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对火箭密集度产生极大影响的火箭燃气喷射流,其理论和计算至今仍不完善。本文拟就这一问题作一尝试。 本文第一部分论述火箭燃气喷射流的若干机理。这里在火箭燃气喷射流流动结构内增加了羽状流转移段,并作出转向模型和火箭燃气喷射流边界层混合区的诸普遍相似剖面。 在第二部分中,利用一元稳定等熵流理论得到羽状流转移段诸参数,应用非等温湍流射流理论且通过射流积分第一和第二方程问题,并考虑火箭发动机喷射流燃烧的影响,确定与温度比有关的结构参数和特性参数。 最后,利用电子计算机模拟发射两种火箭系统,获得较满意的结果。
The rocket gas jet, which has a great influence on the rocket intensity, has not yet been fully developed in theory and calculation. This article intends to make an attempt on this issue. The first part of this paper discusses several mechanisms of rocket gas jet. A plume-like stream transfer section was added here to the rocket gas jet flow structure and commonly-similar sections of the steering model and the mixed zone of the rocket gas jet boundary layer were made. In the second part, using the theory of univariate steady isentropic flow theory, the parameters of the plume-like flow transfer section are obtained. By applying the theory of non-isothermal turbulent jet and integrating the first and second equations of jet flow, and considering the influence of jet combustion of the rocket engine, Determine the temperature and structure-related parameters and characteristics of the parameters. Finally, two kinds of rocket systems were simulated by computer simulation to obtain more satisfactory results.