【作者】 肖学海；

【导师】 李进贤；

【作者基本信息】 西北工业大学 ， 火炮、自动武器与弹药工程， 2004， 硕士

【摘要】 我国发展中远程、超音速导弹计划已经启动，其动力装置首选固体火箭冲压发动机，而地面试验技术是发动机研究重要基础。 本文以西北工业大学固体火箭冲压发动机直连式试车台为研究对象，探讨固体火箭冲压发动机地面试验技术。 首先，从推力的定义出发，建立了试验中来流空气流量、燃料流量与固体火箭冲压发动机推力之关系。通过讨论高空飞行推力与地面可测试参数的关系，得到了固体火箭冲压发动机高空飞行状态下推力折算方法，并开发相应的计算程序。 其次，为满足固体火箭冲压发动机试验技术进一步研究需要，在深入分析LabVIEW图形化编程软件优化方法的基础上，改进了现有的固体火箭冲压发动机试验测控程序，并应用于发动机试验中。 最后，通过固体火箭冲压发动机试验验证研究成果的正确性，并实际应用。 应用表明，推力计算方法正确，改进的测控程序运行良好、方便实用、稳定可靠。 本文研究成果对发动机地面试验进行、对试验发动机性能的评估以及对今后进一步的发动机研究具有重要的意义。更多还原

【Abstract】 The research of the high-powered solid rocket-ramjet engine has been launched, which is one of the key technologies of the middle-long and supersonic missile project. The determination of solid rocket ramjet thrust and testing method are the important basis of the developing engine.An experimental program evaluating solid rocket-ramjet in NWPU connected-pipe facility is underway. According to the definition and expression of the thrust, as well as the condition derived from them, a method of solid rocket ramjet thrust determination and its program are provided on the basis of engine ground simulation test.In order to determination the thrust, the thrust definition and many control parameters are analyzed discussed, which mass flow rate and flight altitude are involved.It is difficult to measure the flight thrust of solid rocket ramjet directly. It is determined now by calculation with mathematical relationship of the flight thrust to the physical quantities which can be measured directly.The optimization of the software development platform is also analyzed inspect of the solid rocket-ramjet developmental program.The comparison of calculation results with experimental data confirms the reliable of the determination method of the flight thrust.更多还原