Annotation: The paper describes the spacecraft separation system ground functional tests, including SC separation dynamics refinement, in the process of which the separation system operability is confirmed and the parameters characterizing separation dynamics are determined.

Annotation: The technique is proposed to determine width of the spherical-type flange coupling’s metal gasket clamping area by the specified joint tightening force considering the joint geometry and mechanical properties of the gasket material.

Annotation: The paper is about the ground tests to refine the action dynamics of dividing valve operating in liquid oxygen environment.

Annotation: To support ignition of Taurus LV first stage core structure engine, an oxidizer dividing valve has been developed that ensures minimal hydraulic resistance, opening time and hydraulic impact. The paper considers the valve design, main phases of its ground development testing and basic critical comments on the design made in the process of manufacturing and testing.

Annotation: The paper deals with the result of solution of one of most important and topical problems of space rocket engineering – creation of launch vehicle space head modules ensuring injection of various class spacecrafts into target orbits providing high separation reliability and orbital motion accuracy.

Annotation: The comparison of Integrated Launch Vehicles structural perfection coefficients shows that Yuzhnoyedeveloped Cyclone-4 launch vehicle has structural perfection at the best world rocket model level

Annotation: The paper is about the development by Yuzhnoye SDO of modern integration means, namely devices for spacecraft attachment and separation to/from the launch vehicles that meet the high requirements of present-day launch services market and ensure highly reliable spacecraft separation with minimal disturbances.

Annotation: The article deals with the peculiarities of creation of technological crimping device for assembling the spacecraft separation system clamp band. The crimping device is intended to ensure uniform distribution of tension forces in the clamp band belts during assembling of the attachment clamp band, which allows minimizing the load on pyrolocks-pushers and thereby ensuring their operation reliability. The device consists of pressing mechanisms located along circumference symmetrically to the clamp band belts interface plane and fixed on a rest with adjustable supports. The pressing mechanism is a structure with driving kinematic scheme, which allows compensating for mounting errors, unfavorable combination of tolerances, avoiding occurrence of radial load on the thrust screw. However, during testing of the clamp band assembling technology, jamming of threaded connection as a result of thrust screw turn crush in the area of first turn of insert, gap in the thread after multiple use, scratches and minor scores on the conical surface of pressing mechanism, hardship of work with two wrenches were detected. To remove these defects, the sleeve with insert was replaced by the sleeve with protruding part, which allowed distributing the load in all turns more uniformly. The material of nut and screw was replaced based on relation between the strength limits: σв of rod > 1.3 σв and nut. The design of pressing mechanism was changed in respect of connection of thrust screw with hold-down, which allowed decreasing the load on screw pair as a consequence of axial force transfer from screw’s spherical surface to flat surface of hold-down, decreasing the tightening moment to ensure design force of clamp band belts fixation and making the process of pressing mechanisms assembling and disassembling easier. As a result of the updates, the manufacturable and ergonomic structure of crimping device was obtained, the use of which during assembling of the clamp band allows uniformly distributing the crimping forces in clamp band belts, which ensures reliability of spacecraft separation system operation.