Annotation: The technique is proposed of reliability evaluation of space launch vehicle low pressure air thermostating system joints hoses. By calculation method, high reliability level was confirmed of hoses of joints being an interface elements of launch vehicle launch complexes.

Annotation: The problem is defined of designing the space rocket low-pressure air thermostating systems joints. The basic requirements imposed to the joints from the side of space rocket and ground complex are determined and stated. For this purpose, the analysis of operating conditions and possible situations during rocket launches is made. Besides, the methodological principles based on problematic, systematic, and structuralfunctional approach were applied using the theoretical and empirical capabilities, attraction of general scientific and special investigation methods, as well as historical and logical methods. The list of topical issues is reflected for implementation in joint’s design. The ways are proposed to create the joints meeting the requirements imposed. As a result, it was ascertained that the joints can be made of simpler and at the same time failure-free design in the form of combined triune rubber hose fitted with a metal fixation/release unit installed on a sealing flange in a special groove. Of special note is the versatility of the proposed technical solution for use in any of the space launch systems known in the world’s practice. The article is concluded with following: the basic requirements have been formulated for ground complexes thermostating systems joints to ensure space rockets prelaunch processing and launch, in doing so, the topical problems were defined; the scientific principles were proposed to design the thermostating systems joints for comprehensive solution of the topical problems , including potential critical situations; the thermostating systems joints have been developed, manufactured and have successfully passed the ground development tests with simulation of the conditions maximally close to operating ones at static operating air pressures and in off-nominal situations.

Annotation: A series of materials is proposed for creation of space launch vehicle low-pressure air thermostating systems joints hoses. The topical issues are considered of materials designing with consideration for specific features of the hoses as special industrial rubber articles of launch vehicle launch sites.

Annotation: The results of ground development test and investigation of Cyclone-4 ILV low-pressure air thermostating system joints are presented. The obtained test data is analyzed, and conclusions are drawn on the effect of different factors on joint performance including force action on ILV in disconnection. An assessment of applicability of the tested joints, as baseline design, on other similar space launch systems is performed.

Annotation: The range of problems of development testing of thermostating systems mating hoses for the needs of space rocketry building is most topical. In publications, insufficient attention is given to the presented range of problems. The purpose of this article is to fill in this gap. Testing of the hoses performed in accordance with comprehensive program implies a number of sequential tests and has its peculiarities. Generally, these are factory tests, participation in system and integrated tests and participation in flight tests of a space rocket. Special reference was made to the role of accelerated climatic tests, as a part of factory tests, to confirm warranty obligations for the hoses. In conclusion of the article, the concept was formulated on organization of development testing of space rockets thermostating systems hoses that reflects test peculiarities and the conclusion was made that conducting the testing of hoses according to the presented sequence ensures creation of articles that meet the requirements imposed.

Annotation: Explosive bolts are widely used as actuating devices in the spacecraft separation systems. Explosive bolt body is divided into parts as a result of engagement of the pyromixture placed inside. Activated explosive bolts have negative mechanical effect on the interface elements and sensitive electronic devices installed nearby owing to explosive behavior of the pyromixture combustion, generating shock front with high pressure and velocities, impacts and collisions of the structural units. Cumulative effect of the above factors on the separated objects is called pyroshock. For separation systems with increased requirements to external actions and cleanliness, authors developed a shear explosive bolt or pyrobolt, divided into parts, cutting the body walls in segments, which are set in motion by action of the pressure of gases, released as a result of pyrocartridge activation. The basic sources of pyroshock for these shear explosive bolts with segments are: combustion of pyromixture, internal impacts of structural units against the bolt body; cutting of body wall in segments, release of preliminary deformed interface after activation. Structural solutions are presented to reduce the pyroshock per each of the components. Vibration impulsive loading during pyromixture combustion is reduced by optimization of explosive quantity, finding its minimum to provide the reliable activation of the device. To reduce the impact on the explosive bolt elements and shock front interface the rubber gasket is installed in the path of shock wave distribution, partially disseminating and absorbing its kinetic energy. Damper, made of easily deformable aluminum alloy, is also installed to decrease the internal impact of the rod against the explosive bolt body. Functional testing of the device, using the pendulum suspension and measuring separation speed and vibration impulsive loading, showed that body parts of the shear explosive bolt with segments are separated without significant impact loads and discharge of high-temperature gases and debris, providing reliable separation of compartments and units without damaging the sensitive equipment. Obtained values of the mechanical momentum, I = 0,4÷0,7 N•s and shock load spectrum – g-load 1950 g at the frequency range up to 5000 Hz, meet the up-to-date requirements to pyrotechnical devices.