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本文以膏体火箭发动机多次启动为应用背景，对膏体推进剂的流变学特性、膏体发动机的点火和熄火机理、膏体发动机的整体结构设计、膏体发动机的多次启动点火试验进行了研究。本文具体研究内容为：首先对膏体推进剂进行了流变学测试，分析其复合粘度与温度、剪切速率之间的曲线关系，得到膏体推进剂具有剪切稀化的特性。对膏体推进剂的储存模量、损耗模量和与角频率的关系曲线进行了分析。得到膏体推进剂在低剪切应力时表现出弹性，随着剪切应力的增大表现出粘性。lf0063
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通过膏体推进剂管道挤出试验装置研究膏体推进剂的管道挤出特性。得到膏体推进剂挤出管道的流速随着质量流率流速的增加而增加。膏体推进剂挤出管道后的下垂程度随管道直径或质量流率的增加而减弱。
其次对膏体火箭发动机的整体结构进行了设计，为了保证发动机的二次启动，着重设计了两套防回火装置。
最后搭建了膏体推进剂挤压及运输点火试验系统。实现了膏体推进剂的二次供给且时间间隔为1s，完成了输入信号电路。
关键词 火箭发动机；膏体推进剂；多次启动；防回火；
Abstract
In this paper, with multi-time start of pasty propellant rocket engine as its applied background, the rheological properties of pasty propellant, ignition and flameout mechanism of pasty propellant engine, the overall design of the engine paste, paste repeatedly start the engine ignition trials research. In this dissertation, the main research contents include:
First paste propellant rheological testing, analysis curve relationship of complex viscosity and temperature, shear rate, intrinsic pasty propellant having a shear thinning. Analysis curve relationship of paste propellant storage modulus, loss modulus and a angular frequency. Get pasty propellant at low shear stress exhibit flexibility, with the increase of shear stress exhibited stickiness.
Study a pasty propellant propellant conduit pipe extrusion characteristics through paste extrusion test device. Get out of pasty propellant flow rate of the pipeline with the increase of mass flow rate of the flow rate increases. After paste propellant were extruded from pipe, the degree of sagging are weakened with pipe diameter or increase the mass flow rate.
Secondly, the overall structure of the paste rocket engine were design, in order to ensure that the second start of the engine, focusing on the design of the two anti-tempering devices.
Finally, we set up a paste propellant extruded and transportation ignition test systems. Achieve a secondary supply of pasty propellant and the time interval is 1s, completed a circuit of the input signal.
Keywords rocket engine; pasty propellant; multiple start; anti-tempering;