【作者】 李博；

【导师】 谢侃；

【作者基本信息】 北京理工大学 ， 航天工程， 2015， 硕士

【摘要】 为了提高导弹的机动性和突防能力,作为导弹动力装置的发动机,要求其具备推力控制能力,特别是推力随机控制的功能。推力调节技术是固体火箭发动机的一个重要研究领域。与推力预定的发动机(如单室双推力、脉冲发动机等)相比,前者更能合理地分配推进剂能量。根据工作需要调节其推力,这是未来固体火箭发动机的发展趋势。实现推力的随机控制将意味着固体火箭发动机技术的重大突破。流体喉部矢量喷管是将流体喉部喷管技术与激波诱导矢量技术相结合,从而实现推力大小及方向的实时调节。流体喉部技术是指通过二次流体喷射,使二次流与主流相互作用从而改变主流的喉部形状和流通面积(流体喷射方法)。在喉部附近向主流逆向的喷入二次流体,通过二次流体的挤压和增加流阻使主流流通面积减小,通过调节二次流工质(气体或液体)参数(流量、压强或工作脉宽)从而实现对主流喉道面积大小的控制。激波诱导技术是指在扩张段喷入非对称的二次流,在喷入处产生激波,从而诱导流场发生偏转。本课题的主要研究内容是研究固体火箭发动机流体喉部与激波诱导技术结合后推力矢量的一般规律以及喉部流场的流动特性。通过数值模拟与冷流及热试相结合,研究流体喉部矢量喷管的有效喉部面积与主流、二次流流量比的变化规律;不同喷射方案对推力矢量的影响。喷管内气液两相流的流动特性。验证数值模拟的可靠性,为流体喉部矢量喷管的工程应用提供参考。更多还原

【Abstract】 In order to improve the maneuverability and penetration ability of missile, as the power unit, engine is demand to be provided with the ability of thrust control, especially the thrust stochastic control function. Thrust control technology is one of the important research fields of solid rocket motors. Compared with the reserve thrust engine(eg. single room double thrust and impulse engine etc.), the former is better at allocating propellant energy. According to the work conditions, we need to adjust its thrust, which is the development trend of solid rocket motors. Realizing stochastic control of thrust will be a breakthrough of solid rocket motor technology.Fluidic vector nozzle is the combination of the fluidic nozzle throat and the shock wave induced vector technology, which realize the real-time adjustment of thrust size and direction. The concept of "Fluid nozzle throat" is the interaction between mainstream and secondary flow by injecting secondary flow, which change the shape of throat and the circulation area(fluid injection method). Secondary fluid is reverse injected into the mainstream near the throat, which extrude the mainstream and increase the flow resistance that make the mainstream flow area reduce. Adjusting the secondary flow working substance parameters can realize the control of mainstream throat area size. Shock wave induced technology means injecting asymmetric secondary flow at nozzle divergent section, which make shock wave, induce the mainstream deflectionThe main content of my study is the general rules of the combination of Fluidic nozzle throat technology and shock wave induce technology as well as flow field characteristic of throat. By combining the numerical simulation with cold flow and thermal test, we can gain the relationship between effective throat area in fluidic vectored nozzle throat and flow ratio of the secondary flow and mainstream, as well as the influence of different injection solutions on the thrust vector. At the seam time, we can obtain the flow characteristics of gas-liquid two phase flow in nozzle. By testing and verifying the reliability of numerical simulation, we can provide a reference for the engineering application of fluid vectored nozzle throat.更多还原