We performed laser ignition experiment of green monopropellant for spacecrafts and obtained its ignition characteristics. In conventional monopropellant thruster of a spacecraft, hydrazine is used as propellant and catalytic ignition is employed. However, it is dangerous to handle hydrazine because hydrazine has high toxicity. Furthermore, in catalytic ignition, a catalyst tends to deteriorate by the high temperature and oxidation atmosphere. Recently, the study on green monopropellant is focused by other researchers for improvement of safety, performance and saving cost in operation of a thruster. Moreover, it is expected to apply a microchip-laser to spacecrafts in the future. In this study, we obtained combustion characteristics of green monopropellant in laser ignition and evaluated the feasibility of laser ignition for green monopropellant for spacecrafts.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
スラスタ用低毒1液推進剤を対象にしたレーザー点火特性の研究
AA1730012002.pdf
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