固体火箭尾舱热环境研究

Study on Thermal Environment of Solid Rocket Tail Compartment

对固体火箭尾舱热环境的组成成分进行了分析,利用理论和数值仿真方法,给出固体火箭沿真实飞行轨道条件下的热环境预示结果,并与地面试验及飞行试验测量结果进行对比。结果表明,固体火箭尾舱热环境存在天地差异,在地面发动机试车状态时,尾舱热环境以喷流辐射热流为主;真实飞行状态时,在发动机喷流和高速来流的相互作用下,火箭尾舱还存在量值更大的对流热流。针对固体火箭尾舱对流热环境提出的线性化热学参数单一介质数值模拟方法可用于固体火箭尾舱热环境设计。

The components of the thermal environment of a solid rocket tail compartment are analyzed in this paper. By means of the theory and numerical simulation,the prediction results of the thermal environment under the real flight trajectory are given. The results are compared with both the ground test and flight data. There are differences of the thermal environment between the condition in the sky and on the ground. In the ground test thermal environment in the tail compartment mainly contains the radiation heat flux,while in real flight,there is extra lager amount of convection heat flux. The simplified method by using a single medium of the linear thermodynamic parameters can guide the design of a solid rocket.