igniter

Nondestructive Inspection Principle and Failure Criteria of the Electric Igniter in Rocket

火箭弹发动机电点火具无损检测原理与失效判据分析

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Determination of burning rate of the bleed propellant and ignition time of the igniter in base bleed projectiles

底部排气弹排气药剂燃速及点火具工作时间的确定

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The jet flows from holes a center-core igniter strongly influence the process of ignition in guns.

中心点火管传火孔射流场直接影响火炮膛内的点火传火过程.

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This paper introduces the development and pressure-time curves of the composition of match head on the chemical igniter.

介绍了化学点火具中点火头药剂的研制及其压力&时间曲线。

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An analysis of the influence of igniter on the properties of the base bleed projectile

底部排气弹点火具特性对底排工作影响的分析

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According to the gas ignition theory, the ignition condition of piezoelectric cock igniter and the reason for difficult ignition of the igniter when using natural gas are analyzed with gas characteristics.

根据燃气点火理论，结合燃气特性，分析了压电式旋塞阀点火器的点火条件及其用于天然气时较难点火的原因。

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To the especially structure and material welding performance of a spaceflight igniter, the key welding problem is the spatter and strike fire phenomenon which is brought by high contact resistance.

前言：针对特殊结构和材料的焊接性能，指出目前的焊接问题主要是存在飞溅和接触电阻过大而带来的“打火”现象；

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A new type of electric igniter is used as an electric element for igniting the propellant charge of the new and special shell series, which suits to operate in electro-magnetic enviroment.

新型电发火件是用于新型特种系列弹发射装药的电发火元件，工作于复杂的电磁场环境中。

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Flame propagation characteries of the low velocity detonation center core igniter

低速爆轰中心传火管的传火特性

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Taking aft-end igniter design for a rocket motor for example, design methods for ignition sequence, amorce quantity estimation and nozzle closure were described respectively.

以某型号发动机尾部点火设计为研究对象，对点火序列设计、点火药量的估算、喷管堵片的设计方法进行了阐述。

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Comparative Analysis of Several Types of Igniter for Rocket Projectile

几种火箭弹点火具的对比研究

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A hybrid rocket motor using this igniter was tested. The experiment results demonstrated that this new igniter can successfully start the N2O/ PMMA hybrid motor.

试验表明，在催化剂被加热到400~600℃左右后，该点火器可以成功启动N2O/有机玻璃（PMMA）混合火箭发动机。

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The experiment indicates that the welder fulfills the welding process requirement of spaceflight igniter and eliminates the spatter and strike fire phenomenon.

将电容储能焊与逆变技术相结合，成功研制了电容储能式逆变点焊机，试验表明该焊机完全满足桥带的焊接工艺要求，并且消除了焊接飞溅和打火现象。

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Firing Test of Inertial Igniter

惯性点火具的发火试验方法

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Main products are: Electoric Igniter for Fireworks display , Electoric ignitors, Fibreglass Mortar Tubes, Indoor & Stage Fireworks etc. series products.

主要产品有: 烟花烯放用电子点火器 、 电子点火头、玻璃钢发射炮筒 、 冷光舞台烟花等.

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Tests show that the digital CDI igniter can improve performance of the motorcycle gasoline engine.

通过试验证实了数字式CDI点火器工作可靠,性能稳定,能不同程度地改善摩托车汽油机的性能.

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Influence of Silica Powder and Lead Tetroxide on the Electric Igniter Property

Si粉、Pb3O4对某电点火具性能的影响

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Application of the Space-Time Conservation Element and Solution Element Method to the Simulation of Two-Phase Flow in Igniter

CE/SE方法在点火管一维两相流数值计算中的应用

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The igniter with multiple slit burner is characterized by its higher combustion efficien-cy, better adjustment of flame length, more rational temperature distribution in the furnace hearth.

多缝式烧嘴点火器具有燃烧效率高、火焰长度易调、炉膛温度分布合理等优点。

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Validation of the Taylor atomization theory and the turbulent jet spread theory for regenerative liquid propellant guns ( RLPG) is analyzed. THE EXPERIMENTAL STUDY OF A TWO STAGE ELECTRICAL IGNITER FOR USE IN REGENERATIVE LIQUID PROPELLANT GUNS

分析了泰勒雾化理论和湍射流扩散理论对于RLPG的适用范围。在观测射流雾化性能的基础上，提出了进一步测定射流雾化规律的方法。RLPG两级电点火具实验研究

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Ignition Condition of Piezoelectric Natural Gas Cock Igniter

压电式天然气旋塞阀点火器的点火条件

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An innovative igniter based on catalytic decomposition of N2O was designed and manufactured. In a typical hybrid, the fuel is a solid and the oxidizer is a liquid.

利用N2O催化分解原理，设计了一个用于启动N2O混合火箭发动机的催化点火器。固液混合火箭发动机是采用液体作为氧化剂，固体作为燃料的一种典型的混合火箭发动机。

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Antistatic Technology Study On An Electric Igniter Which Used A Missile

某导弹用电点火具防静电技术研究

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Ground Ignition Test of an Orbit Maneuver H_2/ O_2 Thruster Based on Gas Dynamic Resonance Igniter

基于气动谐振点火器的氢氧变轨火箭发动机地面点火试验

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Safety Fault Analysis of Igniter Based on FTA and BN

基于FTA与BN技术的某点火具安全失效分析

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Orbit maneuver hydrogen-oxygen thruster based on gas dynamic resonance igniter is a novel chemical propulsion technology especially prospective in space station application.

结合气动谐振点火器进行头部设计的氢氧变轨火箭发动机是一项新颖化学火箭推进技术，尤其适于空间站应用。

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Therefore the high temperature furnace tube is very easy to have the cartridge igniter expiration.

所以高温炉管很容易发生爆管失效。

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This article describes the method of separating a kind of electric igniter with two kinds of different structure sized firing pin by using 3s principle and x-ray photography.

介绍了运用3σ原理和X射线照相的方法，分离装有两种不同结构尺寸撞针的某电点火器。

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The igniter combustion often produces hot condensed particles.

这种点剂燃烧常常产生热的凝结颗粒.

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Instantaneous equilibrium pressure method is used in this paper to analysis the internal ballistics of pyrogen-type igniters. A concept of igniter heat loss coefficient is also presented.

用固体火箭发动机中常用的瞬态平衡压强法对烟火剂式点火器内弹道性能进行了理论预示，并提出热损失系数的概念。

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