Figure 5.15 [left]. Dependence of force F= in a central impact for Ft — 6 kN (Soyuz-Soyuz). 1. not considering the inertia of the shock absorber; 2. considering the inertia of the shock absorber. X-axis in seconds, y-axis in kN. Figure 5.16 [right]. Dependence of applied inertial momentum on angle. 1. two Soyuz spacecraft; 2. Soyuz-Apollo; 3. Salyut-Soyuz; 4. Soyuz-“heavy” station. Top: lo10s, kgm2; bottom, #(0), degrees. absorbed in the further course of the rod. For example, the longitudinal shock absorber of the Soyuz-Salyut docking mechanism, at a maximum course of 0.1 m absorbs 900 J of energy. The full course of the rod, until the rod contacts the docking frames, is 0.4 m. The energy which may be absorbed by the brake in this course, not considering the energy scattered by the electromagnetic brake, is 4 kJ. Thus, for these conditions one can provide sufficient shock absorption during docking with a longitudinal velocity exceeding the maximum by more than a factor of two. 5.5.4. Shock Absorption of Angular Rotations Low frequency oscillations of the spacecraft in the angular shock absorber may be studied using a simplified (5.27) with , that is, after deformations
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