首页>
外国专利>
DEVICE FOR DETERMINING THE PARAMETERS OF FIRE IN THE inhabit pressurized compartment of the spacecraft in orbital flight
DEVICE FOR DETERMINING THE PARAMETERS OF FIRE IN THE inhabit pressurized compartment of the spacecraft in orbital flight
展开▼
机译:用于确定在轨道飞行中航天器的居住加压舱内着火参数的装置
展开▼
页面导航
摘要
著录项
相似文献
摘要
FIELD: fire-prevention facilities.;SUBSTANCE: invention relates to devices for determining the data required for development of fire-fighting systems in habitable pressurised compartments of the spacecrafts (hereinafter - SC) in orbital flight. The device for determining the process parameters of extinguishing fire under the conditions of habitable pressurised compartments of the spacecrafts in orbital flight, is located in the habitable pressurised compartment of the spacecraft and comprises a combustion chamber blown with flow of gaseous atmosphere of the pressurised compartment. In the combustion chamber the test material samples are installed. The combustible flat samples of materials are placed in parallel to each other. The distance between the samples and between the samples and elements of the combustion chamber are set not less than the value determined from the relation: dmin=4,64×(Lmod×νen/Vlim)0,5, where Lmod is the length of the sample in the direction of gas medium flow, cm, νen is the kinematic coefficient of viscosity of the gas medium in the combustion zone, cm2/s; Vlim is the limit speed of the gas medium for combustion of test material, cm/s. The geometric center of the combustion chamber of the device during experiments with this material is placed at a distance from the center of mass of the spacecraft, not exceeding a value determined from the relation: Rmax=0.1·glim/ω2cc.max, where glim is limit acceleration of force of gravity for combustion of the test material, cm2/s, ωcc.max is maximum possible angular velocity of rotation of the spacecraft in normal orbital flight, l/s.;EFFECT: increased efficiency of extinguishing fire.;5 dwg
展开▼
机译:技术领域本发明涉及用于确定在轨道飞行中在航天器(在下文中-SC)的可居住加压舱中开发消防系统所需的数据的装置。用于确定在轨道飞行中的航天器的可居住加压舱的条件下灭火的过程参数的装置,位于航天器的可居住加压舱中,并且包括燃烧室,该燃烧室吹有加压舱的气态气流。在燃烧室内安装测试材料样品。材料的可燃扁平样品彼此平行放置。样本之间以及样本与燃烧室元件之间的距离设置为不小于由以下关系式确定的值:d min Sub> = 4,64×(L mod Sub >×ν en Sub> / V lim Sub>) 0,5 Sup>,其中L mod Sub>是样本中的长度气体介质的流动方向,cm,ν en Sub>是燃烧区内气体介质的运动粘度系数,cm 2 Sup> / s; V lim Sub>是用于燃烧测试材料的气体介质的极限速度,cm / s。在使用这种材料进行实验期间,设备燃烧室的几何中心与航天器的质心相距一定距离,且不得超过由以下关系式确定的值:R max Sub> = 0.1· g lim Sub> /ω 2 Sup> cc.max Sub>,其中g lim Sub>是用于燃烧燃烧的重力极限加速度测试材料cm 2 Sup> / s,ω cc.max Sub>是航天器在正常轨道飞行中的最大可能旋转角速度l / s;效果:增加灭火效率; 5 dwg
展开▼