5) bail-screw converter; 6) blocks of differentials; 7) latches; 8) locks of the docking frame; 9) electrical connections; 10) hydraulic connections, etc. 3.2. General Configuration. Hulls of the Docking Assemblies The general configuration and size of the assembly depend on its position on the spacecraft, and as a rule, are limited by the cowl, the so-called payload zone on the rocket booster. Significant dynamic overloads in a wide range of frequencies arise in the active portion of the flight; thus, it is necessary to have very rigid attachment of units and elements. As a rule, cantilevered attachments of the long and heavy parts and assemblies are unacceptable. The docking assembly has a large number of units which require correct interaction, and which are connected by a .ompiex system of electrical cable connections. Overall, the configuration of docking assemblies is a complex task, and its solution requires the choice of a valid force schematic, efficient arrangement of units, technological efficiency of manufacturing and assembly, and convenient access to the units which require servicing during testing and use. The hull of the docking assembly usually consists of a casing with a docking frame and a rear flange to attach to the spacecraft. In the internal cavity of the docking frame are locks with drives where cable connections and other units of the joint are mounted. There should be good access for assembly, regulation, and monitoring. The number of locks is significantly smaller than the number of bolts connecting the analogous joints. Thus, the docking frame should be sufficiently rigid. The largest load is on the hull of the hermetic docking device; its design, manufacturing, and testing are very complex. The rigidity of the frame of the hermetic hull should be such that deformations from external and internal loads do not permit the formation of significant gaps in the joint. Experiments show that the formation of local gaps 0.1-0.2 mm in size do not lead to disintegration of hermeticity. These dislocations, however, should be considered in the determination of the rigidity of the docking device in bending and stretching, since the lengthening of the docking assembly hulls are about on that order. In joint testing of the APDAs, the docking assemblies were loaded with a bending momentum =
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