Aluminum in solid rocket propellants is a highly desirable ingredient for many applications. This paper aims to have a deep understanding of the influence of high temperature particles in the plume on motor performance and bubbles of underwater jet. In this paper, a numerical computational model has been developed incorporating the dy namic meshing technique with multiphase Volume of Fluid (VOF) method which simulates the transient motion of a plume particle through the gas-fluid interface. Variation of the particle movement is investigated by varying solid-liquid contact angle, particle diameter and velocity. For values of Bo>8, plume particles move through the gas -fluid interface via the trailing transport configuration. Numerical calculations results which the form and breakup of tailing in conjunction with experiment in the references verifies the validity of this model. With this model, this paper also analyzes the characteristics of a particle in the plume, such as the form of cavity, rebound and velocity oscillations. The results of simulation indicate that critical velocity has the greatest impact on behavior of a particle; particle with different speed break up different regions of bubbles of underwater jet, thus both structure of jet and thrust characteristic of underwater solid rocket motor are affected, the plume particles which has critical speed show different characteristics. Besides, the diameter of plume particle and solid- liquid contact angle have a slight impact on the movement of plume particle.
In order to study the effect of flight altitude on the radiation characteristics of engine lateral jet, based on the simulation results of three-dimensional flow field, radiation transfer equation and molecular spectral line parameter database, we applied the apparent light line of sight method to solve the lateral jet radiation transfer equation and established a procedure to calculate the infrared radiation characteristics of the lateral jet of the attitude control engine; Correct the spectral line intensity of gases at high temperature and pressure. Using the spectral band model to calculate the spectrum absorption coefficients. The infrared radiation characteristics of the lateral jet of the attitude control engine at different flight altitudes are studied, and the distribution of the infrared radiation brightness of the lateral jet in different bands is obtained. The lateral jet spectral irradiance of the attitude control engine decreases with the increase of flight altitude in the low altitude environment, and increases with the increase of flight altitude in the high altitude environment. The results show that the program can simulate the infrared radiation characteristics of the lateral jet of the attitude control engine well and is widely applicable; Different flight altitudes affect the infrared radiation characteristics of the lateral jet of the engine to a certain extent and the flight altitudes at low and high altitudes have different effects on the radiation characteristics of the lateral jet of the attitude control engine.
The infrared radiation signature of exhaust plume from solid propellant rockets has been widely mentioned for its important realistic meaning. The content of aluminum powder in the propellants is a key factor that affects the infrared radiation signature of the plume. The related studies are mostly on the conical nozzles. In this paper, the influence of aluminum on the flow field of plume, temperature distribution, and the infrared radiation characteristics were numerically studied with an object of 3D quadrate nozzle. Firstly, the gas phase flow field and gas-solid multi phase flow filed of the exhaust plume were calculated using CFD method. The result indicates that the Al203 particles have significant effect on the flow field of plume. Secondly, the radiation transfer equation was solved by using a discrete coordinate method. The spectral radiation intensity from 1000-2400 cm-1 was obtained. To study the infrared radiation characteristics of exhaust plume, an exceptional quadrate nozzle was employed and much attention was paid to the influences of Al203 particles in solid propellants. The results could dedicate the design of the divert control motor in such hypervelocity interceptors or missiles, or be of certain meaning to the improvement of ingredients of solid propellants.
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