圆孔装药固体火箭发动机的慢速烤燃特性研究

目的 研究圆孔装药固体火箭发动机的慢速烤燃特性.方法 针对装填高能推进剂的固体火箭发动机,建立了二维瞬态慢速烤燃模型.其中AP/HTPB推进剂的化学动力学模型为两步总包反应模型.在升温速率分别为3.6、7.2、10.8 K/h的工况下,进行固体火箭发动机的烤燃数值模拟,并具体分析慢速烤燃工况下固体火箭发动机的传热特性和...

Slow Cook-Off Characteristics of Solid Rocket Motor with Round-hole Charge

In order to research on slow Cook-off Characteristics of Solid Rocket Motor with Round-hole Charge. The thermal safety of solid rocket motor has attracted more and more attention with the high energy of propellant. In this paper, a two-dimensional transient slow cook-off model is established for solid rocket motor filled with high energy propellant. The chemical kinetic model of AP/HTPB propellant is a two-step overall reaction model. Under the working conditions of heating rate of 3.6, 7.2 and 10.8 K/h respectively, the numerical simulation of solid rocket motor is carried out, and the heat transfer characteristics and ignition characteristics of solid rocket motor under slow cook-off working conditions are analyzed in detail. The ignition response times corresponding to the three slow cook-off conditions are 30.96, 22.19 and 18.70 h respectively, and the ignition temperatures are 518.84, 518.85 and 519.59 K respectively. With the increase of the slow heating rate, the ignition center of cook-off moves to the outer wall and the right end face of the propellant, and the ignition region changes from an ellipse to a semi-ellipse. The numerical results of cook-off show that in the slow cook-off process of solid rocket motor with round-hole charge, the external heat conduction dominates the temperature change of propellant in the early stage, and the self-heating reaction of propellant dominates in the later stage.