火箭底部喷流辐射加热的数值模拟研究

摘要

The thermal shield design for the base of rocket affects vehicle’s carrying capability directly. An accurate computation of rocket’s plume radiation is a crux of the thermal shield design. On the basis of finite volume method, a numerical computation concept that is used to calculate the thermal radiation of rocket’s plume on its base is proposed. This concept adopts finite volume method to solve the radiation transfer equation of high temperature mix gas, and develops a program applicable to plume radiation computation. To examine the reliability of the program, it has been validated and the results accord with those that were published in public reference. Finally, after a further computation of plume radiation, the change principles of radiation thermal flow density of various gas components are explored. The results indicates the crucial effects of rocket’s plume on base thermal environment. The study can be used as a practical guide for thermal shield design for base of rocket.%火箭底部防热结构设计直接关系其运载的能力，然而，如何准确计算火箭底部喷流辐射是其防热设计过程中的一个难点。提出一个基于有限体积法的火箭羽流对其底部热辐射的数值计算方案。在该方案中，采用有限体积法求解高温混合气体辐射传输方程，编制开发一个适用于计算火箭底部羽流辐射的程序。为了考察计算程序的可靠性，通过验证表明：计算结果与公开发表文献中的结果均符合很好。最后，进一步计算了发动机喷流对火箭底部热辐射，探讨气体成份各自辐射热流密度的变化规律，计算结果说明主要的火箭羽流组份对底部热环境的决定性影响，为火箭底部的防热设计提供依据。