Non-aluminum NEPE propellant

40% faster thermal adjustment at high pressure

Exhibits lower burning rate deviation under periodic laser disturbance, providing a more reliable propellant formulation for combustion stability optimization in solid rocket motors.

Kaixuan, Chen · Xue, Xiaochun · Yu, Yonggang

Case Studies in Thermal Engineering 2025

Specifications

Maximum simulation-experiment deviation

{'zh': '5.67', 'en': '5.67'} %

Transient burning rate increase

{'zh': '20–35', 'en': '20–35'} %

Thermal adjustment time reduction

{'zh': '40', 'en': '40'} %

Critical laser power range

{'zh': '50–75', 'en': '50–75'} MW

Advantages

Low simulation-experiment deviation

The model achieves a maximum deviation of only 5.67% from experimental data across 5–12 MPa and 10–75 MW, indicating its accuracy in capturing combustion dynamics.

Faster response at high pressure

At 12 MPa, thermal adjustment time is reduced by 40% compared to lower pressures, enabling faster stabilization under high-pressure conditions.

Identifies critical laser power

A critical laser power range (50–75 MW) significantly prolongs thermal stabilization durations, providing insight into stability under external disturbance.

Applications

• Solid rocket motor propellant：Assess propellant combustion stability under laser disturbance
• High-energy propellant combustion stability：Provide transient burning rate behavior to suppress instability
• Energetic material formulation：Optimize formulation via model prediction, reduce trials