FIELD: cosmonautics.
SUBSTANCE: invention relates to rocket propulsion systems and is intended for use as a multi-vector multi-matrix reconfigurable propulsion system (MMRPS) of small spacecraft. In the initial state, the MMRPS contains three compactly nested cylindrical MHRD substrates with a wavy outer contour with a matrix organization of an ordered array of motor cells consisting of multidirectional ranged by volume solid-propellant motor elements. During deployment, the cylindrical with wavy outer contour MHRD substrates linearly extend relative to each other by outer contour, carried out by means of a telescopic stay controlled by a reversible step motor connected to the controller, which is also connected to a memory unit of alternative code combinations for subsequent correction of the position of the MHRD substrates. Control over values and direction of jet thrust, sampling of motor matrices is carried out using three decoders: rows, columns, data, commutators of motor cells and sampling of motor matrices, address generators of activated igniters of motor cells, memory units of spent and alternative code combinations, controller.
EFFECT: possibility of targeted geometrical adjustment of MMRPS configuration consisting of more than two motor matrix structures with individual traction and power characteristics.
1 cl, 4 dwg
