固体火箭推进剂

固体火箭推进剂燃烧粒子场的离轴全息研究

Off-axis holographic investigation of particle fields of solid rocket propellant combustion

固体火箭推进剂起爆技术

An experimental research on initiating technique of solid rocket propellant

固体火箭推进剂包覆层激光全息无损检测研究

A study on holographic nondestructive testing of solid rocket propellant coating layers

固体火箭推进剂侵蚀燃烧动态实时测试方法

An Instantaneous Measuring Method of Erosive Burning Rate of Solid Rocket Propellant

密闭燃烧器在固体火箭推进剂燃速测定中的应用研究

Application of closed burner for measuring burning rate of solid rocket propellant

研制生态安全的固体火箭推进剂的可能途径

Possible ways to develop solid propellants for ecological safety

高速动能导弹及超高速导弹用固体火箭推进剂

Solid Propellants Applying for Kinetic or Hyper-velocity Missiles

该文描述了一种固体火箭推进剂侵蚀燃烧的测试方法。

A test method for erosion of the nozzle with adjustable particle mass flow ;

用于固体火箭推进剂的多功能集成虚拟机床技术

Virtual Machine Tool Technology for Solid Rocket Propellant

固体火箭推进剂在振动过程中的能量耗损和热量计算

The calculation of energy dissipation and heat of solid rocket propellant grains subjected to vibration

固体火箭推进剂贮存使用寿命的累积损伤-反应论模型

The Cumulative Damage-reaction Theory Life Model to the Storage and Usage of Solid Rocket Propellant

固体火箭推进剂的侵蚀准则

Erosive Criterion of Solid Propellants

根据固体火箭推进剂的寿命预示方程，对发动机装药寿命进行了预估.用实时全息法配合摄像机研究固体火箭推进剂的燃烧过程

Finally , the prediction equation of solid rocket propellant is given and the service life is estimated . Application of real time holographic method to combustion analysis by using a video camera for recording interferograms

本文采用实时全息法与摄像机相结合的方法来研究固体火箭推进剂的燃烧过程，记录速度为25帧／秒，曝光快门速度最高可达1／2000秒。

By using real time holographic interferometry , the solid rocket propellant combustion process were investigated and recorded by a video camera with a shooting speed of 25 frames per second and the maximum electronic shutter speed of 1 / 2000 second .

通过对常用失效物理模型的分析和总结，提出了固体火箭推进剂贮存使用寿命的累积损伤-反应论模型，并通过算例阐释了这一模型。

By studying and summing up the failure physical models in common use , this paper advanced a cumulative damage-reaction theory life model to the storage and usage of solid rocket propellant , and , by calculating examples , demonstrated this model clearly .

根据固体火箭发动机推进剂药柱的粘弹性特性，得到了药柱线性粘弹性本构方程。

According to the solid rocket motor propellant viscoelasticity , a linear viscoelastic constitutive equation of the grain is obtained .

我国在固体火箭发动机推进剂配制和型腔设计方面处于国际领先水平，但制造固体火箭发动机的设备自动化水平不高，工艺装备落后，研制自主知识产权的自动化装备势在必行。

In the aspects of propellant configuration and cavity design of solid rocket motor , our country is at international leading level . But the equipment automation level of manufacturing solid rocket motor is not high and process equipment is backward .

海防导弹用固体火箭发动机对推进剂的特殊要求

The special requirements on solid propellant for Anti-ship Missile