This research focuses on electrically ignited solid propellants (ESPs), comparing their properties and combustion characteristics to conventional propellants. The study analyzes how different ESP formulations and electric ignition methods affect key performance parameters like burn rate, thrust, and ignition efficiency( HIPEP)
The investigation has two main application goals:
Micro-propulsion: To evaluate ESPs' fundamental plasma and combustion properties for use in small systems, such as pulse plasma thrusters.
Macro-propulsion: To understand the scalability of ESPs for use in large-scale systems, aiming to improve the overall safety, efficiency, and control of solid rocket technology.
Figure: ASPEN Propellant Ignitions and Combustion Experiment Left to Right
Figure: Preparation Method of Aluminized HIPEP
Plasma Thruster Mode
Figure: LCR Circuit Analysis of Pulsed plasma thrusters at peak voltage of 2 KV
Figure: Ablation mass study (M) VS Pulse Duration at different current levels
Figure: Ablation Mass Study VS Arc Energy
Figure: Ablation Mass VS Pulse Duration at different Voltages
Figure: Final Diameter VS Ablated Mass
Figure: Electron Density VS Pulse Duration
Figure: Electron Temperature VS Pulse Duration
Figure: Electron Temperature VS Peak Voltage at different bias Voltages
Figure: Exhaust Velocity VS Chamber Temperature
Figure: Force VS current from plasma generation
Plasma Assisted Combustion Mode
Figure: Ohmic Heating VS Electric Field Strength
Figure: Flame Velocity vs Electric Field Strength
Figure: Burn Rate VS Electric Field Strength
Figure: Thrust VS Electric Field Strength