Combustion Dynamics of Solid Propellants

Combustion dynamics of solid propellants encompass the physical and chemical processes governing the rate and stability of propellant burning within rocket motors and ballistic devices. Solid propellants typically comprise a polymeric binder, oxidiser particles and metallic additives, which decompose and react at elevated temperatures to generate high‐pressure gas. The burning rate is sensitive to chamber pressure, grain geometry and heat transfer to the propellant surface. Transient phenomena such as erosive burning—where high gas‐flow velocities enhance the local burning rate—and tail‐off anomalies during grain depletion pose challenges for performance prediction and safety. Mathematical models couple surface regression and internal ballistic pressure evolution, while real‐time diagnostics such as radiographic imaging elucidate non‐uniform combustion. Advancements in additive manufacturing have enabled complex multi‐material grain designs, demanding refined simulation methods that resolve local burn‐rate heterogeneity. A thorough understanding of these dynamics underpins reliable thrust generation, chamber pressure control and the design of safer, more efficient solid‐propellant systems for space launch and defence applications.

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Combustion Dynamics of Solid Propellants publication trend

The graph below shows the total number of articles in combustion dynamics of solid propellants across all publications each year (not limited to Nature Index journals).

Technical terms

Burn rate: The linear speed at which the propellant surface regresses during combustion, typically expressed in mm/s and dependent on chamber pressure.

Erosive burning: The enhancement of local burning rate due to high tangential gas velocities adjacent to the propellant surface.

Internal ballistics: The study of pressure and thrust development within a combustion chamber from ignition to tail‐off.

Surface regression: The mathematical representation of the inward movement of the propellant burning surface.

Impulse method: A technique to infer propellant burn rate by measuring the thrust impulse generated during combustion in a single test.

References

1. Transient Burning Rate Model for Solid Rocket Motor Internal Ballistic Simulations. International Journal of Aerospace Engineering (2007).
2. Prediction of Tail-Off Pressure Peak Anomaly on Small-Scale Rocket Motors. Aerospace (2023).
3. Burning Rate Enhancement Analysis of End‐Burning Solid Propellant Grains Based on X‐Ray Real‐Time Radiography. International Journal of Aerospace Engineering (2020).
4. Modeling and Simulation of Multi‐Material and Complex‐Shaped Gun Propellant Combustion in Closed Vessels. Propellants Explosives Pyrotechnics (2024).
5. Numerical Investigation on the Effect of Ammonium Perchlorate Content and Position on the Combustion Characteristics of an Ammonium Perchlorate/Hydroxyl-Terminated Polybutadiene Propellant. Aerospace (2023).
6. Using the Impulse Method to Determine High-Pressure Dynamic Burning Rate of Solid Propellants. Aerospace (2023).