Study on Asymmetric Outflow Stability of Liquid Rocket Feeding System
In order to reduce the amount of asymmetric propellant flow out of the heavy launch vehi-cle,the research was carried out on collapse of the remaining propellant.The theoretical analysis model of the flow field of the outlet and cover plate structure was established,and the flow field sim-ulation analysis was carried out.The residual propellant with different flow structures was obtained,with symmetric structure propellant remaining at 1.341 m3 and asymmetric structure propellant re-maining at approximately 1.712 m3.The results showed that the scheme of circular cover plate could significantly reduce the residual liquid.Compared with the symmetrical configuration,the amount of liquid remaining in the asymmetric outlet configuration increased significantly,and the propellant entrapment appeared earlier in the densely arranged position.During asymmetric arrangement,suffi-cient flow area could reduce local flow velocity and delay air entrainment time.
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