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针对焊接工艺应用于高体积分数SiC/Al复合材料的不成熟性研究了焊接工艺应用于航天遥感器机身结构的的稳定性。根据光学设计公差分析结果和机身的结构形式,提出了通过运用经纬仪和三坐标测量机测量角量和线量的验证原理,论证了胶接工艺的可行性。对机身进行了热循环试验,标定了实验前后各测点的角度以及距离,对实验前后的数据进行了比较。结果表明,机身最大转角俯仰方向为2.1″,方位方向为2.3″,机身三个方向的最大距离变化分别为0.034mm,0.044mm,0.034mm,焊接工艺应用于高体积分数SiC/Al复合材料,能够满足设计指标为转角小于5″,距离公差±0.05mm的设计要求。
Aiming at the immaturity of high volume fraction SiC / Al composites by using welding process, the stability of the welding process applied to the fuselage structure of aerospace sensors was studied. According to the results of optical design tolerance analysis and the structural form of the fuselage, a verification principle of measuring the amount of angle and the amount of wire by using theodolite and CMM is proposed. The feasibility of the bonding process is demonstrated. The thermal cycling test was carried out on the airframe, the angles and distances of each measuring point before and after the experiment were calibrated, and the data before and after the experiment were compared. The results show that the maximum rotation angle of the fuselage is 2.1 “and the azimuth direction is 2.3”. The maximum distance variation in the three directions of the fuselage is 0.034mm, 0.044mm and 0.034mm respectively. The welding process is applied to SiC / Al composite with high volume fraction Material, designed to meet the design criteria for the corner of less than 5 ", tolerance ± 0.05mm design requirements.