Heat and Mass Transfer in Rocket Propulsion

Dear Colleagues,

We invite you to contribute your latest advancements in rocket propulsion systems to the upcoming Special Issue, “Heat and Mass Transfer in Rocket Propulsion”. While the title may appear modest, it reflects a fundamental truth: rocket systems are, at their core, thermal devices. Heat and mass transfer are not peripheral—they are the beating heart of propulsion, and among the most critical sources of failure.

This is well understood in combustion-based systems—comprising liquid, solid, hybrid, and monopropellants—where thermal loads and material erosion dictate performance and reliability; however, even electric propulsion systems are not exempt from this. Their continuous operation and absence of liquid propellants complicate thermal management, demanding innovative strategies to dissipate heat and safeguard component integrity.

Heat and mass transfer phenomena permeate nearly every subsystem in rocket propulsion:

1. Combustion Chambers and Nozzles

Flames transfer heat to chamber walls, injector plates, and nozzle throats. Radiative contributions must be quantified through high-fidelity numerical models alongside convection. The nozzle throat is especially vulnerable, particularly in solid rockets employing pintle mechanisms for thrust modulation.

2. Cooling Channels and Cryogenic Handling

In cooling and feed systems, heat absorbed by the coolant induces phase change—from liquid to gas—under subcritical conditions or during cryogenic propellant management. Conversely, in high-performance turbopumps, pressure-induced mass transfer drives heat exchange and bubble formation, with implications for cavitation and system stability.

3. Solid and Hybrid Propellants

Heat and mass transfer near the propellant surface operate in a tightly coupled feedback loop, generating hot gases for thrust from solid materials. In hybrid rockets, mass transfer involves relatively simple pyrolysis; in solid rockets, energetic regression leads to complex flame structures and dynamic heat–mass interactions.

4. Monopropellants

Catalytic compartments decompose cold liquid propellants into hot gases via multiphase mass transfer. The exothermic reaction reheats the catalyst bed, sustaining decomposition. This delicate thermal loop is essential for efficiency and complete gas-phase exhaust.

5. Electric Propulsion Systems

Discharge channels experience intense localized heating from ionization and acceleration, accelerating material erosion and reducing component lifetimes. The power processing unit (PPU) introduces additional thermal load, requiring careful isolation from sensitive spacecraft subsystems and efficient radiation-based heat rejection.

We welcome contributions that explore these phenomena across propulsion architectures—from experimental to modeling innovations and system-level integration. Your work in advancing rocket technology is deeply valued by the editorial team.

Dr. Giuseppe Gallo
Prof. Dr. Harunori Nagata
Dr. Landon Kamps
Guest Editors

Manuscript Submission Information

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