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281.
为了清晰地反映涡轮叶片的疲劳-蠕变交互作用,提高寿命预测结果的准确性及可靠性,并改善涡轮叶片疲劳寿命对随机变量的敏感程度,分别采用Manson-Coffin公式和Larson-Miller方程计算了涡轮叶片的低循环疲劳寿命和蠕变持久寿命,利用修正的时间-寿命分数法计算了涡轮叶片疲劳-蠕变损伤,在此基础上,将响应面法(RSM)与果蝇优化算法(FFOA)相结合,考虑载荷、材料参数、疲劳-蠕变交互程度的不确定性,对涡轮叶片疲劳寿命进行了稳健性优化设计。优化结果表明:涡轮叶片疲劳-蠕变小时寿命的概率区间减小了8.48%,验证了该优化方法的工程可行性。 相似文献
282.
针对复合材料单面胶接修理飞机损伤金属结构疲劳寿命分析时,多种失效模式耦合作用、残余热应力和附加弯曲力矩以及裂纹非均匀扩展的影响,提出了一种能够综合考虑上述影响因素的复合材料修理损伤金属结构疲劳寿命评估方法。算例分析结果与试验结果吻合,表明本文方法可为复合材料单面胶接修理损伤金属结构疲劳寿命估算提供参考。 相似文献
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284.
《中国航空学报》2021,34(4):451-464
For higher efficiency and precision manufacturing, more and more attentions are focused on the surface roughness and residual stress of machined parts to obtain a good fatigue life. At present, the in-situ TiB2/7050Al metal matrix composites are widely researched due to its attractive properties such as low density, good wear resistance and improved strength. It is of great significance to investigate the machined surface roughness, residual stress and fatigue life for higher efficiency and precision manufacturing of this new kind material. In this study, the surface roughness including two-dimensional and three-dimensional roughness, residual stress and fatigue life of milling in-situ TiB2/7050Al metal matrix composites were analyzed. It was found from comparative investigation that the three-dimensional surface roughness would be more appropriate to represent the machined surface profile of milling particle reinforced metal matrix composites. The cutting temperature played a great role on the residual stress. However, the effect of increasing cutting force could slow down the transformation from compressive stress to tensile stress under 270 °C. An exponential relationship between three-dimensional roughness and fatigue life was established and the main fracture mechanism was brittle fracture with observation of obvious shellfish veins, river pattern veins and wave shaped veins in fracture surface. 相似文献
285.
Pascal Willis Hervé Fagard Pascale Ferrage Frank G. Lemoine Carey E. Noll Ron Noomen Michiel Otten John C. Ries Markus Rothacher Laurent Soudarin Gilles Tavernier Jean-Jacques Valette 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2010
DORIS is one of the four space-geodetic techniques participating in the Global Geodetic Observing System (GGOS), particularly to maintain and disseminate the Terrestrial Reference Frame as determined by International Earth rotation and Reference frame Service (IERS). A few years ago, under the umbrella of the International Association of Geodesy, a DORIS International Service (IDS) was created in order to foster international cooperation and to provide new scientific products. This paper addresses the organizational aspects of the IDS and presents some recent DORIS scientific results. It is for the first time that, in preparation of the ITRF2008, seven Analysis Centers (AC’s) contributed to derive long-term time series of DORIS stations positions. These solutions were then combined into a homogeneous time series IDS-2 for which a precision of less than 10 mm was obtained. Orbit comparisons between the various AC’s showed an excellent agreement in the radial component, both for the SPOT satellites (e.g. 0.5–2.1 cm RMS for SPOT-2) and Envisat (0.9–2.1 cm RMS), using different software packages, models, corrections and analysis strategies. There is now a wide international participation within IDS that should lead to future improvements in DORIS analysis strategies and DORIS-derived geodetic products. 相似文献
286.
A new type of aluminum lithium alloy (Al-Li alloy) Al-Li-S-4 was investigated by test in this paper. Alloy plate of 400 mm · 140 mm · 6 mm with single edge notch was made into samples bonded with Ti-6Al-4V alloy (Ti alloy) strap by FM 94 film adhesive after the surface was treated. Fatigue crack growth of samples was investigated under cyclic loading with stress ratio (R) of 0.1 and load amplitude constant. The results show that Al-Li alloy plate bonded with Ti alloy strap could retard fatigue crack propagation. Retardation effect is related with width and thickness of strap. Flaws have an observable effect on crack propagation direction. 相似文献
287.
Quanyong Cheng Shuangsheng Guo Weidang AiYongkang Tang Lifeng Qin 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
Material closure is important for the establishment of Bioregenerative Life Support System, and many studies have focused on transforming candidate plant residues into plant culture medium. For the limitations of using wheat straw compost as substrate for plant cultivation, a straw-soil co-composting technique was studied. The changes of pH, C/N value, germination index, cellulose, lignin and so on were monitored during the co-composting process. The maturity was evaluated by the C/N value and the germination index. The result showed that after 45 days’ fermentation, the straw-soil final co-compost with inoculation (T1) became mature, while the co-compost without inoculation (T0) was not mature. In the plant culture test, the T1 substrate could satisfy the needs for lettuce’s growth, and the edible biomass yield of lettuce averaged 74.42 g pot−1 at harvest. But the lettuces in T0 substrate showed stress symptoms and have not completed the growth cycle. Moreover, the results of nitrogen (N) transformation experiment showed that about 10.0% and 3.1% N were lost during the T1 co-composting and plant cultivation, respectively, 23.5% N was absorbed by lettuce, and 63.4% N remained in the T1 substrate after cultivation. 相似文献
288.
采用系统灵敏度理论,以修正的带宽准则,增益和相位裕度准则以及Neal-smith准则等飞机纵向驾驶员诱发振荡(PIO)预测准则作为系统指标,建立了参数变化对诱发振荡预测指标影响的灵敏度公式,以JJ7飞机为例,给出了飞机,操纵系统及驾驶员参数上述指标影响的灵敏度,根据计算结果进行了PIO参数敏度预测分析,同时与数值仿真结果进行了对比分析。 相似文献
289.
290.
载人航天器具有系统规模大、技术难度高、单件小批量、无法通过多次飞行持续完善设计、可靠性要求高等特点。当前载人航天器研制中仍存在着参数化和模型化程度不高、基于模型的系统综合仿真验证不足、研制各环节缺乏数字化集成等问题,传统基于文本的系统工程方法已无法满足研制需求,亟需采用基于模型的系统工程方法。本文针对载人航天器的研制现状和应用需求,提出了面向载人航天器全生命周期的模型体系,定义了需求模型、功能模型、产品模型、工程模型、制造模型、实做模型等六类模型,提出了基于模型的研制流程,包含系统设计闭环验证、产品设计闭环验证、实做产品闭环验证3个验证环节,并深入探索了各研制环节中不同模型间的传递与关联关系。以某型号载人航天器为应用基础,系统地验证了提出的方法。 相似文献