Figure 1.24. Schematic of the control of the Apollo docking mechanism. 1. power supply switches with automatic shielding; 2. “retraction-undocking” switches; 3. lock sensors; 4. linkage sensors; 5. terminal switches; 6. electromagnet of the catch; 7. electromagnet of the latches; 8. pyrotechnic fuse of the frame; 9. retraction switch (back-up); 10. back-up cable; 11. pyrotechnic needles of tanks; 12. switch to fire the frame; 13. transparency; 14. extension switch (tank 1). 15. tank; 16. supply for pyrotechnics; 17. (to system B); 18. from automation of emergency rescue system. 1.5.5. APDA's for the Apollo-Soyuz Project After preliminary negotiations between the directors of NASA and the USSR Academy of Sciences, in 1970 meetings of specialist in the USSR and USA began on the creation of compatible equipment for the approach and docking of spacecraft. Analysis was done on the experience which had been accumulated up to this time, and the specialists decided to create a principally new docking device, a peripheral androgynous type [26, 59]. This type of docking mechanism is located along the periphery of the docking frame; thus, the docking device is called a peripheral
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