the efTect of the thrust of the jet control system and characteristics of the springs given in Table 5.1 and in Figure 5.9, and with damping with an electromagnetic brake with a coefficient s/m the necessary velocity of approach is 0.14 m/s. It is very important to delay actuation of the jet control system. A delay of 0.5 s (the maximum value allowed in the Apollo-Soyuz project) increases the required velocity m/s. To insure linkage at small approach velocities, according to the results of testing of the APDA, the dampers in the Figure 5.20. Energy correlations during rotation of the ring (Soyuz APDA). 1. force characteristic of the shock absorber; 2. energy absorbed by the shock absorber; 3. equivalent thrust; 4. work of the force of thrust; 5. kinetic energy, a. .shock absorbers of ring elevation were removed and the force of the springs somewhat reduced. These changes increased the lower limit of the approach velocity at which the ring could rotate by . This change, and some decrease in the inertia of the moving parts of the docking mechanism also substantially decreased the maximum value of the longitudinal force for central impact (by about 40%). Linkage can always occur if the static force of the inclination of the ring is less than the equivalent thrust Thus, for the Apollo-Soyuz project this force
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