which will actually affect the execution of given functions by the docking device. The following methods are used to determine testing conditions: 1) analysis of the conditions of previous flights (the level of vibration, impact, and linear overloads, the depth of vacuum, etc.); 2) theoretical analysis and calculation of the working parameters and conditions (loads, temperatures, etc.); 3) combined testing methods (7.1 and 7.2); 4) the use of results of other types of Earth testing (for example, the determination of loads from dynamic tests, temperatures during thermal testing, etc.); 5) analysis of potential failures and their consequences to determine the most critical operations and elements; 6) analysis of criticality of the effect of various conditions (temperature, vacuum, etc.) in flight and in Earth testing; 7) analysis of failures in Earth and flight testing. An analysis was done of failures which took place during flight testing. The analysis showed that the majority of failures occurred due to incorrect interactions of elements of the docking system among themselves and with other systems which were not revealed during Earth testing or pre-flight testing. This confirmed the need for integrated verification in testing. The loading of the shock absorbers of the APDA with unrated loads was brought about by incorrect use of the Apollo control system. This was prevented by introducing special Earth testing and training (see section 7.7.4). Experience has shown that the failure of individual elements and units occurs in flight much more rarely, because organization of flight testing is simpler, and construction drawbacks are usually eliminated during testing. An analysis was also made of failures which occurred during debugging and Earth testing. It showed that: 1) the majority of failures occur in the initial stage of testing in the execution of basic functions, in electrotechnical verification, and in heavy-duty loads on assemblies and individual units; 2) many of the failures occur due to incorrect interaction of docking device elements, frequently units of the mechanism operate incorrectly due to deformations of the construction; 3) of extreme conditions, the one which has the most effect is vibration overloading (primarily on screw lock threaded connections), and in a number of cases, cooling may cause an unacceptable change in characteristics; 4) heating (to 50-70*C) and vacuum, especially for a short lifetime, has a lesser effect on electromechanical docking devices. Thus, the main attention in the testing of units should be concentrated on
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