Numerical simulation of combustion surface regression based on Butterworth filter in hybrid rocket motor

Meng, Xiangyu; Tian, Hui; Chen, Xinglun; Jiang, Xianzhu; Wang, Pengfei; Wei, Tianfang; Cai, Guobiao

doi:10.1016/j.actaastro.2022.11.003

Cited by 14 publications

(5 citation statements)

References 22 publications

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“…Based on the aforementioned content, the current long-duration dynamic numerical simulation of hybrid rocket motors is constrained by severe deforming of the combustion surface mesh and the absence of consideration for nozzle erosion. In this paper, the issue of severe mesh deformation during the long-duration simulation process by employing the burning surface mesh optimization technique introduced in our previous work [9]. The simulation is based on the Φ336 mm hybrid rocket motor, capable of continuous operation for 200 s with a maximum thrust of 3 kN.…”

Section: Transient Simulation Modelsmentioning

confidence: 99%

“…The results indicate a positive correlation between the regression and oxidizer mass flow rates. In our earlier research, we created a 2D simulation model using dynamic mesh technology and integrated the Butterworth filter, which was utilized to smooth the interface and prevent severe grid deformation [9,10]. The simulation duration reached 40 s. Concurrently, these motors face severe nozzle erosion during prolonged operation, with nozzle erosion displaying characteristics of prolonged nonlinearity and spatial non-uniformity [11,12].…”

Section: Introductionmentioning

confidence: 99%

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Long-Duration Dynamic Numerical Simulation of Combustion and Flow in Hybrid Rocket Motors Considering Nozzle Erosion

Meng,

Tian,

Niu

et al. 2024

Aerospace

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Hybrid rocket motors have great development potential due to their outstanding thrust adjustment flexibility and long-term operation ability. However, nozzle erosion during the motor operation can cause an increase in the throat area of the nozzle, which leads to a decrease in combustion chamber pressure and nozzle efficiency. Therefore, a performance prediction model for hybrid rocket motors considering nozzle erosion has become a key technology that must be addressed when developing hybrid rocket motors. This study uses dynamic grid technology to simulate the regression of the combustion surface and nozzle erosion, which fits well with experimental values. The behavior of high-energy particles in the combustion chamber is simulated through a discrete phase model. Notably, distinctive behavior is observed in Al and Mg droplets, with Al droplets exhibiting incomplete vaporization in the combustion chamber while Mg droplets completely vaporize. A ground firing test using the Φ336 mm hybrid rocket motor lasting 200 s is conducted. The results show that the dynamic numerical simulation, accounting for nozzle erosion, substantially enhances performance prediction accuracy. The average deviation in motor thrust remains below 1.8%, and the combustion chamber pressure deviation stays under 2.6%, confirming the precision of the model. Ultimately, both simulation and experimental outcomes indicate a gradual decrease in specific impulse and characteristic velocity over the long-term operation, attributed to the gradual deviation of the oxygen-fuel ratio. This research provides valuable insights for guiding hybrid rocket motor design and optimizing design parameters to improve overall performance. This model can achieve long-duration and high-precision performance predictions for hybrid rocket motors.

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Section: Transient Simulation Modelsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Long-Duration Dynamic Numerical Simulation of Combustion and Flow in Hybrid Rocket Motors Considering Nozzle Erosion

Meng,

Tian,

Niu

et al. 2024

Aerospace

Self Cite

View full text Add to dashboard Cite

show abstract

“…Finally, it can be argued whether Reynolds-averaged Navier-Stokes approaches (as in the majority of HRE simulations) are ideally suited for the complex wall blowing and pyrolysing phenomena at the fuel surface. Nevertheless, numerical simulations of HREs are improving significantly, be it in the modelling of hydrodynamic instabilities [149,150], swirl injection [138,[152][153][154], shape changing simulations [153][154][155][156][157] (see Figures 7 and 8), complex geometries such as helices [158][159][160], rotated grains [144,161], throttling [72,162], or nozzle erosion [94,163]. Simplified geometries and simulations carried out on the average fuel port diameter are considerably less computationally costly compared to multiple instances of the fuel port progression, with both providing satisfactory representations of the HRE flow field and local regression rates [157,164].…”

Section: Numerical Simulationsmentioning

confidence: 99%

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Glaser,

Hijlkema,

Anthoine

2023

Aerospace

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Hybrid rocket propulsion, first demonstrated by the Russian GIRD-09 rocket in 1933, combines liquid oxidizer and solid fuel for thrust generation. Despite numerous advantages, such as enhanced safety, controllability, and potential environmental benefits, hybrid propulsion has yet to achieve its full potential in space applications. In recent years, the research on hybrid propulsion has gained enormous momentum in both academia and industry. Recent accomplishments such as the altitude record for student rockets (64 km), the launch of the first electric pump-fed hybrid rocket, and a successful 25 s hovering test highlight the potential of hybrid rockets. However, although the hybrid community is growing constantly, industrial utilizations and in-space validations do not yet exist. In this work, we reassess the possibilities of hybrid rocket engines by presenting potential fields of applications from the literature. Most importantly, we identify the technical challenges that hinder the breakthrough of hybrid propulsion in the space sector and evaluate the technologies and approaches necessary to bridge the gaps in hybrid rocket development.

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“…Verification of the method was performed by firing an eco-friendly, non-toxic, and high-performance combination of 98% H 2 O 2 and HTPB. Meng et al's most recent publication [146] focuses on simulating combustion surface regression through a numerical model powered by a Butterworth filter. The validation was performed through a firing test based on 98% HTP and HTPB.…”

Section: Hydrogen Peroxidementioning

confidence: 99%

Test Activities on Hybrid Rocket Engines: Combustion Analyses and Green Storable Oxidizers—A Short Review

2023

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Hybrid rocket engines (HREs) offer a low-cost, reliable, and environmentally friendly solution for both launch and in-space applications. Hybrid propellants have been identified as green thanks to their use of non-toxic, non-carcinogenic oxidizers. Of particular relevance are storable oxidizers, namely high-concentration (≥90 wt.%) hydrogen peroxide (HP, H2O2) and nitrous oxide (N2O). This work provides a survey of experimental activities based on H2O2 and N2O for hybrid rocket propulsion applications. Open literature data are completed with original thermochemical calculations to support the discussion.

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Numerical simulation of combustion surface regression based on Butterworth filter in hybrid rocket motor

Cited by 14 publications

References 22 publications

Long-Duration Dynamic Numerical Simulation of Combustion and Flow in Hybrid Rocket Motors Considering Nozzle Erosion

Long-Duration Dynamic Numerical Simulation of Combustion and Flow in Hybrid Rocket Motors Considering Nozzle Erosion

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Test Activities on Hybrid Rocket Engines: Combustion Analyses and Green Storable Oxidizers—A Short Review

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