METHOD OF MINIMISING ZONES OF EXCLUSION OF CARRIER ROCKET SEPARATED PARTS Russian patent published in 2018 - IPC F42B15/36 B64G1/64 

FIELD: cosmonautics; rocket technology.

SUBSTANCE: invention relates to rocket and space technology and can be used to reduce the areas of falling separating parts of stages of launch vehicles. According to the method, in the pre-flight preparation stage of the launch vehicle, the separating parts are distinguished, differing in the degree of their destruction in the dense layers of the atmosphere after separation from the carrier rocket. Calculate the parameters of motion before they fall on the surface of the exclusion zone. Calculate the amount of heat produced by the detachable part due to aerodynamic heating when moving on the atmospheric portion of the descent trajectory to a specified altitude, where its combustion should end. Calculate the necessary additional amount of heat to ensure complete combustion of the segregating part in the atmosphere. Determine the required amount of energy material to ensure that a given amount of heat is obtained. As a filler material, a material capable of combustion in the absence of an additional oxidizer and having the appropriate characteristics to ensure the requirements of operating conditions in the composition of the separating part at all sites of its functioning is selected. Number and position of the ignition points of the energy material in the composition of the separating part is determined from the condition of its burning at a given time interval. Initiation of ignition of said material is carried out after the predetermined parameters of the motion of the detachable part are reached at the atmospheric portion of the descent path, taking into account the duration of the combustion process time interval and the design of the detachable part to its possible destruction to large fragments.

EFFECT: decrease in the areas of alienation zones because of the separated parts due to ensuring their complete combustion in the atmospheric section of the descent trajectory.

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