Figure 1.14. Cyclogram of docking using the docking device for the Salyut-Soyuz complex. 1. work of the control system and docking assembly mechanisms; 2. approach; 3. shock absorption; 4. coupling of docking mechanisms; 5. coupling of joint; 6. Uncoupling and separation of rod; 7. verification of hermeticity; 8. opening of hatches; 9. contact; 10. jet control system; 11. contact sensor 1, linkage; 12. contact sensor 2; 13. alignment of joint; 14. docking mechanism drive; 15. DSS [unknown sensor]; 16. DOU [unknown sensor]; 17. lock drive; 18. latch drive; 19. 1.5-3 hours; 20. hermetization drive; 21. hatch drive; 22. signaling to cosmonaut's panel; power to system; 23. docking mechanism: coupling; 24. uncoupling; 25. locks: open; 26. close; 27. latches: retracted; 28. advanced; 29. electrical connections; 30. hatch: closed; 31. opened. 1.5.3. Docking Device for the Gemini Program The first docking device created in the USA was used to dock the Gemini spacecraft with the Agena rocket stage [34, 44]. The designers intended the docking device to be the basis for subsequent projects. The Gemini program did not require a hermetized transition between the spacecraft, but the design and configuration of the docking device could be relatively simply changed to form a transition tunnel. However, analysis done during work on the Apollo project detected poorer weight,
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