Accurate prediction of radiative heating during rocket descent poses a fundamental challenge for reusable launch vehicle design. Traditional methods struggle to balance computational cost with physical fidelity, particularly for clustered multi-engine configurations where complex plume interactions create extreme thermal environments. In response to this challenge, LandSpace Technology's research team has developed an innovative numerical framework detailed in the Chinese Journal of Aeronautics on May 22, 2025. The methodology synergistically combines the DTM for radiative path tracking with a newly constructed wide-band k-distribution model based on the HITEMP2010 high-temperature spectroscopic database.
The core innovation lies in establishing an efficient computational pipeline that translates CFD flow-field data into precise radiative heat flux predictions. By implementing pressure correction to account for altitude-dependent molecular density effects and developing automated data-coupling protocols, the team created a robust 3D simulation tool. Validation against high-resolution Statistical Narrow Band benchmarks demonstrated remarkable accuracy with maximum relative errors below 6.0% – all achieved at less than 20% computational cost of conventional line-by-line methods. This breakthrough resolves the longstanding conflict between precision and practicality in reusable launch vehicle thermal analysis.
Applying this method to LandSpace's nine-engine LOX/CH4 rocket revealed critical flight-environment insights. During ascent, base radiative heating peaks at 50 kW/m² at liftoff before diminishing by 80% above 20 km altitude. The return phase exhibits distinct thermal behavior: sidewall heating reaches 29.1 kW/m² at 40 km – 30% higher than concurrent base heating – while three-engine operation generates 186% greater base heat flux than single-engine mode. Most notably, the study quantifies previously undocumented thermal transitions during landing, where sidewall heating attenuates 83% below 4 km and base heat flux plummets to 7.8 kW/m² during final descent.
These findings deliver unprecedented engineering value for reusable rocket development. "Our methodology provides the first systematic quantification of radiative heating distribution across all flight phases," explains corresponding author Dr. Qian Wan. "It offers direct design inputs for optimizing thermal protection materials and informing cryogenic propellant management strategies – particularly crucial for China's new generation of methane-fueled reusable launchers." The framework's adaptability to various vehicle configurations further extends its impact across the aerospace sector.
Looking ahead, the team plans experimental validation using ground test and flight data to enhance model robustness. As reusable launch vehicle technology advances globally, this research establishes a vital computational foundation for mastering the complex thermal environments that define the next frontier of space access.
Original Source
Zhenhua ZHOU, Qian WAN, Lei SHI, Guang ZUO, Yuhong CUI. Numerical approach for radiative-heat-transfer of a reusable liquid-propellant launch vehicle [J] Chinese Journal of Aeronautics, 2025, https://doi.org/10.1016/j.cja.2025.103581.
About Chinese Journal of Aeronautics
Chinese Journal of Aeronautics (CJA) is an open access, peer-reviewed international journal covering all aspects of aerospace engineering, monthly published by Elsevier. The Journal reports the scientific and technological achievements and frontiers in aeronautic engineering and astronautic engineering, in both theory and practice. CJA is indexed in SCI (IF = 5.7, Q1), EI, IAA, AJ, CSA, Scopus.
