Time delay integration (TDI) CCD focal plane assembly is one of the most important components for a space camera, which mainly fulfill photoelectric conversion and output video signal of analog CCD. Due to the hard condition resulted from the transportation and launch of a space camera, it is difficult to keep a TDI CCD with high interleaving precision. Therefore, in this work, we design a TDI CCD focal plane assembly with a good performance based on the optimization both on structural control and thermal control. According to the analysis of the factors that affect the interleaving precision of a TDI CCD focal plane assembly and the maximal error of three axes theoretically, we design an especial structure for a TDI CCD focal plane assembly to keep the high interleaving precision of a TDI CCD which can fit the hard condition for the transportation and launch of a camera and the harsh on-orbit operating temperature. The effectiveness of the modified TDI CCD focal plane assembly is supported by the results obtained from dynamic test and thermal vacuum test. For the dynamic test, the response result shows that the assembly can conquer the interference of dynamic environment and keep a high interleaving precision of TDI CCD. For the thermal vacuum test, thermal balance test indicates that the highest temperature of TDI CCD is 30 ℃ in 1.5 min, which can work properly. The interleaving precision of focal plane is done after the dynamic environment and thermal vacuum tests. The linearity error of the TDI CCD is 3.5 μm, the interleaving error is 4 μm, the parallelism error between two lines of the TDI CCD is 3.5 μm, and the coplanar error of 4 TDI CCD is 5 μm. These results satisfy the optical design very well. Therefore, the aforementioned course proves that this design is feasible and precise, and it can achieve a high interleaving precision for a TDI CCD.