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0.034 mm,0.044 mm,0.034 mm,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±0.05 mm的设计要求。

As for the immaturity of the weld technology applied to the high volume fraction SiC/Al composites, the stability of the space remote sensor skeleton construction was studied. According to the findings of the tolerance analysis of optical deign and structures, the verification of measuring angle and linearity using three-coordinate measuring machine and theodolite was proposed. The feasibility of cementing technology was demonstrated. By the thermal cycling test of frame, the angel and the distance of measuring point were calibrate. The calibrated data was compared. The results show that the torsional angel of the frame is 2.1″ in pitch, 2.3″ in azimuth, and the changes of the distance in the three directions are 0.034 mm, 0.044 mm and 0.034 mm, which can meet the technical requirements of torsional angel smaller than 5″ and the distance tolerance of ±0.05 mm.