METHOD FOR MINIMIZATION OF EXCLUSION ZONES FOR CARRIER ROCKET SEPARATING PARTS AND DEVICE FOR ITS IMPLEMENTATION

摘要

FIELD: astronautics.;SUBSTANCE: group of inventions relates to aerospace engineering and can be used to reduce areas of falling parts of carrier rocket stages. Method consists in the fact that at the pre-flight preparation stage of the carrier rocket the parameters of the motion of the separating parts – SP are determined to their falling to the ground. Based on the results of calculations, sections are determined on escapement path for impact on SP. Signal is generated during autonomous flight of SP and additional structure is subjected to impact on structure. When forming SP from polymer composite materials, a combustion system consisting of several modules is installed on the structure of SP, providing for thermal loading of extracted masses of the structure of SP by supplying heat contained in combustion products of a mixture of oxygen and propane gases. Amount of heat released by each module is determined from the condition for heating the selected mass of the SP structure to the combustion temperature. Ratio of mass seconds flow of oxygen and propane in a specific module of the combustion system, direction of movement of jets of combustion products is determined from the condition of ensuring operability of the module structure on the interval of heating time, minimum reserves of oxygen and propane. Number of modules - points of thermal loading of structure of SP for providing heating of selected mass of structure of SP to combustion temperature is selected from condition of combustion of structure SP at specified time interval.;EFFECT: reduction of areas of falling of separating parts by their burning at atmospheric section of descent trajectory.;2 cl, 3 dwg