control engines of the Apollo operating along the x axis was , and the equivalent thrust was 33% of that is,. If the engines of the Soyuz had been turned on (thrust), the equivalent thrust would have been . Considering the effect of the thrust of the jet control system the equation of deformation of the shock absorbers of ring rotation at small angles has the form Analysis shows that the momenta rotating the spacecraft to align the rings are small. This is due to the fact that the radii are small, although is close to the mass of direct impact . Overall, the spacecraft may rotate due to the effect of other forces and initial velocities to align the rings and to open them. In design calculations, one must consider that for linkage the ring must rotate by an angle equal to the initial value of not considering the rotation of the spacecraft themselves. To approximately determine the characteristics of the shock absorbers it is sufficient to examine the energy correlations. The kinetic energy of the relative motion of the bodies and the action of equivalent thrust may be sufficient to rotate the ring by the given angle defined by the initial conditions and the rotation of the spacecraft from first contact to contact of the rings, that is, One can use the characteristic of the shock absorber , and the dependence of the work of force (Figure 5.20) to determine the maximum angle of rotation of the ring for a given velocity of approach and thrust or solve the reverse problem: determining the minimal velocity of approach at which linkage occurs for a given angular displacement of the longitudinal axes of the spacecraft. For example, when the ring of the Soyuz APDA is at an angle , with
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