Table 2.1. Mass of units and elements of several docking assemblies, a. group of units and elements; b. mass, kg; c. Soyuz docking device; d. Soyuz-Salyut docking device; e. Soyuz APDA; f. Apollo APDA; g. active; h. passive; i. hull; j. docking mechanism; k. mechanisms of the docking frame, including the locks and drive; 1. additional elements; total mass; n. *With hatch, 480 kg. order to reduce the weight of the peripheral docking mechanism, one must primarily reduce the size of the ring with the guide protrusions, and this requires a reduction of the initial displacement in the first contact of spacecraft (see section 1.4). A decrease in the initial velocity of the approach makes it possible to decrease the length and force of the shock absorbers, which in the final analysis also leads to a lighter docking mechanism structure. Naturally, reduction of the initial velocities will also make it possible to reduce the weight of the docking mechanism with the rod. However, peripheral docking mechanisms have many more elements (the rod, shock absorbers, etc), the weight of which may be decreased. There is yet another way to lighten the APDAs. One can reduce the weight of all groups of mechanisms and elements. As a rule, there is no need to install on all spacecraft completely equipped APDAs. If the flight program allows, one can use a lightened docking assembly which is compatible with the APDA and economize on mass. One can create, for example, a fully passive assembly which is compatible with the APDA which is 2-2.5 times lighter than the latter.
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