fuel regression rates and stable combustion performance
Problems Addressed
- Low Controllability
- Inefficient Thrust
- Lacks Stability
- Inefficient Combustion
- Lacks Stability
- Inefficient Performance
- Low Regression Rate
Tech Features
- Efficient Regression Rate
- Enhanced Thrust Control
- Better Fuel Utilization
- Efficient Oxidizer Flow
- Enhanced Combustion Stability
- Better Performance Consistency
Target Audience
- Aerospace & Space Exploration Agencies
- Defense & Military Propulsion Systems
- Aviation & Missile Technology Companies
- Satellite Launch Vehicle Developers
- Research & Development
Tech ID: P04-1619 TRL 5 Patent Status: Granted Available For Exclusive and Non-exclusive License
