MATRIX ROCKET ENGINE SYSTEM WITH INDIVIDUAL DIGITAL MANAGEMENT OF THE THRUST VALUE OF EACH MOTOR CELL FOR SMALL SPACECRAFT Russian patent published in 2018 - IPC B64G1/40 

FIELD: engines and pumps; astronautics.

SUBSTANCE: invention relates to propulsion systems for small spacecraft (SSC). Monolithic heat-resistant dielectric substrate contains conical micropores orderly placed on the surface and filled with solid fuel. On the centers of the bases of cone-shaped micropores spherical ignitors are placed, fixed in through cylindrical micropores and clamped between the centering holes of the bus bars of rows and columns of the first heat-resistant dielectric membrane, on which a second heat-resistant dielectric membrane is superimposed with through cone-shaped micropores forming nozzles over cone-shaped micropores filled with solid fuel. Address bus bars of rows and columns are connected, respectively, with a row decoder and, through the address switch motor cells, with a column decoder and a data decoder, controlling the coordinates and values of thrust of motor cells. Inputs of the decoders are connected to the information outputs of the memory block of alternative code combinations whose inputs are connected to the outputs of the memory block of the spent code combinations.

EFFECT: increase in the accuracy of SSC maneuvering.

1 cl, 3 dwg