Abstract During the rocket launch, a flame deflector is mounted under the rocket to improve the thermal environment resulting from exhaust gas impingement on the launch platform. The uplift angle of the deflector should be designed to restrain the recirculation and accumulation of exhaust gas and reduce the thermal loads of the hot backflow on the rocket. According to the hybrid RANS/LES (Reynolds-Averaged Navier-Stokes/Large Eddy Simulation) turbulence model and finite-rate chemical kinetics model, an impingement model was established to investigate the effect of the uplift angle on the thermal environment of the deflector, and the numerical model was validated by a comparison with experimental data. Subsequently, the flow fields of the rocket reaction flow impinging on the deflector at six different uplift angles were calculated. The results indicated that the thermal environment of the deflector was improved to different extents for different uplift angles. When the uplift angle was 6°, the peak temperatures of the symmetry plane and deflector surface were reduced by 5.55% and 9.59%, respectively, compared with those for the deflector without an uplift angle. The air ejector coefficient and gas guiding coefficient of the deflector with an uplift angle of 6° were 3.76 and 0.96, respectively, corresponding to the best guiding performance. The results of this study provide valuable guidance for the design of deflector systems.


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    Titel :

    Effect of uplift angle on thermal environment of flame deflector during rocket launch


    Beteiligte:
    Zhou, Zhitan (Autor:in) / Wang, Limin (Autor:in) / Li, Yiqing (Autor:in) / Feng, Shuaixing (Autor:in) / Ding, Xiangyu (Autor:in)

    Erschienen in:

    Advances in Space Research ; 71 , 10 ; 4127-4141


    Erscheinungsdatum :

    2022-12-15


    Format / Umfang :

    15 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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