Annotation: The paper addresses a new, authors- developed method of mass optimization of rocket bays of wafer structure bearing during operation on locally disposed parking supports. The method allows, due to more rational distribution of materials in the structure in accordance with acting load, decreasing the mass of bays by up to 20%.

Annotation: The paper considers the TZS-U design developed by Yuzhnoye SDO specialists for windward part of reusable spacecraft with external metal three-layer panel, U-like joint and tiled thermal protection, in which the problem is solved of compensation of thermal expansions and sealing of gaps; for optimization of structural mass. The specially created dispersion-hardened powder alloy based on nichrome and aluminum with yttrium dioxide with decreased specific mass of 7500 kg/m3 and lighter felt of MKRF brand are used , and honeycomb filler of three-layer panel is replaced by the filler with square cell.

Annotation: The paper presents the original test methods with simulation of axial loads nx＜＜ 1 and nx ＞＞1 and the test stands which were used on testing the Zenit-2 ILV large-sized nose fairing.

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: 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:

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.