Research On Temperature Field Characteristics Of Exhaust Plume From Solid Rocket Motor

In rockets and missiles,solid rocket motor is widely used as a power equipment.Engine thrust and exhaust plume temperature is an important performance indicator.Research the influence of the ingredients components of propellant,flight conditions of the flight vehicle and operating conditions of the rocket motor on thrust and plume temperature,these could provide reference frame for the engine design,the improvement of ingredients of solid propellants,the development of the technology of target recognition and tracking and stealth.In this paper,we use numerical methods to solid rocket motor with Al₂O₃ particles in gas-solid two-phase flow calculations.In the calculation process,the gas-particle multi phase flow filed of the exhaust plume was calculated based on the Euler-Lagrange method,the finite rate chemistry model and CO/H₂ reaction mechanism were used to simulate the afterburning phenomenon.The discrete particle model was used to tract the motion trajectories of the Al₂O₃ particles in the exhaust plume.Main tasks are as follows:Firstly,in the case of other ingredients the same,by changing the content of aluminum in 100 g propellant,study on the aluminum content of solid propellant rocket engine nozzle flow field parameters and the effect of engine thrust.Research results show that with increasing aluminum content,rocket motor thrust first increases and then decreases the trend;when the propellant when the aluminum content of 17% is likely to be the optimal formula of propellant,engine thrust increased aluminum content for 0%about 8.5%.Secondly,the afterburning,different speeds,altitudes and pressure effects on the characteristic of the exhaust plume temperature field was studied.Research results showed that: the influence of afterburning on temperature field can’t be ignored;the afterburning phenomenon will be inhibited with the increase of the flight velocity and the flight altitude,then the influence of the afterburning on the temperature field will decline;the high temperature regional of area expands with the increase of the operating pressure.The flow temperature field of the exhaust plume of the solid propellants ofdifferent formulations were studied,and the influence of different ingredients on the temperature field was obtained.NC has a fairly small influence for the double base propellant,while NG can increase the temperature of the exhaust plume to some extent.For the modified double base propellant,the temperature of the plume around the axis line will increase with some increment of HMX.Increased content of AP in modified double base propellant,plume temperature near the nozzle exit risen,the exhaust plume temperature decrease;For the composite propellant,the increase of the temperature of the plume is relatively small with the increment of AP,while the enhancement of aluminum powder on the temperature of the plume is comparatively significant.