Rocket Engine Plants TRIZ Cases
- Room-Temperature Cured Polysiloxane Flexible Stops for Thrusters
Ambient curing of liquid polysiloxane eliminates energy-intensive heating while maintaining mechanical strength across a wide temperature range.
- Missile Thrust Vectoring via Segmented Flow Deflectors
Three segmented flow deflectors steer jet exhaust to manage pitch, roll, and yaw without complex aerodynamic surfaces.
- Nitro-Substituted MOF Fuels for High Energy Density Propulsion
Nitro-substituted metal-organic frameworks resolve energy density versus chemical stability trade-offs in rocket propulsion systems.
- Single-Expansion Ramp Nozzle Propulsion Assembly
Rocket engines accelerate air to supersonic speeds within a channel feeding a single-expansion ramp nozzle.
- Cryogenic Rocket Engine Radiative Heat Recovery
A heating device captures thermal radiation from a rocket nozzle to heat an inert fluid circulating through external conduits.
- Hybrid Chemical-Electrothermal Thruster for High-Thrust and High-Specific-Impulse Maneuvers
Electromagnetic heating of chemical reaction products in a single cavity merges high thrust with high specific impulse, reducing spacecraft mass and complexity.
- Exhaust Nozzle Transitioning Circular Inlet to Rectangular Exit
A three-dimensional exhaust nozzle transitions a circular inlet to a rectangular exit using curved surface geometry and tessellated panels.
- Passive Gas Ejection Modulation for Nozzle Thrust Optimization
A passive modulation device adjusts the gas ejection section using pressure-driven pistons to optimize thrust across varying flow regimes.