Browse Topic: Combustion and combustion processes
This paper addresses non-sustained ignition in numerical simulations of hydrogen/air turbulent diffusion flames. A reproducible LES-PaSR case study was constructed on the OpenFOAM platform, and a box-shaped ignition core was applied using setFields. The work is positioned as a numerical diagnostic and benchmark workflow, not as an experimentally validated prediction of a stable flame. The evidence chain, consisting of three diagnostic indicators - the domain-wide maximum temperature, centerline statistics along the ignition axis, and slices at critical moments - tracks the complete ignition-peak decay process. Calculations show that the domain-wide maximum temperature (Tmax) reaches a peak of 2852.5 K at t = 3.13×10^–4 s and then rapidly drops to 956.4 K at t = 0.0015 s. The duration of Tmax ≥ 2000 K is 0.818 ms, while Tmax ≥ 1000 K lasts for 1.388 ms. Comparison between the centerline and cross-sections further indicates that the high-temperature OH reaction zone is mainly limited to the ignition core and its downstream neighboring region. Under the combined effects of convective transport and turbulent mixing, this region rapidly cools and dissipates, failing to form a stable self-sustained exothermic structure. Finally, three physically plausible explanatory pathways and corresponding sensitivity-case designs are proposed, providing a practical basis for subsequent parameter scanning, mechanism replacement, and future comparison with experimental or literature-reported data. A supplementary sensitivity case with the ignition-kernel temperature increased from 2200 K to 2400 K exhibits a higher peak temperature and delayed threshold crossings, yet the reacting structure remains non-sustained within the simulated time window. Tmax ≥ 2000KTmax ≥ 1000K
To solve a problem that ignition anomaly can’t be detected in time, based on the thermal equilibrium equation, the space heat flow, heater heating, propellant combustion, and thermal radiation to cryogenic space are considered to build an accurate ignition temperature method for the 10 N thruster by using on-orbit true temperature. Further, considering the error of measuring the thermistor, an envelope model for the 10 N thruster ignition temperature is established. Based on the above, a detection method for the 10 N thruster ignition anomaly of on-orbit satellites is proposed. The accuracy of the method is relatively high, and the absolute error is less than 3 degrees Celsius. An anomaly can be quickly detected when the 10N thruster ignition temperature deviates from the normal trend by 3–5 degrees celsius. The method is applied to a DFH-3 satellite, and the maximum difference of 10 N thruster ignition temperature between the theoretical values calculated by the proposed method and the measured values is only 2.72 degrees celsius. It has been proven that the prediction accuracy of the proposed method is high. It plays an important role in discovering the 10N thruster ignition anomaly in time and ensuring the success of satellite orbit or attitude control.
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