中止燃烧方法模拟固体推进剂动态点火冲击过程（英文）
发布时间：2024-05-28 20:09
为了研究火箭发动机点火过程中动态冲击对固体推进剂的影响,设计了一个基于中止燃烧的模拟点火冲击装置。该装置由点火螺栓、燃烧室和泄压螺栓组成。金属爆破片安装在泄压螺栓的剪切口处,在点火冲击过程中准确控制泄压压力。模拟点火冲击试验的研究对象是圆环柱体形状的poly(BAMO-THF)/AP/Al固体推进剂试样。p-t曲线表明爆破片的泄压压力与测得的压力一致,其误差在±6%。根据p-t曲线计算增压速率,10 MPa下增压速率达到7000 MPa·s-1,15 MPa下增压速率达到12000 MPa·s-1,这远远大于固体火箭实际点火过程中的增压速率。在模拟点火冲击试验后,推进剂试样端面(受损表面)镶嵌的粒子受损,而内侧表面(未损表面)仍保持完整的状态。点火冲击试验后,推进剂试样的压缩强度增加,而压缩强度开始增加时的形变值降低。这说明在模拟点火冲击试验后,推进剂受损表面会进一步受损,力学性能也会发生改变。
【文章页数】：9 页
【文章目录】：
1 Introduction
2 Experimental
2.1 Simulation Ignition Shock Principles
2.2 Experimental Setup
2.3 Propellant Samples
2.4 Mass of Ignition Material
2.5 Characteristic of Propellant Samples
3 Results and Discussion
3.1 Choice of the Ignition Mode
3.1.1 Weak Ignition
3.1.2 Strong Ignition
3.2 Repeatability Testing of Simulation Ignition Shock
3.3 p-t and dp/dt-t Curves at Different Ignition Pressure
3.4 p-t and dp/dt-t Curves at Different Propellant Temperatures
3.5 Effects on Propellant Micro Morphology by Ignition Shock Process
3.6 Effect of Ignition Pressure and Propellant Temperature on Compressive Strength
4 Conclusions
本文编号：3983667
【文章页数】：9 页
【文章目录】：
1 Introduction
2 Experimental
2.1 Simulation Ignition Shock Principles
2.2 Experimental Setup
2.3 Propellant Samples
2.4 Mass of Ignition Material
2.5 Characteristic of Propellant Samples
3 Results and Discussion
3.1 Choice of the Ignition Mode
3.1.1 Weak Ignition
3.1.2 Strong Ignition
3.2 Repeatability Testing of Simulation Ignition Shock
3.3 p-t and dp/dt-t Curves at Different Ignition Pressure
3.4 p-t and dp/dt-t Curves at Different Propellant Temperatures
3.5 Effects on Propellant Micro Morphology by Ignition Shock Process
3.6 Effect of Ignition Pressure and Propellant Temperature on Compressive Strength
4 Conclusions
本文编号：3983667
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