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首页> 外文会议>AIAA/ASME/SAE/ASEE joint propulsion conference exhibit >Advanced Development of a Compact 5-15 lbf Lox/Methane Thruster for an Integrated Reaction Control and Main Engine Propulsion System
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Advanced Development of a Compact 5-15 lbf Lox/Methane Thruster for an Integrated Reaction Control and Main Engine Propulsion System

机译：紧凑型5-15 lbf Lox /甲烷推进器的高级开发，用于集成反应控制和主机推进系统

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This paper describes the advanced development and testing of a compact 5 to 15 lbf LOX/LCH4 thruster for a pressure-fed integrated main engine and RCS propulsion system to be used on a spacecraft "vertical" test bed (VTB). Allowing the RCS thruster and the main engine to be fed from the same propellant supply in zero-g reduces overall system mass and improves mission flexibility. This compact RCS engine incorporates several features to dramatically reduce mass and parts count, to ease manufacturing, and to maintain acceptable performance given that specific impulse (Isp) is not a key requirement. For example, radial injection holes placed on the chamber body for easier drilling, and high temperature Haynes Alloy 230 was selected for the chamber over other more expensive material options. Before welding, the valve inlets are rotatable before welding allowing different orientations for easier vehicle integration. In addition, the engine design effort selected a coil-on-plug ignition system which integrates the coil driver and coil with the plug electrode, and moves the trigger electronics to the avionics driver board. The engine injector design has small dribble volumes to target minimum pulse widths of 20 msec, and an efficient minimum impulse bit of less than 0.05 lbf-sec. The propellants, oxygen and methane, were chosen because together they are a non toxic, Mars-forward, high density, space storable, and high performance propellant combination that is capable of pressure-fed and pump-fed configurations as well as integration with life support and power subsystems. This paper will present the results of the advanced development testing to date of the RCS thruster and the integration with a vehicle propulsion system.
机译：本文介绍了用于航天飞机“垂直”测试台（VTB）的压力馈送集成式主机和RCS推进系统的紧凑型5至15 lbf LOX / LCH4推进器的高级开发和测试。允许RCS推进器和主机从相同的推进剂供气量为零克，这可以减少整个系统的质量并提高任务的灵活性。鉴于特定的脉冲（Isp）不是关键要求，因此该紧凑型RCS引擎具有多项功能，可显着减少质量和零件数量，简化制造并保持可接受的性能。例如，为了方便钻孔而在腔体上放置了径向注入孔，并且比其他更昂贵的材料选择了高温Haynes合金230作为腔体。在焊接之前，气门入口在焊接之前是可旋转的，从而允许不同的方向，从而使车辆易于集成。此外，发动机设计人员选择了一个塞上线圈点火系统，该系统将线圈驱动器和线圈与塞式电极集成在一起，并将触发电子装置移至航空电子驱动器板上。发动机喷油器的运球量较小，目标最小脉冲宽度为20毫秒，有效最小脉冲位小于0.05 lbf-秒。之所以选择氧气和甲烷作为推进剂，是因为它们是无毒的，火星前进的，高密度，可储存空间的高性能推进剂组合，能够压送和泵送配置，并与生命融为一体支持和电源子系统。本文将介绍RCS推进器迄今进行的高级开发测试的结果以及与车辆推进系统的集成。

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