Laser Controlled Solid Propellant Micro-thruster

激光控制固体推进剂微型推进器

• 批准号: 17360411
• 负责人: TACHIBANA Takeshi
• 金额: $ 6.55万
• 依托单位: Kyushu Institute of Technology
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (B)
• 财政年份: 2005
• 资助国家: 日本
• 起止时间: 2005 至 2007
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-17360411/
• 关键词: Solid Propellant; Combustion Control; Laser; Thruster; Satellite; 航空宇宙工学; ロケット; 推進薬

The ultimate goal of this study is completion of a small rocket motor for satellites (micro-thruster) having high performance, reliability and wide range of thrust. Our proposing concept towards the purpose is tried by use of solid propellants for high performance, reliability and simplicity coupled with laser for the combustion on/off and thrust level control. In the research work of this time, the fundamentals of combustion control were experimentally ascertained using an originally made strand burner. The results revealed that our proposing concept is feasible: forced combustion of fuel rich HTPB/AP composite propellants by laser have the same tendency in burning behavior as ordinary self-combustible propellant under high pressures and a disposition good for combustion control in reasonably wide range of pressures. Measurements by thermography for the temperature distribution combined with regression rates gave the heat balance near the combustion surface which in turn suggested that most of the heat transferred to the burning surface is provided by chemical reaction of the propellants and laser supplies only supplementary heat flux to compensate for insufficiency. Regarding the concept of an array type rocket, laser ignition of solid propellant (Boron/Potassium nitrate)in vacuum has been realized using 1W laser diode system. This rocket system can provide an impulse of 30 mNs-1Ns using 30 mg-1 g B/KNO propellants. Mixture ratio suitable for the operation of the array type rocket system was experimentally determined to optimize its performance. This rocket system successfully operated after 2-month exposure in vacuum, showing its high reliability that can be used in actual space missions.

这项研究的最终目标是完成具有高性能，可靠性和广泛推力的小型火箭电机（微型刺激性）。我们针对此目的的提议概念是通过使用固体推进剂来进行高性能，可靠性和简单性以及激光器的燃烧和推力水平控制的高性能。在这段时间的研究工作中，使用最初制造的链燃烧器在实验中确定了燃烧控制的基本面。结果表明，我们提出的概念是可行的：激光强迫燃烧富含燃料的HTPB/AP复合推进剂在燃烧行为方面具有与普通的自燃推进剂相同的趋势，在高压下，在相当广泛的压力范围内对燃烧的配置有益。通过热量计学测量温度分布与回归速率相结合，在燃烧表面附近的热量平衡又表明，大多数传递到燃烧表面的热量都是由推进剂和激光供应的化学反应提供的仅补充热通量以补偿不足的。关于阵列类型火箭的概念，使用1W激光二极管系统实现了真空中固体推进剂（硼/硝酸钾）的激光点火。这种火箭系统可以使用30 mg-1 g/knO推进剂提供30 MNS-1NS的冲动。实验确定适合阵列类型火箭系统运行的混合比率以优化其性能。该火箭系统在真空度2个月后成功操作，显示其高可靠性可用于实际空间任务。

项目成果

Ignition Charactehstics of Boron/Potassium Nitrate Using a Diode Laser in Vacuum

真空中使用二极管激光器的硼/硝酸钾的点火特性

• 发表时间: 2007
• 作者: Hiroyuki Koizumi;Masatsu Nakano;Masashi Watanabe;Takayoshi Inoue;Kimiya Komurasaki;Yoshihro Arakawa
• 通讯作者: Yoshihro Arakawa

Laser-assisted combustion of solid propellants

固体推进剂的激光辅助燃烧

• 发表时间: 2007
• 作者: Akira Kakami;Ryoma Hiyamizu;Kiyotaka Shuzennji;Takeshi Tachibana
• 通讯作者: Takeshi Tachibana

Ignition Characteristics of Boron/Potassium Nitrate Using a Diode Laser in Vacuum

真空中使用二极管激光器的硝酸硼/硝酸钾的点火特性

• 发表时间: 2007
• 作者: Hiroyuki;Koizumi;Masakatsu;Nakano;Masashi;Watanabe;Takayoshi;Inoue;Kimiya;Komurasaki;Yoshihiro;Arakawa
• 通讯作者: Arakawa

Ignition Characteristics of Boron/Potassium Nitrate Usinga Diode Laser in Vacuum

真空中使用二极管激光器的硝酸硼/硝酸钾的点火特性

• 发表时间: 2007
• 作者: Hiroyuki Koizumi;Masakatsu Nakano;Masashi Watanabe;Takayoshi Inoue;Kimiya Komurasaki;Yoshihiro Arakawa
• 通讯作者: Yoshihiro Arakawa

レーザにより燃焼制御および可変推力を実現する宇宙用固体推進機の検討

利用激光实现燃烧控制和变推力的空间固体推进器研究

• 期刊: Science Technology of Energetic Materials 掲載決定
• 作者: 各務聡;眞崎信一郎;冷水陵馬;堀澤秀之;橘武史
• 通讯作者: 橘武史