Figure 5.10. Dependence of on the angle between the longitudinal axes of the spacecraft. 1. Soyuz-Soyuz; 2. Soyuz-Salyut; 3. Soyuz-“heavy” station, a. (Soyuz-Salyut); b. mx (Soyuz-Soyuz); c. #(0), degrees. the coefficient of recovery for impacts with the cone; the total course of the longitudinal shock absorber is reduced; one can reduce the return spring. It is interesting to determine on which Spacecraft, from the point of view of the energy capacity of the shock absorbers, it is more suitable to install the docking mechanism, and on which the receiving cone. Analysis of the dependence of on the angle between the longitudinal axes of the spacecraft shows that if the cone is installed on the “light” spacecraft, and the docking mechanism on the “heavy” spacecraft, the maximum energy in impacts with the cone is larger than in the converse case. Thus, if the passive assembly of the Salyut station is installed on the Soyuz craft, the energy capacity of the first stage of the longitudinal shock absorber must be increased by a factor of 1.9. The characteristics of the shock absorbers determine the coefficient of recovery s in impacts with the cone. It is important for the designers of docking devices to know the maximum allowable value of at which linkage is performed. One can obtain the following formula, which is deduced from the assumption that the end of the rod is guaranteed to enter the vertex of the cone, without considering the action of the jet control system, and given that the angles between the axes of the spacecraft do not exceed permissible values:
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