In this paper , data mining was applied to acquire knowledge to solve the bottleneck problem of knowledge acquisition in the fault detection and diagnosis of liquid rocket engine 本文利用数据挖掘技术提取知识,以克服液体火箭发动机故障检测和诊断系统知识获取的瓶颈。
At last , the sensor fault diagnostic software of liquid rocket engine ground test system is developed successfully , including the designs of arithmetic , database and interface software 本文开发了液体火箭发动机试车台传感器故障诊断系统,包括算法实现、数据库设计和用户界面设计。
The application of computer numerical modeling and simulation technology in liquid rocket engine spray combustion design is discussed . the suggestion for further development is presented 讨论了计算机数值模拟与仿真技术在液体火箭发动机喷雾燃烧设计中的应用并提出了进一步发展的意见。
Abstract : the application of computer numerical modeling and simulation technology in liquid rocket engine spray combustion design is discussed . the suggestion for further development is presented 文摘:讨论了计算机数值模拟与仿真技术在液体火箭发动机喷雾燃烧设计中的应用并提出了进一步发展的意见。
The fault diagnosis of liquid rocket engine can be considered as a problem of mode identification , the task of which is to divide samples into mode types by obtained characteristics 液体火箭发动机故障诊断可视为一个模式识别问题,模式识别的任务是利用从样本中提取出的特征,将样本划分成相应的模式类别。
A lot of parameters needed to be detected for the fault detection and diagnosis of liquid rocket engine . data need to be recorded at every certain time , so , large amount of data need to be analyzed 由于液体火箭发动机故障检测和诊断需要大量的参数,而且每隔一定的时间步长就要记录一次数据,直到试车结束,因此,液体火箭发动机故障检测和诊断需要分析大量的数据。
The faults of liquid rocket engine are all kinds of abnormal states and the states different from preconcerted working states . the fault detection of liquid rocket engine is a judgement process for engine working state by measured data 液体火箭发动机故障检测是利用由传感器测量得到的、反映发动机当前工作状态的测量数据,经特征提取后,对发动机是否正常工作做出可靠判断的过程。
The key is atomizing the propellant perfectly through nozzles , which are the most important elements in the chamber of liquid propellant rocket engine . it is very necessary of the experimental and theoretic to research on them 达到这一目标的关键在于通过喷嘴使推进剂组元产生良好的雾化，因此，喷嘴是液体火箭发动机推力室最关键的部件之一，对其进行充分的理论和实验研究十分必要。
Reliability assessment method in the case of zero - failure and few - failure data of liquid rocket engine is mainly researched in this dissertation , and it has carried on the discussion to the method that the reliability data conversion under different operating status 本文主要研究了液体火箭发动机在无失效以及极少失效条件下的可靠性评估方法,并对不同工况下可靠性数据折算的方法进行了探讨。
The results of static firing test shows that the thermal erosion properties , mechanical properties , tand thermal shock resistance of the c / sic composites can meet a demand for thermal - structure application in the area of aerospace such as liquid rocket thruster 试验发动机地面热试车结果表明，该c / sic复合材料的力学性能、烧蚀性能和热震性能优良，可满足宇航工程中诸如液体火箭发动机推力室等对热结构材料的使用性能要求。
