FIELD: engines and pumps.
SUBSTANCE: invention relates to rocketry. Proposed method comprises mechanical cutting of propellant to separate elements with sector-shape cross-section by drawing the cutting head along the body which has circular and radial cutting edges and removing said propellant elements. Said cutting head is secured at the centre of bar directed in the holes of covers fitted on body ends. Propellant is cut off in several passes of cutting head to decreased head drawing force and to ease of removal of cut propellant elements.
EFFECT: safe removal, ruled out rocket body damages.
3 cl, 2 dwg
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