Fig. 1. Internal disturbance source of micro-vibration of aerospace optical camera

Fig. 2. Perturbation causes boresight jitter to produce image shift

Fig. 3. Structure and optical system model of the SNAP spacecraft^［16］

Fig. 4. Optical-mechanical integration analysis process of SNAP spacecraft

Fig. 5. Mars terminal payload model and optical system model^［18］

Fig. 6. Optical-mechanical integration analysis process of Mars terminal payload model

Fig. 7. FY-4 satellite

Fig. 8. Optical-mechanical integration analysis of FY-4

Fig. 9. JL-1 Gaofen-03 satellite model and optical system^［21］

Fig. 10. Micro-vibration centralized analysis process^［22］

Fig. 11. Micro-vibrational integration model based on imaging deletion^［21］

Fig. 12. Topology optimization model of opto-mechanical structure

Fig. 13. Terrestrial Planet Finder and the optical system^［27］

Fig. 14. TPF integrated modeling analysis^［28］

Fig. 15. SDO and finite element model^［34］

Fig. 16. SDO integration model^［33］

Fig. 17. SSTL-300S1 satellite and finite element model^［38］

Fig. 18. Craig-Bampton random method flow chart^［38］

Fig. 19. JWST Conceptual Model^［40］

Fig. 20. JWST opto-mechanical integration analysis model^［41］

Fig. 21. Full-link integration model^［28］

Fig. 22. Dynamic analysis process of the optical machine structure based on linear state space

Fig. 23. Relationship between Wave Front Aberration and Rigid Body Displacement

Fig. 24. Outlook for optical-mechanical integration analysis