Department of Space Flight Systems, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
The Graduate University for Advanced Studies (SOKENDAI)
Department of Space Flight Systems, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
To improve the propulsion performance of third stage solid rocket motor, high-performance solid propellant is required. This propellant is needed to inhibit Al agglomeration on the combustion surface and decrease burning rate. In this study, Mg-Al particles are incorporated into the general solid propellants in order to reduce Al agglomeration since the agglomeration characteristics of Mg-Al are different to Al. However, the burning rate of propellants containing Mg-Al particles is higher than that containing Al. To control the burning rate solid propellants, the catalysts are generally added. In this study, the effects of titanium oxide as a catalyst to burning rate of AP composite propellants are obtained.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
AP系コンポジット推進薬の燃焼速度制御: TiO2添加の効果
AA1530055008.pdf
(754.87KB)
