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首页> 外国专利> METHOD OF ALTITUDE TESTS OF LARGE-SIZE SOLID PROPELLANT ROCKET ENGINE AND PLANT FOR ITS REALISATION

METHOD OF ALTITUDE TESTS OF LARGE-SIZE SOLID PROPELLANT ROCKET ENGINE AND PLANT FOR ITS REALISATION

机译：大型固体火箭发动机和工厂的高空试验方法及其实现

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FIELD: engines and pumps.;SUBSTANCE: during altitude tests of a rocket engine, underpressure is pulled by preliminary vacuumising of the space around the engine, ejecting properties of a combustion products jet in a diffuser and injection of additional gas into an exhaust manifold. The diffuser start-up is provided to the moment until a reflected wave of combustion products compression reaches it. In case of pressure drop in the rocket engine, the additional gas is injected into the exhaust manifold, directly downstream the diffuser, providing for variation of its flow in inverse ratio to variation of the combustion products consumption. Then consumption of injected gas is gradually reduced to zero. Gas for injection is compressed air of high pressure. A plant for altitude tests comprises a pressure chamber for placement of rocket engine in it with a pressure sensor in a combustion chamber, a system of preliminary air pumping, an exhaust manifold with a diffuser, a system of gas injection with a source of gas and manifolds for its supply to the injecting facility and a flap plug. In the exhaust manifold at the outlet from the diffuser a header of larger diameter is installed with length of 125-150 m. The zone of diffuser and header contact is equipped with a chamber separating it from the environment. The injecting facility is arranged between the diffuser and the header and is made in the form of nozzles or in the form of a circular injector, the function of which is performed by a through gap between the diffuser and the header, or in the form of perforation of a closed gap between the diffuser and the header. The source of injected gas represents cylinders with compressed gas, and flow rate controllers are mounted on manifolds of compressed air supply to the injecting facility. Drives of flow rate controllers are connected by electric circuits serially with a setter of compressed air flow, a pressure alarm, a signal delay relay and a pressure sensor in a combustion chamber of a rocket engine.;EFFECT: inventions make it possible to provide for reliable preservation of integrity of thin-walled nozzles for the entire time of rocket engine operation, with simplification of a testing plant.;2 cl, 4 dwg
机译：领域：发动机和泵;物质：在火箭发动机的高度测试期间，通过对发动机周围的空间进行初步抽真空，将燃料喷射到扩散器中的燃烧产物喷射特性以及将其他气体喷射到排气歧管中来拉低压力。扩散器启动一直持续到燃烧产物压缩的反射波到达该时刻为止。在火箭发动机的压力下降的情况下，将额外的气体直接喷入扩散器下游的排气歧管，以使其流量与燃烧产物消耗的变化成反比。然后，注入气体的消耗逐渐减少到零。注入气体是高压压缩空气。用于海拔高度测试的设备包括：压力室，用于在燃烧室中放置带有压力传感器的火箭发动机;预备空气泵送系统;带扩散器的排气歧管;带气源的气体喷射系统;以及用于将其供应到注射设备的歧管和一个阀瓣塞。在扩散器出口处的排气歧管中，安装了直径较大的集管，其长度为125-150 m。扩散器和集流管接触区配有一个将其与环境隔开的腔室。注入装置布置在扩散器和集管之间，并且以喷嘴的形式或圆形注入器的形式制成，其功能由扩散器和集管之间的贯通间隙执行，或者以扩散器和集管之间的闭合间隙穿孔。注入气体的来源代表装有压缩气体的气瓶，流量控制器安装在向注入设备供应的压缩空气的歧管上。流量控制器的驱动器通过电路与火箭发动机燃烧室中的压缩空气流量，压力报警器，信号延迟继电器和压力传感器串行连接。效果：发明可以提供在整个火箭发动机运行期间可靠地保持薄壁喷嘴的完整性，并简化了测试设备。; 2 cl，4 dwg

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