Abstract Numerical simulation based on the discrete phase model and dynamic mesh model can more accurately simulate the working process for hybrid rockets, including the motion and evaporation process of particles and regression process of the fuel grain. The dynamic numerical simulation of combustion and flow in hybrid rocket motors based on a discrete phase model is carried out. Aluminum and aluminum hydride are added to the internal flow field as discrete droplets. Then, a hybrid rocket is designed with 95 % hydrogen peroxide as oxidizer and 38 % aluminum hydride+20 % aluminum+42 % hydroxyl-terminated polybutadiene as the fuel and used to verify the model by firing test. A high degree of agreement between experiment and simulation findings is found. The average deviations for thrust and pressure are 3.6 % and 5.9 %, respectively. It offers the required backing for using the simulation method to investigate the flow and combustion process for the hybrid rockets. The results also demonstrate the transient characteristics of the inner flow field, including the separation and merging of vortexes in the pre-chamber. It is found that a peak of the regression rate appears at the front of the grain and moves backward. This is mainly because the vortex appears here and enhances its heat transfer. Through the discrete phase model, it is worth noting that the aluminum droplet content gradually decreases at the nozzle over time, which is consistent with the firing test. Further research on the impact of aluminum hydride content on the performance of the hybrid rockets has been carried out. The results show that the higher aluminum hydride content can lead to better performance for the hybrid rockets. The thrust, pressure, specific impulse, and characteristic velocity enhance with the increase of aluminum hydride content. An interesting discovery is that the average regression rate is maximum at 48 % aluminum hydride content. This research innovatively couples dynamic mesh and discrete phase models, which can help better understand the working process for hybrid rockets and provide important guidance for the selection of fuel formula.

    Highlights A simulation model of hybrid rocket motors based on a discrete phase model is established. The motion and evaporation of particles and regression of the fuel grain are simulated. A test of hybrid rockets with fuel containing aluminum and aluminum hydride is carried out. A high degree of agreement between experiment and simulation findings is found. The impact of aluminum hydride content on the performance of the hybrid rockets is conducted.


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    Title :

    Study on the dynamic numerical simulation of flow and combustion in hybrid rocket motors based on a discrete phase model


    Contributors:
    Meng, Xiangyu (author) / Gao, Jingfei (author) / Tian, Hui (author) / Niu, Xiaoting (author) / Chen, Ruikai (author) / Cai, Guobiao (author)

    Published in:

    Acta Astronautica ; 215 ; 156-167


    Publication date :

    2023-12-02


    Size :

    12 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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