| 1. | The experimental results show that distortion of the monolithic component from odd - even of the three different sequences is the smallest
结果表明，三种模拟结果中奇偶铣削加工得到的结构件的变形最小。 |
| 2. | The first stage of cbd is the era of monolithic components , a seeming oxymoron that describes the adolescent state of components today
Cbd的第一阶段是单片式组件的时代，是今天组件青春期表面矛盾的描述。 |
| 3. | Three milling machining sequences consisting of ordinal , odd - even and even - odd were simulated based on the model for frame monolithic components
利用该模型对整体框类结构件进行了奇偶铣削、偶奇铣削和顺序铣削三种加工顺序的有限元模拟。 |
| 4. | The agreement of simulation and experimental results proves the validity of the model for predicting distortion law of aerospace monolithic components due to milling process
该模型对三种加工顺序的模拟结果与试验结果一致，可用于预测整体结构件的加工变形。 |
| 5. | In the next stage , monolithic components give way to distributed components as maturing component standards and new infrastructural components permit component interoperability and portability
在下一阶段，随着成熟的组件标准和新的基础设施组件允许实现组件的互操作性和可移植性，单独式组件让位于分布式组件。 |
| 6. | To resolve the problem of distortion of large - complex aerospace monolithic components during milling process , a finite element model ( fem ) of milling process simulation in distortion field and temper - attire field was established
摘要为了控制尺寸大、形状复杂的航空框类整体在铣削加工时产生的变形，建立了铣削加工时的变形场和温度场的有限元模型。 |
| 7. | In chapter 1 , the background and significance of this research is introduced firstly . then , the state of the art in the research of machining distortion of the monolithic component is summarized . finally , the main contents and frame structure of this dissertation are shown
第一章阐述了论文研究的背景和意义,总结了航空整体结构件数控加工变形的国内外研究现状,提出了本论文的研究内容和总体框架。 |
| 8. | Machining deformation of aircraft monolithic component is simulated by finite element method ( fem ) and validated by experiment . the initial residual stress in pre - stretched plate is generated by simulating quenching and stretching processes . with a single tool - tooth milling process fem , the machining loads in monolithic component material removing is obtained . restart - calculation is put forward to complete the whole simulation of machining process . to verify the fem result , an experiment is carried out . the deformation distribution of the monolithic component resulting from fem shows a good agreement with the experiment result , which indicates that the key technologies presented in the paper are practicable and can be used to simulate the milling process of monolithic component to predict its deformation . lengthy and expensive trial and error experiment process can be avoided
在模拟淬火、拉伸过程获得含有初始残余应力的预拉伸板材以及模拟单齿切削过程获得切削载荷的基础上,提出并采用接力算法,对一航空整体结构件的材料铣削过程进行有限元仿真,同时进行了试验研究.结果表明,有限元模拟的整体结构件的变形与试验具有一致性,从而证明提出的整体结构件加工仿真关键技术的可行性,避免了为研究加工变形而进行的繁琐的试错法 |
