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1. 发明专利

JPS59128955A Rocket engine 失效
标题翻译： ROCKET发动机
公开(公告)号：JPS59128955A
公开(公告)日：1984-07-25
申请号：JP188583
申请日：1983-01-10
申请人： Daicel Chem Ind Ltd
发明人： WATANABE TADAHIKO
IPC分类号： F02K9/10 , F02K9/18 , F02K9/26
CPC分类号： F02K9/26
摘要： PURPOSE:To obtain optimum thrust force X time, by arranging in the axial direction a combustion control member, which is installed partially in the circumferential direction of grains loaded in a rocket chamber and which has a portion closed toward the periphery. CONSTITUTION:A combustion control member 3, which is installed in the circumferential direction of grains 1 loaded in a rocket chamber 4 and which has a portion closed toward the periphery, is arranged in the axial direction. Thereby the web according to the inner-surface combustion system will become a one having substantially a diameter 2-3 times as large as the grains' 1, to cause substantial increase of the combustion progressive web. The combustion pattern thus obtained will transfer from the combustion initial face 1a to the combustion progressive face A one after another, wherein a comparatively large thrust force is obtained in the initial stage, while a comparatively small, approx. constant and stable thrust force is obtained continuously after passage of a certain period of time. This provides effectiveness for launching an aeronautical body in vertical position to a high altitude, as well as the reach can be stretched even in launching aslant.
摘要翻译：目的：为了获得最佳推力X时间，通过沿轴向布置燃烧控制构件，该燃烧控制构件部分地安装在装载在火箭室中的颗粒的圆周方向上，并且具有朝向周边封闭的部分。构成：安装在装载在火箭室4中并且具有朝向周边封闭的部分的颗粒1的圆周方向上的燃烧控制构件3沿轴向布置。因此，根据内表面燃烧系统的纤维网将变成具有基本上直径为颗粒1的2-3倍直径的纤维网，从而引起燃烧进行幅材的显着增加。这样获得的燃烧模式将从燃烧初始面1a一个接一个地转移到燃烧渐进面A，其中在初始阶段获得相当大的推力，而相对较小的约经过一段时间后，连续获得恒定和稳定的推力。这提供了在高空垂直位置发射航空器的有效性，并且即使在发射时也可以伸展。

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