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首页> 外文会议>Recent Advances in Space Technologies, 2005. RAST 2005. Proceedings of 2nd International Conference on >Ground testing of a liquid fueled rocket motor
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Ground testing of a liquid fueled rocket motor

机译：液体燃料火箭发动机的地面测试

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In a research project carried by TUBITAK-SAGE, Turkey's first operational liquid fuelled rocket motor has been designed, manufactured and tested. The rocket motor uses hydrogen peroxide as oxidizer and hydrocarbon based chemical as fuel. Also some metal salts are added into the fuel in order to attain hypergolic ignition. The fuel and oxidizer are fed into the system by using high pressure nitrogen gas. The control of pressurized fuel and oxidizer into the motor combustion chamber is achieved by using pressure operated valves and a control card. Mass flow rates of oxidizer and fuel are controlled by using cavitating venturis. In order to improve the combustion performance, an unlike triple impinging type injector is used to spray the fuel and injector into the combustion chamber. Before the testing of the liquid propellant rocket motor (LPRM) system, some simplified tests were performed on subsystems. These tests include flow rate check tests, hypergolic ignition tests and flow tinting tests. This paper contains the detailed explanation of the liquid propellant rocket motor system that has been ground tested, and the results of the tests performed. The ground tests were performed at the static test ramp, at TUBITAK-SAGE, Ankara. In the first motor test no data is taken and the general characteristic of the rocket motor is observed by using normal speed and high-speed cameras. In later tests two pressure transducers is mounted on the rocket liquid propellant rocket motor (LPRM) System. The first transducer is mounted to the rocket motor body to measure the combustion chamber pressure and the second one is mounted at the exit of the cavitating venturi. The rocket motor aluminum case is instrumented with three strain gages and two temperature sensors. A third temperature sensor is also placed at the nozzle exit to measure the nozzle exit gas temperature.
机译：在TUBITAK-SAGE进行的一项研究项目中，土耳其设计，制造和测试了土耳其第一台可运行的液体燃料火箭发动机。火箭发动机使用过氧化氢作为氧化剂，并使用基于碳氢化合物的化学物质作为燃料。此外，一些金属盐也被添加到燃料中以获得高点燃性。通过使用高压氮气将燃料和氧化剂供入系统中。通过使用压力操作阀和控制卡，可以控制进入发动机燃烧室的加压燃料和氧化剂。通过使用空化文丘里管来控制氧化剂和燃料的质量流率。为了改善燃烧性能，使用了与以往不同的三冲击式喷射器将燃料和喷射器喷射到燃烧室中。在测试液体推进剂火箭发动机（LPRM）系统之前，对子系统进行了一些简化的测试。这些测试包括流量检查测试，超高亮点火测试和流动着色测试。本文包含对已经过地面测试的液体推进剂火箭发动机系统的详细说明，以及进行的测试结果。地面测试是在安卡拉TUBITAK-SAGE的静态测试坡道上进行的。在第一次电动机测试中，未获取任何数据，并且使用正常速度和高速摄像机观察了火箭发动机的一般特性。在以后的测试中，两个压力传感器安装在火箭液体推进剂火箭发动机（LPRM）系统上。第一个传感器安装在火箭发动机主体上，以测量燃烧室压力，第二个传感器安装在空化文丘里管的出口。火箭发动机铝制外壳装有三个应变计和两个温度传感器。第三温度传感器也放置在喷嘴出口处，以测量喷嘴出口气体温度。

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