Characteristics of Ignition Start-up Process of Underwater Solid Rocket Motor with the Effect of Nozzle Closure

doi:10.12382/bgxb.2022.0136

Abstract

Abstract:

To investigate the flow field and working characteristics of the underwater solid rocket motor at the initial stage of ignition, the gas bubble evolution process under the constraint of nozzle closure separation is numerically simulated. Based on the VOF multiphase model and dynamic mesh technique, a numerical model of underwater gas jet with the effect of nozzle closure is established. The transient evolution of gas bubble morphology and the oscillation characteristics of flow field parameters are analyzed. The characteristics and formation mechanism of initial thrust pulsation after ignition at variable depths are revealed. The results show that: at the initial stage of nozzle opening, the pressure difference drives the closure to strongly impact the liquid phase, causing a high pressure zone in the tail wall space and the formation of an initial thrust peak; as the ignition depth increases, the axial growth rate is slower and the length becomes shorter, the gas bubble has neck contraction in advance, and the pulsation characteristics of the flow field parameters and thrust of the motor become stronger; at the initial stage of ignition in deep water, the shock wave near nozzle exit has reciprocating oscillations, and the pressure oscillation in the tail wall space forms multiple fluctuating thrust peaks. It is demonstrated that the unstable motion of shock waves is the leading factor of thrust pulsation.

Key words: solid rocket motor, underwater ignition, shock wave motion, pressure oscillation, thrust pulsation

WANG Deyou, LI Shipeng, JIN Ge, WANG Ruyao, GUAN Dian, WANG Ningfei. Characteristics of Ignition Start-up Process of Underwater Solid Rocket Motor with the Effect of Nozzle Closure[J]. Acta Armamentarii, 2023, 44(6): 1665-1676.

Figures/Tables 20

Fig.1 Calculation of thrust of underwater solid rocket motor

Fig.2 Computational domain and boundary conditions

Fig.3 Meshing

Fig.4 Mesh independence analysis

Table 1 Simulation conditions

工况	点火深度/m	环境压力/MPa	破盖压力/MPa
1	10	0.2	3.2
2	50	0.6	3.6
3	90	1.0	4.0

Fig.5 High pressure tank experimental system[21]

Table 2 Comparison of numerical and experimental results

Fig.6 Comparison of variation law of jet length

Table 3 Evolution process of gas bubble (above) and contour of Mach number (below) at different ignition depths

Fig.7 Velocity and displacement curves of nozzle closure at different ignition depths

Fig.8 Thrust curves of SRM at different ignition depths

Fig.9 Thrust component curves of SRM at 90m depth

Table 4 Flow field parameters of peak thrust at 90m depth

Fig.10 Locations of pressure monitoring points

Fig.11 Pressure signals of tail wall at the initial stage of ignition

Fig.12 Pressure signals of P0 at 90m depth

Fig.13 Pressure (left) and Mach number (right) distribution at 90m depth

Fig.14 Pressure signals of tail wall at 90m depth

Fig.15 Thrust pulsation characteristics at 90m depth

Fig.16 Axial flow parameters (left) and pressure distribution (right) of flow field at typical times

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